EP2340358A1 - Assembly including a turbine disc for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disc of such an assembly - Google Patents
Assembly including a turbine disc for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disc of such an assemblyInfo
- Publication number
- EP2340358A1 EP2340358A1 EP09753955A EP09753955A EP2340358A1 EP 2340358 A1 EP2340358 A1 EP 2340358A1 EP 09753955 A EP09753955 A EP 09753955A EP 09753955 A EP09753955 A EP 09753955A EP 2340358 A1 EP2340358 A1 EP 2340358A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine
- openings
- radial annular
- trunnion
- assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to the field of dual-body gas turbine engines and, more particularly, the cooling of a high-pressure turbine disk of a dual-body gas turbine engine.
- a front-blower and double-body turbojet engine comprises a low-pressure body, called BP body, and a high-pressure body, called HP body.
- a front-blown double-bladed turbojet engine conventionally comprises, from upstream to downstream, a blower, a LP compressor stage, an HP compressor stage, a combustion chamber, an HP turbine stage and a LP turbine stage.
- the shaft of the body BP is guided in rotation in bearings supported by the fixed structure of the engine while the shaft of the HP body is guided by bearings supported by the BP body, the shafts of the two bodies being concentric.
- turbojet engine During operation of the turbojet engine, a mixture of air and fuel is burned in the combustion chamber of the engine to create the thrust required for the displacement of the aircraft on which the turbojet engine is mounted. After combustion, a gas flow at very high temperature circulates in the HP turbine of the turbojet engine.
- HP turbine disk The elements of the turbine, in particular the HP body turbine disk, hereafter referred to as HP turbine disk, are subjected to very high temperatures. high.
- the engine is provided with cooling circuits in which air, drawn upstream of the HP turbine, flows, upstream and downstream in the turbojet, internally to the HP turbine disk. and externally to the BP tree.
- the HP turbine disk cooling circuit is referred to as the cooling circuit of the turbine disk bore, better known by its English name "Circuit Bore Cooling".
- the HP trunnion includes, inter alia, a ring for mounting the bearing 17 for guiding the HP body on the LP shaft as shown in FIG.
- the HP trunnion 10 is fixed by its upstream end to the HP turbine disk 20, the HP turbine disk 20 comprising a radial annular fixing flange 25 coming into contact with a radial annular portion 15 of the trunnion.
- HP 10 The attachment flange 25 of the HP turbine disk 20 is bolted to the HP journal 10 by longitudinal bolts 2.
- the through openings 11 ventilation of the HP 10 trunnion, allowing the evacuation of the cooling air flow, are provided downstream of the portion of the HP trunnion 10 which is bolted to the HP turbine disk 20.
- the openings ventilation through 11 are formed in a frustoconical portion 12 of the HP 10 trunnion, flared upstream, which is highly mechanically stressed in operation.
- the through openings ventilation 11 are machined obliquely in the frustoconical portion 12 of the HP trunnion 10.
- the ventilation openings 11 are not orthogonal to the surface of the frustoconical portion 12 of the HP trunnion 10.
- These oblique openings 11 are difficult to machine, the frustoconical portion 12 of the HP trunnion 10 being difficult to access by the machining tools.
- the through ventilation openings 11 have sharp edges with concentration of fatigue stresses that are likely to weaken the pin HP 10 during its operation.
- the Applicant proposes an assembly of a turbine disk of a gas turbine engine and a bearing support journal, the turbine disc comprising a radial annular mounting flange integral with a radial annular portion of the trunnion by bolts, the bolts successively passing through fixing bores formed in the radial annular flange for fastening the turbine disk and in the radial annular portion of the trunnion, together characterized by the fact that the radial annular portion of the trunnion comprises air circulation openings, the openings being formed between the fixing bores of the trunnion.
- the flow openings of the cooling air flow are formed on the radial annular portion of the journal between the journal fixing bores. This advantageously allows to distribute the mechanical stresses on said radial annular portion of the pin between the fixing bores and the cooling openings, the level of mechanical stress for each bore and each opening being then lower.
- the mounting flange is easily accessible which facilitates the machining of the discharge openings which can be made at the same time as the fixing bores.
- the frustoconical portion of the trunnion no longer performs a cooling air evacuation function, which advantageously makes it possible to add material to this part in order to increase the mass close to the axis of the trunk. rotation of the pin (which is also the axis of the motor) and thus reduce the fatigue caused by the rotation of the pin.
- the radial annular flange for fixing the turbine disk is in the form of a crenellated radial annular band comprising teeth separated by slots, the turbine mounting bores being formed in the teeth of said crenellated strip.
- the radial annular fixing flange is advantageously castellated to reduce the mass of the turbine while allowing the attachment of the turbine to the trunnion.
- the slots of the radial annular fixing flange are arranged for, during attachment of the turbine to the journal, correspond with the air circulation openings provided on the radial annular portion of the journal.
- the air flow circulates successively between the teeth of the mounting flange of the turbine and in the air circulation openings of the spigot.
- the circulation openings and the fixing bores are arranged circumferentially on the radial annular portion of the journal.
- the mechanical stresses are uniformly distributed around the circumference of the trunnion, avoiding the formation of areas of weakness.
- the trunnion comprises a frustoconical portion, downstream of its radial annular portion, comprising an inner radial portion, close to the axis of rotation, thickened ensuring the mechanical strength of the disk, the weight distribution being thus optimized.
- the part The frustoconical trunnion serves a mechanical reinforcement and limits the impact of the centrifugal forces on the trunnion.
- a sealing disc mounted downstream of the journal, is bolted with the journal and the turbine disc, the sealing disc including circulation openings which are aligned with the circulation openings of the journal.
- the sealing disc advantageously makes it possible to seal while allowing the passage of the cooling air of the turbine disc.
- the passage section of the circulation openings of the sealing disk is adapted to calibrate the flow rate of the flow of air.
- the sealing disc is a lightweight mechanical part that is easy to machine.
- the invention also relates to a cooling circuit of the turbine disk in a gas turbine engine comprising an exhaust passage, downstream of the turbine disk, passing through said openings of an assembly as described above.
- the cooling circuit comprises an upstream passage through a central bore of the turbine disk, upstream of the openings of said assembly.
- the cooling circuit in a dual-body engine comprises a high pressure turbine and a low pressure turbine, the turbine of said assembly being the high pressure turbine .
- the circuit comprises a downstream passage, formed downstream of the openings of said assembly, for partially cooling the low pressure turbine.
- FIG. 1 represents a view in axial section of a turbojet engine comprising a cooling circuit of the turbine disk of a turbojet engine according to the prior art
- FIG. 2 shows an axial sectional view of a turbojet engine comprising a cooling circuit of the turbine disk of a turbojet according to the invention
- FIG. 3 represents a perspective view of a turbine disk and a journal of a turbojet according to the invention, the disk and the journal being partially represented;
- FIG. 4 shows the turbine disk and a portion of the pin of Figure 3;
- FIG. 5 schematically represents, in cross-section, the fastening of the turbine disc to the journal of FIG. 4, seen from upstream to downstream, and
- FIG. 6 partially represents, in perspective, a turbine disc, a trunnion and a labyrinth seal according to a second embodiment of the invention.
- a front-blower and double-body turbojet engine comprises a low-pressure body, called BP body, and a high-pressure body, called HP body.
- the terms “inside” and “outside” are defined radially with respect to the axis of the motor.
- a cylinder extending along the axis of the engine has an inner face facing the axis of the motor and an outer surface opposite to its inner surface.
- the HP turbine stage comprises an HP turbine disk 200 which is mounted integral with an HP pin 100, upstream of the latter.
- the HP 200 turbine disk is in the form of a bladed wheel whose blades extend radially and externally relative to the axis of the motor.
- the HP turbine disk 200 comprises a central bore 201 through which the BP shaft passes.
- the thickness of the HP turbine disk 200 is not uniform, the disk 200 comprising a circumferential bulge near its central opening 201.
- the HP turbine disk 200 comprises centrally an axial extra thickness, mechanical reinforcement, so as to increase the mass of the disk 200 near the axis of the motor and thus reduce the mechanical stresses in operation.
- the HP turbine disk 200 comprises a radial upstream fastening annular flange 240 bolted to a drum associated with a flange 241 for supporting sealing strips and guiding the cooling air of the blades. turbine, the drum being bolted to the HP compressor of the engine.
- the drum makes it possible to transmit to the compressor HP the energy of the combustion of the engine recovered by the turbine disc 200.
- the HP turbine disk 200 includes a downstream radial annular flange 250 for maintaining the downstream HP 100 trunnion.
- the downstream flange 250 is in the form of a crenellated radial annular band 250 comprising teeth 251 separated by crenellations 252 as shown in FIGS. 4 and 5. Thereafter, a slot is defined as the space between two teeth. 251 successive of the crenellated band 250.
- the teeth 251 of the downstream fastening flange 250 (shown in hatched form) extend radially towards the axis of the motor and are directed towards the central bore 201 of the turbine disk 200.
- the trunnion HP 100 is in the form of a part of revolution, substantially flared upstream and extending along the axis of the motor.
- the trunnion HP 100 comprises, from upstream to downstream, a radial annular fixing portion 150, arranged to attach to the flange 250 of the HP turbine disk 200, a frustoconical portion 102 and a longitudinal cylindrical portion 103.
- the longitudinal cylindrical portion 103 of the trunnion HP 100 comprises at its downstream end an external thread intended to receive an outer ring on which is mounted an inter-shaft bearing, this bearing (not shown) allowing the HP turbojet body to be supported by the BP shaft.
- the frustoconical portion 102 of the trunnion HP 100 comprises, for its part, a circumferential radial protruding portion 105, mechanical reinforcement, oriented towards the axis of the motor and for reinforcing the mass of the trunnion HP 100.
- the protruding portion 105 is formed near the axis of the motor to reduce the mechanical stresses in operation, in particular, the stresses resulting from centrifugal forces.
- the frustoconical portion 102 of the HP 100 trunnion comprises radial sealing blades 104, forming labyrinth seal, oriented radially outwardly of the engine and intended to seal between the trunnion HP 100 and a mechanical part mounted externally to the trunnion HP 100.
- the frustoconical portion 102 of the trunnion HP 100 further comprises an inner frustoconical flange 107 secured to a sealing sleeve 400 of the engine shaft BP.
- the sealing sheath 400 is in the form of a cylinder extending axially, externally to the LP shaft of the engine and internally to the turbine disk 200.
- the sealing sheath 400 makes it possible to protect the LP shaft against excessive temperatures.
- An annular cooling air circulation duct of the turbine disk is formed internally to the HP turbine disk 200 and outside the sealing sheath 400. The circulation of the cooling air in the channel is represented by arrows on the turbine disk. Figures 2 and 3.
- the radial annular fixing portion 150 of the pin 100 comprises fixing bores 120 alternating with openings 110 for circulating a flow of cooling air of the turbine disc, hereinafter referred to as ventilation openings 110, the bores 120 and the openings 110 being disposed circumferentially on the radial annular fixing portion 150.
- the bores 120 and the openings 110 are uniformly distributed over the circumference.
- the fixing bores 120 and the ventilation openings 110 of the pin 100 are arranged to correspond respectively to the fixing bores 220 and the slots 252 of the HP 200 turbine disk.
- the bores 120 and the openings 110 of the trunnion 100 advantageously make it possible to reduce the tangential stresses in this area of the trunnion HP 100 by the effect of pitch.
- the fixing bores 120 and the ventilation openings 110 are here circular and have, in this example, the same opening section. It goes without saying that the bores 120 and the openings 110 could have shapes (oblong, rectangular, etc.) and different sections.
- the radial annular fixing portion 150 further comprises radial sealing blades provided at its outer radial end, similar to those formed on the frustoconical portion 102 of the pin 100.
- the downstream face of the downstream mounting flange 250 of the HP 200 turbine disk is brought into surface contact with the upstream face of the annular portion. 150 of the trunnion HP 100.
- the fixing holes 120 of the trunnion 100 are aligned with fixing bores 220 of the HP 200 turbine disc. Due to the alignment of the fixing bores 120, 220, the ventilation openings 110 of the HP trunnion 100 are aligned with the slots 252 of the mounting flange 250 of the HP turbine disk 200. In other words, the ventilation openings 110 of the trunnion 100 HP are aligned with the openings formed between the teeth 251 of the mounting flange. 250 of the HP 200 turbine disk.
- a bolt screw 21 is introduced successively into a fastening bore 120 of the journal 100 and then into the fastening bore 220 of the turbine disc 200 with which it is mounted. aligned. A nut 22 of bolt 20 is then screwed to the end of said screw 21 to secure the attachment. This bolting step is repeated for each fixing bore 120 of the trunnion 100, the turbine disc 200 then being integral with the trunnion HP 100.
- the cooling air can circulate between the bolts 20 for holding the trunnion HP 100.
- the radial annular portion 150 of the trunnion 100 allows the attachment to the turbine disk 200 and the evacuation of the cooling air flow of the turbine disk 200.
- a mixture of air and fuel is burned in the combustion chamber of the engine to create the thrust required for the displacement of the aircraft on which the turbojet engine is mounted.
- a gas flow at very high temperature circulates in the HP turbine of the turbojet engine.
- the HP 200 turbine disk is subjected to very high temperatures.
- an airflow is taken upstream of the turbine disk 200, at the level of the HP compressor, and flows upstream and downstream in the turbojet, internally to the HP 200 turbine disk and externally to the sealing sheath 400.
- the annular cooling air stream takes heat from the turbine disk 200 for cooling and forming a cooling air envelope around the sealing sheath 400, thereby protecting the mechanical parts mounted therein.
- the cooling air After cooling the HP turbine disk 200, the cooling air is discharged through the air circulation passages which are formed between the bolts 20 connecting the HP 100 trunnion to the HP 200 turbine disk as shown in FIG. 2 and 3. Downstream of the airflow openings, the cooling air cools the LP turbine of the dual-body engine. In other words, the cooling air circulates successively between the teeth 251 of the flange downstream mounting 250 of the HP 200 turbine disk and through the ventilation openings 110 formed in the HP 100 trunnion.
- a labyrinth sealing disc 300 is mounted with the HP turbine disc 200 and the HP trunnion 100, the sealing disc 300 being mounted downstream of the HP trunnion 100.
- the labyrinth sealing disc 300 is in the form of a radial annular ring comprising at its outer radial end, ie the farthest from the axis of the motor, radial sealing blades 304 forming a labyrinth seal, and comprising at its inner end, ie the closest to the axis of the engine, a radial annular fixing band 350.
- the radial annular fixing band 350 of the sealing disc 300 comprises fixing bores 320 alternating with ventilation openings 310, the bores 320 and the openings 310 being arranged circumferentially on the radial annular fixing band 350.
- the fixing bores 320 and the ventilation openings 310 of the sealing disc 300 are arranged to correspond with their counterparts on the HP 100 trunnion.
- the face facing downstream of the downstream fastening flange 250 of the HP 200 turbine disk is brought into surface contact with the face facing upstream of the radial annular portion 150 of the trunnion.
- HP 100 the face facing upstream of the fastening strip 350 of the sealing disk 300 is brought into surface contact with the face facing downstream of the radial annular portion 150 of the HP pin 100.
- the fixing bores 120, 220, 320 of the HP turbine disk 200, the HP trunnion 100 and the sealing disk 300 are aligned.
- the openings 110, 310 of the HP trunnion 100 and the sealing disc 300 are aligned with the slots 252 of the fastening flange 250 of the HP turbine disc 200.
- the turbine disc 200, the journal 100 and the sealing disc 300 are then bolted together via the fastening bores 120, 220, 320 which are aligned. After fixing, air circulation passages are formed between the holding bolts 20.
- the passage section of the ventilation openings 310 of the sealing disk 300 is adapted so as to be able to calibrate the flow rate of the cooling air in the central bore 201 of the turbine disk 200.
- the diameter circular ventilation openings 310 of the sealing disc 300 are smaller than the diameter of the circular ventilation openings 110 of the HP 100 trunnion, resulting in a reduction of the cooling air flow in the central bore 201.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to an assembly that comprises a turbine disc (200) for a gas turbine engine and a bearing-supporting journal (100), the turbine disc (200) including a radial annular fastening flange (250) connected by bolts (2) to a radial annular portion (150) of the journal (100), wherein the bolts (2) extend in series through fastening bores (120, 220) in the fastening radial annular flange (250) of the turbine disc (200) and in the radial annular portion (150) of the journal (100), and wherein said assembly is characterised in that the radial annular portion (150) of the journal (100) includes air-flow openings (110) between the fastening bores (120) of the journal (100).
Description
Ensemble d'un disque de turbine d'un moteur à turbine à gaz et d'un tourillon support de palier, circuit de refroidissement d'un disque de turbine d'un tel ensemble Set of a turbine disk of a gas turbine engine and a bearing support journal, cooling circuit of a turbine disk of such a set
La présente invention concerne le domaine des moteurs à turbine à gaz à double corps et, plus particulièrement, le refroidissement d'un disque de turbine haute pression d'un moteur à turbine à gaz à double corps.The present invention relates to the field of dual-body gas turbine engines and, more particularly, the cooling of a high-pressure turbine disk of a dual-body gas turbine engine.
Un turboréacteur à soufflante avant et à double corps, par exemple, comprend un corps à basse pression, dit corps BP, et un corps à haute pression, dit corps HP.For example, a front-blower and double-body turbojet engine comprises a low-pressure body, called BP body, and a high-pressure body, called HP body.
Par convention, dans la présente demande, les termes « amont » et « aval » sont définis par rapport au sens de circulation de l'air dans le turboréacteur. Ainsi, un turboréacteur à double corps à soufflante avant comprend classiquement, d'amont en aval, une soufflante, un étage compresseur BP, un étage compresseur HP, une chambre de combustion, un étage de turbine HP et un étage de turbine BP.By convention, in the present application, the terms "upstream" and "downstream" are defined with respect to the direction of air circulation in the turbojet engine. Thus, a front-blown double-bladed turbojet engine conventionally comprises, from upstream to downstream, a blower, a LP compressor stage, an HP compressor stage, a combustion chamber, an HP turbine stage and a LP turbine stage.
L'arbre du corps BP est guidé en rotation dans des paliers supportés par la structure fixe du moteur tandis que l'arbre du corps HP est guidé par des paliers supportés par le corps BP, les arbres des deux corps étant concentriques.The shaft of the body BP is guided in rotation in bearings supported by the fixed structure of the engine while the shaft of the HP body is guided by bearings supported by the BP body, the shafts of the two bodies being concentric.
Lors du fonctionnement du turboréacteur, un mélange d'air et de carburant est brûlé dans la chambre de combustion du moteur pour créer la poussée nécessaire au déplacement de l'aéronef sur lequel est monté le turboréacteur. Après combustion, un flux de gaz à très haute température circule dans la turbine HP du turboréacteur.During operation of the turbojet engine, a mixture of air and fuel is burned in the combustion chamber of the engine to create the thrust required for the displacement of the aircraft on which the turbojet engine is mounted. After combustion, a gas flow at very high temperature circulates in the HP turbine of the turbojet engine.
Les éléments de la turbine, en particulier le disque de turbine du corps HP, désigné par la suite disque de turbine HP, sont soumis à des températures très
élevées. Afin de protéger le disque de turbine HP, on ménage dans le moteur des circuits de refroidissement dans lesquels de l'air, prélevé en amont de la turbine HP, circule, d'amont en aval dans le turboréacteur, intérieurement au disque de turbine HP et extérieurement à l'arbre BP. Le circuit de refroidissement du disque de turbine HP est désigné circuit de refroidissement de l'alésage du disque de turbine, plus connu sous sa dénomination anglaise « Circuit Bore Cooling ».The elements of the turbine, in particular the HP body turbine disk, hereafter referred to as HP turbine disk, are subjected to very high temperatures. high. In order to protect the HP turbine disk, the engine is provided with cooling circuits in which air, drawn upstream of the HP turbine, flows, upstream and downstream in the turbojet, internally to the HP turbine disk. and externally to the BP tree. The HP turbine disk cooling circuit is referred to as the cooling circuit of the turbine disk bore, better known by its English name "Circuit Bore Cooling".
Après avoir refroidi le disque de turbine HP, l'air de refroidissement traverse une pluralité d'ouvertures de ventilation formées dans le tourillon solidaire du disque HP et monté en aval de ce dernier, le tourillon étant désigné par la suite tourillon HP. Le tourillon HP comprend, entre autres, une bague pour le montage du palier 17 permettant le guidage du corps HP sur l'arbre BP comme représenté sur la figure 1.After cooling the HP turbine disk, the cooling air passes through a plurality of ventilation openings formed in the integral pin of the disk HP and mounted downstream thereof, the pin being designated by the following HP pin. The HP trunnion includes, inter alia, a ring for mounting the bearing 17 for guiding the HP body on the LP shaft as shown in FIG.
Toujours en référence à la figure 1, le tourillon HP 10 est fixé par son extrémité amont au disque de turbine HP 20, le disque de turbine HP 20 comprenant une bride annulaire radiale de fixation 25 venant en contact sur une partie annulaire radiale 15 du tourillon HP 10. La bride de fixation 25 du disque de turbine HP 20 est boulonnée au tourillon HP 10 par des boulons longitudinaux 2.Still referring to FIG. 1, the HP trunnion 10 is fixed by its upstream end to the HP turbine disk 20, the HP turbine disk 20 comprising a radial annular fixing flange 25 coming into contact with a radial annular portion 15 of the trunnion. HP 10. The attachment flange 25 of the HP turbine disk 20 is bolted to the HP journal 10 by longitudinal bolts 2.
Les ouvertures traversantes de ventilation 11 du tourillon HP 10, permettant l'évacuation du flux d'air de refroidissement, sont ménagées en aval de la partie du tourillon HP 10 qui est boulonnée au disque de turbine HP 20. De manière classique, les ouvertures traversantes de ventilation 11 sont ménagées dans une partie tronconique 12 du tourillon HP 10, évasée vers l'amont, qui est très sollicitée mécaniquement en fonctionnement.The through openings 11 ventilation of the HP 10 trunnion, allowing the evacuation of the cooling air flow, are provided downstream of the portion of the HP trunnion 10 which is bolted to the HP turbine disk 20. Conventionally, the openings ventilation through 11 are formed in a frustoconical portion 12 of the HP 10 trunnion, flared upstream, which is highly mechanically stressed in operation.
Les ouvertures traversantes de ventilation 11 sont usinées obliquement dans la partie tronconique 12 du tourillon HP 10. Autrement dit, les ouvertures de ventilation 11 ne sont pas orthogonales à la surface de la partie tronconique 12 du
tourillon HP 10. Ces ouvertures obliques 11 sont difficiles à usiner, la partie tronconique 12 du tourillon HP 10 étant difficilement accessible par les outils d'usinage. En outre, après usinage, les ouvertures traversantes de ventilation 11 possèdent des arêtes vives avec concentration de contraintes de fatigues qui sont susceptibles d'affaiblir le tourillon HP 10 au cours de son fonctionnement.The through openings ventilation 11 are machined obliquely in the frustoconical portion 12 of the HP trunnion 10. In other words, the ventilation openings 11 are not orthogonal to the surface of the frustoconical portion 12 of the HP trunnion 10. These oblique openings 11 are difficult to machine, the frustoconical portion 12 of the HP trunnion 10 being difficult to access by the machining tools. In addition, after machining, the through ventilation openings 11 have sharp edges with concentration of fatigue stresses that are likely to weaken the pin HP 10 during its operation.
Afin d'éliminer ces inconvénients, la demanderesse propose un ensemble d'un disque de turbine d'un moteur à turbine à gaz et d'un tourillon support de palier, le disque de turbine comprenant une bride annulaire radiale de fixation solidaire d'une partie annulaire radiale du tourillon par des boulons, les boulons traversant successivement des alésages de fixation ménagés dans la bride annulaire radiale de fixation du disque de turbine et dans la partie annulaire radiale du tourillon, ensemble caractérisé par le fait que la partie annulaire radiale du tourillon comprend des ouvertures de circulation d'air, les ouvertures étant ménagées entre les alésages de fixation du tourillon.In order to eliminate these drawbacks, the Applicant proposes an assembly of a turbine disk of a gas turbine engine and a bearing support journal, the turbine disc comprising a radial annular mounting flange integral with a radial annular portion of the trunnion by bolts, the bolts successively passing through fixing bores formed in the radial annular flange for fastening the turbine disk and in the radial annular portion of the trunnion, together characterized by the fact that the radial annular portion of the trunnion comprises air circulation openings, the openings being formed between the fixing bores of the trunnion.
Les ouvertures de circulation du flux d'air de refroidissement sont formées sur la partie annulaire radiale du tourillon entre les alésages de fixation du tourillon. Cela permet avantageusement de répartir les contraintes mécaniques sur ladite partie annulaire radiale du tourillon entre les alésages de fixation et les ouvertures de refroidissement, le niveau de contrainte mécanique pour chaque alésage et chaque ouverture étant alors plus faible.The flow openings of the cooling air flow are formed on the radial annular portion of the journal between the journal fixing bores. This advantageously allows to distribute the mechanical stresses on said radial annular portion of the pin between the fixing bores and the cooling openings, the level of mechanical stress for each bore and each opening being then lower.
La bride de fixation est facilement accessible ce qui facilite l'usinage des ouvertures d'évacuation qui pouvant être ainsi ménagées en même temps que les alésages de fixation.The mounting flange is easily accessible which facilitates the machining of the discharge openings which can be made at the same time as the fixing bores.
En outre, la partie tronconique du tourillon ne remplit plus de fonction d'évacuation d'air de refroidissement ce qui permet avantageusement d'ajouter de la matière sur cette partie afin d'augmenter la masse à proximité de l'axe de
rotation du tourillon (qui est également l'axe du moteur) et ainsi diminuer les fatigues engendrées par la rotation du tourillon.In addition, the frustoconical portion of the trunnion no longer performs a cooling air evacuation function, which advantageously makes it possible to add material to this part in order to increase the mass close to the axis of the trunk. rotation of the pin (which is also the axis of the motor) and thus reduce the fatigue caused by the rotation of the pin.
De préférence, la bride annulaire radiale de fixation du disque de turbine se présente sous la forme d'une bande annulaire radiale crénelée comprenant des dents séparées par des créneaux, les alésages de fixation de la turbine étant ménagés dans les dents de ladite bande crénelée.Preferably, the radial annular flange for fixing the turbine disk is in the form of a crenellated radial annular band comprising teeth separated by slots, the turbine mounting bores being formed in the teeth of said crenellated strip.
La bride annulaire radiale de fixation est avantageusement crénelée pour diminuer la masse de la turbine tout en permettant la fixation de la turbine au tourillon.The radial annular fixing flange is advantageously castellated to reduce the mass of the turbine while allowing the attachment of the turbine to the trunnion.
De préférence encore, les créneaux de la bride annulaire radiale de fixation sont agencés pour, lors de la fixation de la turbine au tourillon, correspondre avec les ouvertures de circulation d'air ménagées sur la partie annulaire radiale du tourillon.More preferably, the slots of the radial annular fixing flange are arranged for, during attachment of the turbine to the journal, correspond with the air circulation openings provided on the radial annular portion of the journal.
Ainsi, le flux d'air circule successivement entre les dents de la bride de fixation de la turbine et dans les ouvertures de circulation d'air du tourillon.Thus, the air flow circulates successively between the teeth of the mounting flange of the turbine and in the air circulation openings of the spigot.
De préférence, les ouvertures de circulation et les alésages de fixation sont disposés circonférentiellement sur la partie annulaire radiale du tourillon. Les contraintes mécaniques sont uniformément réparties sur le pourtour du tourillon, évitant la formation de zones de faiblesses.Preferably, the circulation openings and the fixing bores are arranged circumferentially on the radial annular portion of the journal. The mechanical stresses are uniformly distributed around the circumference of the trunnion, avoiding the formation of areas of weakness.
Selon une caractéristique particulière, le tourillon comporte une partie tronconique, en aval de sa partie annulaire radiale, comprenant une portion radiale intérieure, proche de l'axe de rotation, épaissie assurant la résistance mécanique du disque, la répartition des masses étant ainsi optimisée. La partie
tronconique du tourillon remplit un rôle de renfort mécanique et permet de limiter l'impact des efforts centrifuges sur le tourillon.According to a particular characteristic, the trunnion comprises a frustoconical portion, downstream of its radial annular portion, comprising an inner radial portion, close to the axis of rotation, thickened ensuring the mechanical strength of the disk, the weight distribution being thus optimized. The part The frustoconical trunnion serves a mechanical reinforcement and limits the impact of the centrifugal forces on the trunnion.
De préférence, un disque d'étanchéité, monté en aval du tourillon, est boulonné avec le tourillon et le disque de turbine, le disque d'étanchéité comprenant des ouvertures de circulation qui sont alignées avec les ouvertures de circulation du tourillon.Preferably, a sealing disc, mounted downstream of the journal, is bolted with the journal and the turbine disc, the sealing disc including circulation openings which are aligned with the circulation openings of the journal.
Le disque d'étanchéité permet avantageusement d'assurer l'étanchéité tout en permettant le passage de l'air de refroidissement du disque de turbine.The sealing disc advantageously makes it possible to seal while allowing the passage of the cooling air of the turbine disc.
De préférence, la section de passage des ouvertures de circulation du disque d'étanchéité est adaptée pour calibrer le débit de circulation du flux d'air.Preferably, the passage section of the circulation openings of the sealing disk is adapted to calibrate the flow rate of the flow of air.
Le disque d'étanchéité est une pièce mécanique légère qui est simple à usiner.The sealing disc is a lightweight mechanical part that is easy to machine.
En adaptant la section de passage des ouvertures de circulation du disque d'étanchéité, on peut calibrer de manière simple le débit de circulation du flux d'air.By adapting the passage section of the circulation openings of the sealing disc, it is possible to simply calibrate the flow rate of the flow of air.
L'invention concerne également un circuit de refroidissement du disque de turbine dans un moteur à turbine à gaz comprenant un passage d'évacuation, en aval du disque de turbine, passant par lesdites ouvertures d'un ensemble tel que décrit précédemment.The invention also relates to a cooling circuit of the turbine disk in a gas turbine engine comprising an exhaust passage, downstream of the turbine disk, passing through said openings of an assembly as described above.
De préférence, le circuit de refroidissement comprend un passage amont à travers un alésage central du disque de turbine, en amont des ouvertures dudit ensemble.Preferably, the cooling circuit comprises an upstream passage through a central bore of the turbine disk, upstream of the openings of said assembly.
De préférence encore, le circuit de refroidissement dans un moteur à double corps comprend une turbine à haute pression et une turbine à basse pression, la turbine dudit ensemble étant la turbine à haute pression
. Le circuit comprend un passage aval, ménagé en aval des ouvertures dudit ensemble, pour refroidir en partie la turbine à basse pression.More preferably, the cooling circuit in a dual-body engine comprises a high pressure turbine and a low pressure turbine, the turbine of said assembly being the high pressure turbine . The circuit comprises a downstream passage, formed downstream of the openings of said assembly, for partially cooling the low pressure turbine.
L'invention sera mieux comprise à l'aide du dessin annexé sur lequel : - la figure 1 représente une vue en coupe axiale d'un turboréacteur comprenant un circuit de refroidissement du disque de turbine d'un turboréacteur selon l'art antérieur ;The invention will be better understood with the aid of the appended drawing in which: FIG. 1 represents a view in axial section of a turbojet engine comprising a cooling circuit of the turbine disk of a turbojet engine according to the prior art;
- la figure 2 représente une vue en coupe axiale d'un turboréacteur comprenant un circuit de refroidissement du disque de turbine d'un turboréacteur selon l'invention ;- Figure 2 shows an axial sectional view of a turbojet engine comprising a cooling circuit of the turbine disk of a turbojet according to the invention;
- la figure 3 représente une vue en perspective d'un disque de turbine et d'un tourillon d'un turboréacteur selon l'invention, le disque et le tourillon étant représentés partiellement ;FIG. 3 represents a perspective view of a turbine disk and a journal of a turbojet according to the invention, the disk and the journal being partially represented;
- la figure 4 représente le disque de turbine et une partie du tourillon de la figure 3;- Figure 4 shows the turbine disk and a portion of the pin of Figure 3;
- la figure 5 représente schématiquement, en coupe transversale, la fixation du disque de turbine au tourillon de la figure 4, vue de l'amont vers l'aval, etFIG. 5 schematically represents, in cross-section, the fastening of the turbine disc to the journal of FIG. 4, seen from upstream to downstream, and
- la figure 6 représente partiellement, en perspective, un disque de turbine, un tourillon et un joint à labyrinthe selon une seconde forme de réalisation de l'invention.FIG. 6 partially represents, in perspective, a turbine disc, a trunnion and a labyrinth seal according to a second embodiment of the invention.
Un turboréacteur à soufflante avant et à double corps, par exemple, comprend un corps à basse pression, dit corps BP, et un corps à haute pression, dit corps HP.For example, a front-blower and double-body turbojet engine comprises a low-pressure body, called BP body, and a high-pressure body, called HP body.
Par convention, dans la présente demande, les termes « intérieur » et « extérieur » sont définis radialement par rapport à l'axe du moteur. Ainsi, un cylindre s 'étendant selon l'axe du moteur comporte une face intérieure tournée vers l'axe du moteur et une surface extérieure, opposée à sa surface intérieure.
En référence aux figures 2 et 3, l'étage de turbine HP comprend un disque de turbine HP 200 qui est monté solidaire avec un tourillon HP 100, en amont de ce dernier.By convention, in the present application, the terms "inside" and "outside" are defined radially with respect to the axis of the motor. Thus, a cylinder extending along the axis of the engine has an inner face facing the axis of the motor and an outer surface opposite to its inner surface. With reference to FIGS. 2 and 3, the HP turbine stage comprises an HP turbine disk 200 which is mounted integral with an HP pin 100, upstream of the latter.
Le disque de turbine HP 200The HP 200 turbine disk
Le disque de turbine HP 200 se présente sous la forme d'une roue aubagée dont les aubes s'étendent radialement et extérieurement par rapport à l'axe du moteur. Le disque de turbine HP 200 comprend un alésage central 201 au travers duquel passe l'arbre BP. L'épaisseur du disque de turbine HP 200 n'est pas uniforme, le disque 200 comprenant un renflement circonférentiel à proximité de son ouverture centrale 201. Autrement dit, le disque de turbine HP 200 comprend centralement une surépaisseur axiale, de renfort mécanique, de manière à augmenter la masse du disque 200 à proximité de l'axe du moteur et ainsi diminuer les sollicitations mécaniques en fonctionnement.The HP 200 turbine disk is in the form of a bladed wheel whose blades extend radially and externally relative to the axis of the motor. The HP turbine disk 200 comprises a central bore 201 through which the BP shaft passes. The thickness of the HP turbine disk 200 is not uniform, the disk 200 comprising a circumferential bulge near its central opening 201. In other words, the HP turbine disk 200 comprises centrally an axial extra thickness, mechanical reinforcement, so as to increase the mass of the disk 200 near the axis of the motor and thus reduce the mechanical stresses in operation.
En référence à la figure 3, le disque de turbine HP 200 comprend une bride annulaire radiale de fixation amont 240 boulonnée à un tambour associé à un flasque 241 de support de lames d'étanchéité et assurant le guidage de l'air de refroidissement des aubes de turbine, le tambour étant boulonné au compresseur HP du moteur. Le tambour permet de transmettre au compresseur HP l'énergie de la combustion du moteur récupérée par le disque de turbine 200.With reference to FIG. 3, the HP turbine disk 200 comprises a radial upstream fastening annular flange 240 bolted to a drum associated with a flange 241 for supporting sealing strips and guiding the cooling air of the blades. turbine, the drum being bolted to the HP compressor of the engine. The drum makes it possible to transmit to the compressor HP the energy of the combustion of the engine recovered by the turbine disc 200.
Le disque de turbine HP 200 comprend une bride annulaire radiale de fixation aval 250 destinée à maintenir le tourillon HP 100 monté en aval. La bride aval 250 se présente sous la forme d'une bande annulaire radiale crénelée 250 comprenant des dents 251 séparées par des créneaux 252 comme représentée sur les figures 4 et 5. Par la suite, on définit un créneau comme l'espace entre deux dents 251 successives de la bande crénelée 250.
En référence à la figure 5, les dents 251 de la bride de fixation aval 250 (représentée en hachurés) s'étendent radialement vers l'axe du moteur et sont dirigées vers l'alésage central 201 du disque de turbine 200. Dans chacune des dents 251 de la bride de fixation aval 250 est usiné un alésage de fixation 220 permettant la fixation de la bride aval 250 du disque de turbine HP 200 au tourillon HP 100. La fixation du tourillon HP 100 au disque de turbine HP 200 sera détaillée par la suite.The HP turbine disk 200 includes a downstream radial annular flange 250 for maintaining the downstream HP 100 trunnion. The downstream flange 250 is in the form of a crenellated radial annular band 250 comprising teeth 251 separated by crenellations 252 as shown in FIGS. 4 and 5. Thereafter, a slot is defined as the space between two teeth. 251 successive of the crenellated band 250. With reference to FIG. 5, the teeth 251 of the downstream fastening flange 250 (shown in hatched form) extend radially towards the axis of the motor and are directed towards the central bore 201 of the turbine disk 200. 251 teeth of the downstream fastening flange 250 is machined a fixing bore 220 for fixing the downstream flange 250 of the HP 200 turbine disk HP 100 trunnion. The attachment of the HP 100 trunnion HP 200 turbine disk will be detailed by the following.
Le tourillon HP 100The HP 100 trunnion
En référence aux figures 2 et 3, le tourillon HP 100 se présente sous la forme d'une pièce de révolution, sensiblement évasée vers l'amont et s'étendant selon l'axe du moteur. Le tourillon HP 100 comprend, d'amont en aval, une partie annulaire radiale de fixation 150, agencée pour se fixer à la bride 250 du disque de turbine HP 200, une partie tronconique 102 et une partie cylindrique longitudinale 103.With reference to Figures 2 and 3, the trunnion HP 100 is in the form of a part of revolution, substantially flared upstream and extending along the axis of the motor. The trunnion HP 100 comprises, from upstream to downstream, a radial annular fixing portion 150, arranged to attach to the flange 250 of the HP turbine disk 200, a frustoconical portion 102 and a longitudinal cylindrical portion 103.
La partie cylindrique longitudinale 103 du tourillon HP 100, la plus en aval du tourillon 100, comprend à son extrémité aval un filetage extérieur destiné à recevoir une bague extérieure sur laquelle est montée un palier inter-arbres, ce palier (non représenté) permettant au corps HP du turboréacteur d'être supporté par l'arbre BP.The longitudinal cylindrical portion 103 of the trunnion HP 100, the most downstream of the trunnion 100, comprises at its downstream end an external thread intended to receive an outer ring on which is mounted an inter-shaft bearing, this bearing (not shown) allowing the HP turbojet body to be supported by the BP shaft.
En référence à la figure 3, la partie tronconique 102 du tourillon HP 100 comprend, pour sa part, une portion saillante radiale circonférentielle 105, de renfort mécanique, orientée vers l'axe du moteur et destinée à renforcer la masse du tourillon HP 100. La portion saillante 105 est ménagée à proximité de l'axe du moteur afin de diminuer les sollicitations mécaniques en fonctionnement, en particulier, les sollicitations résultant des forces centrifuges. La partie tronconique 102 du tourillon HP 100 comprend des lames radiales d'étanchéité
104, formant joint labyrinthe, orientées radialement vers l'extérieur du moteur et destinées à assurer l'étanchéité entre le tourillon HP 100 et une pièce mécanique montée extérieurement au tourillon HP 100.Referring to Figure 3, the frustoconical portion 102 of the trunnion HP 100 comprises, for its part, a circumferential radial protruding portion 105, mechanical reinforcement, oriented towards the axis of the motor and for reinforcing the mass of the trunnion HP 100. The protruding portion 105 is formed near the axis of the motor to reduce the mechanical stresses in operation, in particular, the stresses resulting from centrifugal forces. The frustoconical portion 102 of the HP 100 trunnion comprises radial sealing blades 104, forming labyrinth seal, oriented radially outwardly of the engine and intended to seal between the trunnion HP 100 and a mechanical part mounted externally to the trunnion HP 100.
La partie tronconique 102 du tourillon HP 100 comprend en outre une bride tronconique intérieure 107 maintenue solidaire d'un fourreau d'étanchéité 400 de l'arbre BP du moteur. Le fourreau d'étanchéité 400 se présente sous la forme d'un cylindre s'étendant axialement, extérieurement à l'arbre BP du moteur et intérieurement au disque de turbine 200. Le fourreau d'étanchéité 400 permet de protéger l'arbre BP contre des températures excessives. Un canal de circulation annulaire d'air de refroidissement du disque de turbine est ménagé intérieurement au disque de turbine HP 200 et extérieurement au fourreau d'étanchéité 400. La circulation de l'air de refroidissement dans le canal est représentée par des flèches sur les figures 2 et 3.The frustoconical portion 102 of the trunnion HP 100 further comprises an inner frustoconical flange 107 secured to a sealing sleeve 400 of the engine shaft BP. The sealing sheath 400 is in the form of a cylinder extending axially, externally to the LP shaft of the engine and internally to the turbine disk 200. The sealing sheath 400 makes it possible to protect the LP shaft against excessive temperatures. An annular cooling air circulation duct of the turbine disk is formed internally to the HP turbine disk 200 and outside the sealing sheath 400. The circulation of the cooling air in the channel is represented by arrows on the turbine disk. Figures 2 and 3.
La partie annulaire radiale de fixation 150 du tourillon 100 comprend des alésages de fixation 120 alternés avec des ouvertures 110 de circulation d'un flux d'air de refroidissement du disque de turbine, désignées par la suite ouvertures de ventilation 110, les alésages 120 et les ouvertures 110 étant disposées circonférentiellement sur la partie annulaire radiale de fixation 150. Dans cet exemple, les alésages 120 et les ouvertures 110 sont uniformément réparties sur la circonférence. Les alésages de fixation 120 et les ouvertures de ventilation 110 du tourillon 100 sont ménagés de manière à correspondre respectivement avec les alésages de fixation 220 et les créneaux 252 du disque de turbine HP 200.The radial annular fixing portion 150 of the pin 100 comprises fixing bores 120 alternating with openings 110 for circulating a flow of cooling air of the turbine disc, hereinafter referred to as ventilation openings 110, the bores 120 and the openings 110 being disposed circumferentially on the radial annular fixing portion 150. In this example, the bores 120 and the openings 110 are uniformly distributed over the circumference. The fixing bores 120 and the ventilation openings 110 of the pin 100 are arranged to correspond respectively to the fixing bores 220 and the slots 252 of the HP 200 turbine disk.
Les alésages 120 et les ouvertures 110 du tourillon 100 permettent avantageusement de diminuer les contraintes tangentielles dans cette zone du tourillon HP 100, par effet de pas.
Les alésages de fixation 120 et les ouvertures de ventilation 110 sont ici circulaires et possèdent, dans cet exemple, la même section d'ouverture. Il va de soi que les alésages 120 et les ouvertures 110 pourraient avoir des formes (oblongues, rectangulaires, etc.) et des sections différentes.The bores 120 and the openings 110 of the trunnion 100 advantageously make it possible to reduce the tangential stresses in this area of the trunnion HP 100 by the effect of pitch. The fixing bores 120 and the ventilation openings 110 are here circular and have, in this example, the same opening section. It goes without saying that the bores 120 and the openings 110 could have shapes (oblong, rectangular, etc.) and different sections.
La partie annulaire radiale de fixation 150 comprend en outre des lames radiales d'étanchéités ménagées à son extrémité radiale extérieure, similaires à celles ménagées sur la partie tronconique 102 du tourillon 100.The radial annular fixing portion 150 further comprises radial sealing blades provided at its outer radial end, similar to those formed on the frustoconical portion 102 of the pin 100.
Pour fixer le tourillon HP 100 au disque de turbine HP 200, on met en contact surfacique la face tournée vers l'aval de la bride de fixation aval 250 du disque de turbine HP 200 avec la face tournée vers l'amont de la partie annulaire radiale 150 du tourillon HP 100. Ensuite, on aligne les alésages de fixation 120 du tourillon 100 avec alésages de fixation 220 du disque de turbine HP 200. Du fait de l'alignement des alésages de fixation 120, 220, les ouvertures de ventilation 110 du tourillon HP 100 sont alignées avec les créneaux 252 de la bride de fixation 250 du disque de turbine HP 200. Autrement dit, les ouvertures de ventilation 110 du tourillon 100 HP sont alignées avec les ouvertures formées entre les dents 251 de la bride de fixation 250 du disque de turbine HP 200.To attach the HP trunnion 100 to the HP 200 turbine disk, the downstream face of the downstream mounting flange 250 of the HP 200 turbine disk is brought into surface contact with the upstream face of the annular portion. 150 of the trunnion HP 100. Then, the fixing holes 120 of the trunnion 100 are aligned with fixing bores 220 of the HP 200 turbine disc. Due to the alignment of the fixing bores 120, 220, the ventilation openings 110 of the HP trunnion 100 are aligned with the slots 252 of the mounting flange 250 of the HP turbine disk 200. In other words, the ventilation openings 110 of the trunnion 100 HP are aligned with the openings formed between the teeth 251 of the mounting flange. 250 of the HP 200 turbine disk.
Afin de maintenir solidaire le disque de turbine HP 200 au tourillon HP 100, on introduit une vis 21 de boulon 200 successivement dans un alésage de fixation 120 du tourillon 100 puis dans l'alésage de fixation 220 du disque de turbine 200 avec lequel il est aligné. On visse ensuite un écrou 22 de boulon 20 à l'extrémité de ladite vis 21 pour sécuriser la fixation. On réitère cette étape de boulonnage pour chaque alésage de fixation 120 du tourillon 100, le disque de turbine 200 étant alors solidaire du tourillon HP 100.In order to keep the HP 200 turbine disk integral with the HP 100 spindle, a bolt screw 21 is introduced successively into a fastening bore 120 of the journal 100 and then into the fastening bore 220 of the turbine disc 200 with which it is mounted. aligned. A nut 22 of bolt 20 is then screwed to the end of said screw 21 to secure the attachment. This bolting step is repeated for each fixing bore 120 of the trunnion 100, the turbine disc 200 then being integral with the trunnion HP 100.
Après fixation, l'air de refroidissement peut circuler entre les boulons 20 de maintien du tourillon HP 100. La partie annulaire radiale 150 du tourillon 100
permet la fixation au disque de turbine 200 ainsi que l'évacuation du flux d'air de refroidissement du disque de turbine 200.After fixing, the cooling air can circulate between the bolts 20 for holding the trunnion HP 100. The radial annular portion 150 of the trunnion 100 allows the attachment to the turbine disk 200 and the evacuation of the cooling air flow of the turbine disk 200.
Après avoir décrit la structure des moyens de l'invention, son fonctionnement et sa mise en œuvre vont maintenant être abordés.After describing the structure of the means of the invention, its operation and its implementation will now be discussed.
En référence aux figures 2 et 3, lors du fonctionnement du turboréacteur, un mélange d'air et de carburant est brûlé dans la chambre de combustion du moteur pour créer la poussée nécessaire au déplacement de l'aéronef sur lequel est monté le turboréacteur. Après combustion, un flux de gaz à très haute température circule dans la turbine HP du turboréacteur. Le disque de turbine HP 200 est soumis à des températures très élevées.With reference to FIGS. 2 and 3, during operation of the turbojet engine, a mixture of air and fuel is burned in the combustion chamber of the engine to create the thrust required for the displacement of the aircraft on which the turbojet engine is mounted. After combustion, a gas flow at very high temperature circulates in the HP turbine of the turbojet engine. The HP 200 turbine disk is subjected to very high temperatures.
Afin de protéger le disque de turbine HP 200, un flux d'air est prélevé en amont du disque de turbine 200, au niveau du compresseur HP, et circule d'amont en aval dans le turboréacteur, intérieurement au disque de turbine HP 200 et extérieurement au fourreau d'étanchéité 400. Lors de la circulation de l'air de refroidissement dans l'alésage central 201 du disque de turbine HP 200, le flux d'air de refroidissement annulaire prélève des calories sur le disque de turbine 200 pour le refroidir et forme une enveloppe d'air de refroidissement autour du fourreau d'étanchéité 400, protégeant ainsi les pièces mécaniques montées à l'intérieur de celui-ci.In order to protect the HP turbine disk 200, an airflow is taken upstream of the turbine disk 200, at the level of the HP compressor, and flows upstream and downstream in the turbojet, internally to the HP 200 turbine disk and externally to the sealing sheath 400. During the circulation of the cooling air in the central bore 201 of the HP turbine disk 200, the annular cooling air stream takes heat from the turbine disk 200 for cooling and forming a cooling air envelope around the sealing sheath 400, thereby protecting the mechanical parts mounted therein.
Après avoir refroidi le disque de turbine HP 200, l'air de refroidissement est évacué à travers les passages de circulation d'air qui sont ménagés entre les boulons 20 reliant le tourillon HP 100 au disque de turbine HP 200 comme représenté sur les figure 2 et 3. En aval des ouvertures de circulation d'air, l'air de refroidissement refroidit la turbine BP du moteur à double corps. Autrement dit, l'air de refroidissement circule successivement entre les dents 251 de la bride
de fixation aval 250 du disque de turbine HP 200 et à travers les ouvertures de ventilation 110 ménagées dans le tourillon HP 100.After cooling the HP turbine disk 200, the cooling air is discharged through the air circulation passages which are formed between the bolts 20 connecting the HP 100 trunnion to the HP 200 turbine disk as shown in FIG. 2 and 3. Downstream of the airflow openings, the cooling air cools the LP turbine of the dual-body engine. In other words, the cooling air circulates successively between the teeth 251 of the flange downstream mounting 250 of the HP 200 turbine disk and through the ventilation openings 110 formed in the HP 100 trunnion.
Le disque d'étanchéité à labyrinthe 300The labyrinth sealing disc 300
Selon une autre caractéristique de l'invention, un disque d'étanchéité à labyrinthe 300 est monté avec le disque de turbine HP 200 et le tourillon HP 100, le disque d'étanchéité 300 étant monté en aval du tourillon HP 100.According to another characteristic of the invention, a labyrinth sealing disc 300 is mounted with the HP turbine disc 200 and the HP trunnion 100, the sealing disc 300 being mounted downstream of the HP trunnion 100.
En référence à la figure 6, le disque d'étanchéité à labyrinthe 300 se présente sous la forme d'une couronne annulaire radiale comprenant à son extrémité radiale extérieure, i.e. la plus éloignée de l'axe du moteur, des lames radiales d'étanchéité 304 formant joint d'étanchéité à labyrinthe, et comprenant à son extrémité intérieure, i.e. la plus proche de l'axe du moteur, une bande annulaire radiale de fixation 350.Referring to Figure 6, the labyrinth sealing disc 300 is in the form of a radial annular ring comprising at its outer radial end, ie the farthest from the axis of the motor, radial sealing blades 304 forming a labyrinth seal, and comprising at its inner end, ie the closest to the axis of the engine, a radial annular fixing band 350.
La bande annulaire radiale de fixation 350 du disque d'étanchéité 300 comprend des alésages de fixation 320 alternés avec des ouvertures de ventilation 310, les alésages 320 et les ouvertures 310 étant disposés circonférentiellement sur la bande annulaire radiale de fixation 350. Les alésages de fixation 320 et les ouvertures de ventilation 310 du disque d'étanchéité 300 sont ménagés de manière à correspondre avec leurs homologues ménagés sur le tourillon HP 100.The radial annular fixing band 350 of the sealing disc 300 comprises fixing bores 320 alternating with ventilation openings 310, the bores 320 and the openings 310 being arranged circumferentially on the radial annular fixing band 350. The fixing bores 320 and the ventilation openings 310 of the sealing disc 300 are arranged to correspond with their counterparts on the HP 100 trunnion.
Pour fixer le disque d'étanchéité 300, on met en contact surfacique la face tournée vers l'aval de la bride de fixation aval 250 du disque de turbine HP 200 avec la face tournée vers l'amont de la partie annulaire radiale 150 du tourillon HP 100. Puis, on met en contact surfacique la face tournée vers l'amont de la bande de fixation 350 du disque d'étanchéité 300 avec la face tournée vers l'aval de la partie annulaire radiale 150 du tourillon HP 100.
Ensuite, on aligne les alésages de fixation 120, 220, 320 du disque de turbine HP 200, du tourillon HP 100 et du disque d'étanchéité 300. Du fait de l'alignement des alésages de fixation 120, 220, 320, les ouvertures de ventilation 110, 310 du tourillon HP 100 et du disque d'étanchéité 300 sont alignées avec les créneaux 252 de la bride de fixation 250 du disque de turbine HP 200.In order to fix the sealing disc 300, the face facing downstream of the downstream fastening flange 250 of the HP 200 turbine disk is brought into surface contact with the face facing upstream of the radial annular portion 150 of the trunnion. HP 100. Then, the face facing upstream of the fastening strip 350 of the sealing disk 300 is brought into surface contact with the face facing downstream of the radial annular portion 150 of the HP pin 100. Next, the fixing bores 120, 220, 320 of the HP turbine disk 200, the HP trunnion 100 and the sealing disk 300 are aligned. Due to the alignment of the fixing bores 120, 220, 320, the openings 110, 310 of the HP trunnion 100 and the sealing disc 300 are aligned with the slots 252 of the fastening flange 250 of the HP turbine disc 200.
On boulonne ensuite ensemble le disque de turbine 200, le tourillon 100 et le disque d'étanchéité 300 via les alésages de fixation 120, 220, 320 qui sont alignés. Après fixation, des passages de circulation d'air sont ménagés entre les boulons de maintien 20.The turbine disc 200, the journal 100 and the sealing disc 300 are then bolted together via the fastening bores 120, 220, 320 which are aligned. After fixing, air circulation passages are formed between the holding bolts 20.
La section de passage des ouvertures de ventilation 310 du disque d'étanchéité 300 est adaptée de manière à pouvoir calibrer le débit de circulation de l'air de refroidissement dans l'alésage central 201 du disque de turbine 200. Dans cet exemple, le diamètre des ouvertures circulaires de ventilation 310 du disque d'étanchéité 300 est inférieur au diamètre des ouvertures circulaires de ventilation 110 du tourillon HP 100, entraînant une diminution du débit d'air de refroidissement dans l'alésage de central 201.
The passage section of the ventilation openings 310 of the sealing disk 300 is adapted so as to be able to calibrate the flow rate of the cooling air in the central bore 201 of the turbine disk 200. In this example, the diameter circular ventilation openings 310 of the sealing disc 300 are smaller than the diameter of the circular ventilation openings 110 of the HP 100 trunnion, resulting in a reduction of the cooling air flow in the central bore 201.
Claims
1. Ensemble d'un disque de turbine (200) d'un moteur à turbine à gaz et d'un tourillon (100) support de palier, le disque de turbine (200) comprenant une bride annulaire radiale de fixation (250) solidaire d'une partie annulaire radiale (150) du tourillon (100) par des boulons (2), les boulons (2) traversant successivement des alésages de fixation (120, 220) ménagés dans la bride annulaire radiale de fixation (250) du disque de turbine (200) et dans la partie annulaire radiale (150) du tourillon (100), ensemble caractérisé par le fait que la partie annulaire radiale (150) du tourillon1. A set of a turbine disk (200) of a gas turbine engine and a trunnion (100) bearing support, the turbine disk (200) comprising a fixed radial annular mounting flange (250). a radial annular portion (150) of the trunnion (100) by bolts (2), the bolts (2) successively passing through fixing holes (120, 220) formed in the radial annular flange (250) of the disk turbine (200) and in the radial annular portion (150) of the trunnion (100), characterized in that the radial annular portion (150) of the trunnion
(100) comprend des ouvertures (110) de circulation d'air, les ouvertures (110) étant ménagées entre les alésages de fixation (120) du tourillon (100).(100) comprises airflow openings (110), the openings (110) being provided between the fixing bores (120) of the journal (100).
2. Ensemble selon la revendication 1, dans lequel la bride annulaire radiale de fixation (250) du disque de turbine (200) se présente sous la forme d'une bande annulaire radiale crénelée (250) comprenant des dents (251) séparées par des créneaux (252), les alésages de fixation de la turbine (220) étant ménagés dans les dents (251) de ladite bande crénelée (250).2. The assembly of claim 1, wherein the radial annular flange fastening (250) of the turbine disk (200) is in the form of a crenellated radial annular band (250) comprising teeth (251) separated by crenellations (252), the turbine mounting bores (220) being provided in the teeth (251) of said crenellated band (250).
3. Ensemble selon la revendication 2, dans lequel les créneaux (252) de la bride annulaire radiale de fixation (250) sont agencés pour, correspondre avec les ouvertures (110) de circulation d'air ménagées sur la partie annulaire radiale (150) du tourillon (100).3. The assembly of claim 2, wherein the slots (252) of the radial annular clamping flange (250) are arranged to correspond with the openings (110) of air circulation formed on the radial annular portion (150). of the journal (100).
4. Ensemble selon l'une des revendications 1 à 3, dans lequel les ouvertures (110) de circulation d'air et les alésages de fixation (120) sont disposés circonférentiellement sur la partie annulaire radiale (150) du tourillon (100). 4. An assembly according to one of claims 1 to 3, wherein the openings (110) of air circulation and the fixing bores (120) are arranged circumferentially on the radial annular portion (150) of the pin (100).
5. Ensemble selon l'une des revendications 1 à 4, dans lequel le tourillon (100) comporte une partie tronconique (102), en aval de sa partie annulaire radiale (150), comprenant une portion radiale intérieure (107) de renfort mécanique.5. An assembly according to one of claims 1 to 4, wherein the trunnion (100) comprises a frustoconical portion (102), downstream of its radial annular portion (150), comprising an inner radial portion (107) of mechanical reinforcement. .
6. Ensemble selon l'une des revendications 1 à 5, dans lequel un disque d'étanchéité (300), monté en aval du tourillon (100), est boulonné avec le tourillon (100) et le disque de turbine (200), le disque d'étanchéité (300) comprenant des ouvertures de circulation (310) qui sont alignées avec les ouvertures de circulation d'air (110) du tourillon.6. An assembly according to one of claims 1 to 5, wherein a sealing disc (300), mounted downstream of the pin (100), is bolted with the pin (100) and the turbine disc (200), the sealing disc (300) comprising circulation openings (310) which are aligned with the air circulation openings (110) of the journal.
7. Ensemble selon la revendication 6, dans lequel la section de passage des ouvertures de circulation (310) du disque d'étanchéité (300) est adaptée pour calibrer le débit de circulation d'air.7. The assembly of claim 6, wherein the passage section of the circulation openings (310) of the sealing disc (300) is adapted to calibrate the air flow rate.
8. Circuit de refroidissement du disque de turbine (200) dans un moteur à turbine à gaz comprenant un passage d'évacuation, en aval du disque de turbine (200), passant par lesdites ouvertures (110, 252, 310) de l'ensemble selon l'une des revendications 1 à 7.A turbine disk cooling circuit (200) in a gas turbine engine comprising a discharge passage, downstream of the turbine disk (200), passing through said openings (110, 252, 310) of the turbine disk (200). assembly according to one of claims 1 to 7.
9. Circuit de refroidissement selon la revendication 8 comprenant un passage amont à travers un alésage central (201) du disque de turbine (200), en amont des ouvertures (110, 252, 310) dudit ensemble.The cooling circuit of claim 8 including an upstream passage through a central bore (201) of the turbine disk (200), upstream of the openings (110, 252, 310) of said assembly.
10. Circuit de refroidissement selon les revendications 8 et 9 dans un moteur à double corps comprenant une turbine à haute pression et une turbine à basse pression, la turbine dudit ensemble étant la turbine à haute pression (200), circuit comprenant un passage aval, ménagé en aval des ouvertures (110, 252, 310) dudit ensemble, pour refroidir en partie la turbine à basse pression. 10. Cooling circuit according to claims 8 and 9 in a double-body engine comprising a high-pressure turbine and a low-pressure turbine, the turbine of said assembly being the high-pressure turbine (200), circuit comprising a downstream passage, arranged downstream of the openings (110, 252, 310) of said assembly, for partially cooling the low pressure turbine.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0802945A FR2931873B1 (en) | 2008-05-29 | 2008-05-29 | A TURBINE DISK ASSEMBLY OF A GAS TURBINE ENGINE AND A BEARING BRIDGE SUPPORT CIRCUIT, COOLING CIRCUIT OF A TURBINE DISK OF SUCH AN ASSEMBLY. |
PCT/EP2009/056617 WO2009144300A1 (en) | 2008-05-29 | 2009-05-29 | Assembly including a turbine disc for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disc of such an assembly |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2340358A1 true EP2340358A1 (en) | 2011-07-06 |
Family
ID=40070588
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09753955A Pending EP2340358A1 (en) | 2008-05-29 | 2009-05-29 | Assembly including a turbine disc for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disc of such an assembly |
Country Status (9)
Country | Link |
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US (1) | US8899913B2 (en) |
EP (1) | EP2340358A1 (en) |
JP (1) | JP5319763B2 (en) |
CN (1) | CN102046922A (en) |
BR (1) | BRPI0912114B1 (en) |
CA (1) | CA2726016C (en) |
FR (1) | FR2931873B1 (en) |
RU (1) | RU2504661C2 (en) |
WO (1) | WO2009144300A1 (en) |
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FR3013766B1 (en) * | 2013-11-25 | 2017-11-10 | Snecma | TURBOMACHINE COMPRISING A SHAFT AND ASSOCIATED FOURREAU TUBE |
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US10502059B2 (en) | 2015-02-02 | 2019-12-10 | United Technologies Corporation | Alignment tie rod device and method of utilization |
CN104929779B (en) * | 2015-04-30 | 2016-06-22 | 中国科学院工程热物理研究所 | Wheel disc attachment structure and the gas-turbine unit with it |
KR101663306B1 (en) * | 2015-10-02 | 2016-10-06 | 두산중공업 주식회사 | Gas Turbine disk |
CN106677834B (en) * | 2015-11-05 | 2018-06-08 | 中国航发商用航空发动机有限责任公司 | Connect the bolt fastening structure and method of low-pressure turbine disk and rotor supports cone arm |
CN105401981A (en) * | 2015-12-29 | 2016-03-16 | 中国航空工业集团公司沈阳发动机设计研究所 | High-rotation-speed low-pressure turbine rotor structure |
FR3079299B1 (en) * | 2018-03-22 | 2020-06-05 | Safran Aircraft Engines | DEVICE FOR MEASURING THE CHARACTERISTICS OF AN AIR FLOW |
CN109098773B (en) * | 2018-08-24 | 2023-07-07 | 哈尔滨电气股份有限公司 | Novel variable-section bolt connection structure of turbine wheel disc and connection method thereof |
JP7032279B2 (en) * | 2018-10-04 | 2022-03-08 | 本田技研工業株式会社 | Gas turbine engine |
FR3099204B1 (en) | 2019-07-24 | 2022-12-23 | Safran Aircraft Engines | TURBOMACHINE RECTIFIER STAGE WITH COOLING AIR LEAK PASSAGE WITH VARIABLE SECTION DEPENDING ON BLADE ORIENTATION |
WO2021167001A1 (en) * | 2020-02-20 | 2021-08-26 | 川崎重工業株式会社 | Flange cooling structure for gas turbine engine |
FR3108362B1 (en) | 2020-03-19 | 2022-07-29 | Safran Aircraft Engines | Stage of blades with variable orientation for an axial turbomachine comprising a member for regulating the air flow depending on the orientation of the blades |
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CA2726016C (en) | 2017-06-20 |
JP2011522152A (en) | 2011-07-28 |
BRPI0912114A2 (en) | 2015-11-03 |
FR2931873A1 (en) | 2009-12-04 |
RU2504661C2 (en) | 2014-01-20 |
FR2931873B1 (en) | 2010-08-20 |
WO2009144300A1 (en) | 2009-12-03 |
RU2010154117A (en) | 2012-07-10 |
US8899913B2 (en) | 2014-12-02 |
BRPI0912114B1 (en) | 2019-12-03 |
CN102046922A (en) | 2011-05-04 |
CA2726016A1 (en) | 2009-12-03 |
JP5319763B2 (en) | 2013-10-16 |
US20110129336A1 (en) | 2011-06-02 |
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