EP0651139B1 - Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator - Google Patents
Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator Download PDFInfo
- Publication number
- EP0651139B1 EP0651139B1 EP94402400A EP94402400A EP0651139B1 EP 0651139 B1 EP0651139 B1 EP 0651139B1 EP 94402400 A EP94402400 A EP 94402400A EP 94402400 A EP94402400 A EP 94402400A EP 0651139 B1 EP0651139 B1 EP 0651139B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- ring
- ring sector
- shroud
- screw
- turbomachine according
- 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.)
- Expired - Lifetime
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Classifications
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
- F01D25/265—Vertically split casings; Clamping arrangements therefor
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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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
Definitions
- the subject of the present invention is a turbomachine comprising games control means between stator and rotor and, more precisely, between the stator and the top of the rotor moving blades.
- the major warm-ups to which a aircraft engine turbomachine is subject cause generally thermal expansions that it is higher interest to be able to control to avoid, in in particular, gas leaks between the rotor and the structure of the stator which surrounds it as well as the losses of efficiency, following these gas leaks.
- Aircraft engines (especially those used for propulsion of jet airplanes) must be able to operate under conditions which can vary quickly. These variations of operating conditions can be a runaway of the cold rotor, a stroke of the throttle, runaway hot rotor, or any other operating conditions well known to man of the job.
- stator in such a way that it is possible to circulate there gas, taken for example from another location in the machine, at a temperature and flow that produce at will a heating or cooling capable of adjust the expansion of the ferrule and therefore its play with the moving blades.
- Such a variable temperature air shipment on the structure of the rectifier support allows, by a variation in the speed of expansion and contraction of the structure, to accommodate different engine operating conditions.
- this is generally made of a single piece; it is therefore a 360 ° housing of circumference.
- FR-2 683 851, FR-2 516 980 and FR-2 482 661 describe turbomachinery whose stators have double skin housings extending around the rotors on a full circumference, the air heating or cooling between the two crankcase skins.
- shell elements or shell sectors
- the shell elements may undergo displacements which harm the circularity of the structure.
- the document GB-2 115 487 describes stator rings fitted by dovetail in supports.
- the document FR-2 482 662 describes a stator ring segmented and pierced with orifices.
- turbomachine comprising a stator whose 360 ° circumference housing and components ferrule are linked via a fixed point and sliding supports ensuring flexibility of the shell circumferential.
- This turbomachine is characterized by the fact that it has a support ring housed between the casing and the ferrule, integral with said ferrule and comprising a plurality of circular ring sectors each attached to the casing by a fixed point means (10) and at least two sliding support means (11) located on either side else of the fixed point means to ensure the ferrule circumferential flexibility relative to the casing.
- the turbomachine comprises a ring of support housed between the casing and the ferrule and comprising a plurality of fixed circular ring sectors each on the housing by means of a fixed point and sliding supports having a shaped section of a U whose opening is directed towards the shell, each shell element comprising means hooking able to be introduced into the opening at least one ring sector for securing said ring area and ferrule element.
- each ring sector has an upstream wing and a wing downstream, each of said upstream and downstream wings comprising first recesses open radially towards the ferrule to provide circumferential flexibility audit ring sector.
- the upstream wing has, in in addition, second recesses.
- the turbomachine comprises clamping means in support of on either side of each ring sector to ensure securing said ring sector with the means of attachment of the ferrule element.
- clamping means comprise a screw and a conical nut inserted inside the sector ring and able to deviate during the introduction of the screw, the base of said nut then being supported on the internal faces of the ring sector.
- each element of ferrule constitute, with the ends of the wings upstream and downstream of the ring sector in which it is introduced, a dovetail assembly.
- each means point system has a screw / nut system ensuring a seamless connection of a ring sector with the casing, the nut being introduced inside the ring by the second recess and arranged in support on an internal face of the core of the ring sector.
- the screw can be, for example, introduced in the ring sector with a neighboring inclination 45 ° to the radial direction.
- She can, according to another example, to be introduced radially in the ring sector, the nut then having a shape conical, the base of which is directed towards the shell.
- the screw is then introduced into the sector ring with a longitudinal inclination of angle a, and the supporting parts have an inclined surface at an angle a to the radial direction.
- the first recesses of the downstream wing are closed by sealing plates.
- Each ring sector comprises, around the first recesses, grooves in which are positioned and fitted the sealing plates.
- Each downstream wing of a ring sector can have an extension tab at one end and, at another end, machining ensuring a interlocking with covering of said ring sector in neighboring ring areas.
- FIG 1 there is shown in section axial, a high pressure compressor having a housing exterior 1 of 360 ° circumference and means of piloting of games conforming to the first mode of realization of the invention.
- This housing 1 has two envelopes (or two skins) concentric, slightly conical, separated by a volume (shown hatched in Figure 1) in which the heating air circulates or cooling.
- This two-skin housing is type of that described in the document FR-2 683 851 cited previously; it will therefore not be described further in detail.
- This casing 1 surrounds a plurality ferrule elements 2 which are substantially conical. These shell elements 2 are arranged end to end and assembled by interlocking joints 3 to form a single continuous ferrule and substantially parallel to the housing 1.
- Each ferrule element 2 carries a stage stationary stator vanes 4, also called stage rectifier.
- a stage of movable rotor blades 5 extends between each pair of stages of fixed blades 4.
- FIG 1 there is also shown the rings 6 according to the first embodiment of the invention, these rings allowing displacements sensitive of the shell elements 2 according to the casing dilations and contractions 1.
- These rings 6 each have a plurality of ring sectors arranged end to end and fitted into each other others to make continuous rings.
- each ring 6 has a U-shaped section, the open side of the U being directed towards the shell 2.
- Each ferrule element 2 has on its external face, i.e. on the face not bearing fixed vanes 4, attachment means 9 of the ring 6.
- these attachment means 9 consist of a tenon 9a in dovetail adapted to be inserted into the opening of the ring 6.
- the ends of the wings upstream 7 and downstream 8 of the ring 6 form a mortise 9b suitable for receiving the post 9a.
- Mortise 9b and tenon 9a thus form a dovetail assembly.
- clamping means not shown in this FIG. 1, pinch on both sides of the wings upstream 7 and downstream 8 of the ring 6 to ensure a securing of said ring 6 with the ferrule 2.
- Each ring sector 6 is fixed to the casing by means of a fixed point 10 which will be described more in detail through the following figures.
- Each ring sector is also fixed on the casing at means of sliding supports not shown on this Figure 1 but described in more detail below the description.
- FIG 2 shows the angular distribution ferrule elements 2 and ring sectors 6 to inside the casing 1.
- the ferrule 2 therefore comprises a plurality of shell elements, three of which are shown in Figure 2 and referenced 2a, 2b and 2c.
- the ring 6 has a plurality of sectors of which four are shown in this figure 2 and referenced 6a, 6b, 6c and 6d.
- each ring sector has a size equivalent to approximately two shell elements.
- the ring sector 6a has two sliding supports 11a and 11b on either side of the point fixed 10a and two sliding supports 11c and 11d each of its ends.
- All of these sliding supports ensure, for each ring sector, one displacement immediate circumferential (represented by arrows in FIG. 2) of the ring sector, and therefore of ferrule elements connected to this ring sector, by relative to the displacement of the housing.
- each ring sector includes, indeed, a plurality of recesses, namely the recesses 12 only on the upstream wing and the recesses 13 on the upstream wing and on the downstream wing, these recesses providing circumferential flexibility at the ring area.
- the ring sectors 6a, 6b, ... are assembled with neighboring ring sectors at level from the center of a recess 12.
- Figure 3 shows a view in perspective of the ring sector 6a of FIG. 2.
- This figure therefore shows the ring sector 6a cut at a recess 13, the casing 1 on which is fixed the ring sector 6a, as well as the ferrule 2 with its tenon 9a in dovetail around which fits the dovetail ends 9b of the upstream wings 7 and downstream 8.
- the ring sector 6a is connected to the casing 1 via the point fixed 10a and several sliding supports including three are represented in this figure and referenced 11a, 11b and 11c.
- This figure shows the recesses 12 of the upstream wing as well as the recesses 13 with their radial slot, these recesses 13 being also present on the downstream wing 8, but not visible on this perspective view of the ring sector 6a.
- part A of the Figure 4 shows the outer face of the upstream wing 7 of the ring sector 6a.
- This part A therefore shows the recesses 12 of the upstream wing 7 as well as the recesses 13 of this same upstream wing 7.
- these recesses 13 include a radial opening 13a, or radial slot, starting from the internal part of the ring sector (i.e. the part of smaller diameter) and ending in the recess 13.
- These radial slots give the ring 6 a circumferential flexibility.
- Part B of Figure 4 shows the face internal of the downstream wing 8 of the ring sector 6a.
- This downstream wing 8 has the recesses 13 with their radial slots 13a as well as screws 15 which pass through the ring sector right through and are fixed in the nuts 14 of the upstream wing 7.
- Each associated screw 15 to a nut 14 constitutes the clamping means which pinch the ring sector around the dovetail tenon of the ferrule.
- the sliding support is also represented on this part B of figure 4.
- the screw 18a of the sliding support is inserted into a sole 18b surmounted by a projection pierced with a hole on the wall of which a thread has been made.
- This sole 18b is supported on support pieces 19a and 19b arranged on either side of said hole in the sole 18b. These support pieces 19a and 19b are crossed by the screws 15, which secures said support pieces on the downstream wing 8.
- An opening 21 is, in addition, produced in the core 20 of the ring sector; the sole 18b has, with the projection which surmounts it, a form of "pickaxe" able to pass partly into the opening 21 of the core 20 of the ring sector 6a to be in contact direct with the internal wall of the casing 1.
- the parts sides of the sole 18b can therefore slide on these support pieces 19a and 19b thus creating a clearance circumference of the ring segment 6a with respect to the housing 1.
- this sole 18b is a double span nut.
- the supporting parts 19a and 19b form a angle of about 45 ° to the downstream wing 8 of so as to ensure a better sliding of the sole 18b.
- This part B of FIG. 4 shows, in in addition, a sealing plate 25 which can be introduced into grooves (or slots) machined around recesses 13 in the downstream wing 8.
- These grooves, referenced 26, are shown in dotted lines on the figure because they are made on the external face of the downstream wing 8.
- the sealing plate 25 includes returns (dotted) suitable for entering the grooves 26 for positioning and the fitting of said sealing plates 25 in the downstream wing 8. The positioning of such plates sealing in front of the recesses 13 of the downstream wing 8 of ring sector 6a is intended to prevent possible reintroductions of gases from downstream to upstream of the ring.
- the seal of the downstream wing of each ring sector is carried out by means of an annular seal 38 bearing on the part downstream of the dovetail assembly.
- FIG 5 there is shown the means clamping in axial section.
- these clamping means comprise a screw 15 introduced into the downstream wing 8 of the ring 6 and crossing said ring right through. This screw 15 is fixed in a nut 14 bearing on the external face upstream wing 7.
- These clamping means allow thus compressing the mortise 9b produced by the wings 7 and 8 of the ring 6 against the tail 9a at the tail dovetail of the ferrule 2.
- This fixed point 10 consists of a screw / nut system introduced into housing 1 and into ring 6 to secure them. More specifically, this screw / nut system includes a screw 16a introduced in the casing 1 and in the core 20 of the ring 6 by a breakthrough. A nut 16b introduced into the ring 6 by one recesses 12 of the upstream wing 7 ensures the fixing of the screw 16a. The screw 16a thus fixed in the nut 16b secures the ring 6 by its core 20 against the inner wall of the housing 1.
- the nut 16b is of the lug nut type whose legs are fixed to the ring 6 by the rivets referenced 17a and 17b in Figure 4.
- the screw 16a is introduced in housing 1 and ring 6 with an inclination longitudinal, the nut 16b having a shape suitable for receive the screw 16a thus inclined while having a solid support against the internal face of the core 20 of the ring 6.
- the means for hooking the ferrule 2 with the ring 6 consist in a mortise 30b made in each element of ferrule 2 and a lug 30a produced by the ends internal of downstream 8 and upstream wings 7 of sectors ring.
- the joining without play of each ring sector with the casing 1 is achieved by means a domed screw 32 introduced radially into the housing 1 and in the ring.
- This screw is introduced in a nut 34 of conical shape whose base, directed towards the shell, is in contact with the internal faces upstream and downstream wings.
- a lunule 36 is machined on the external face of each ferrule element.
- screw 32 is tight, its curved end is supported in the lunula 36, the nut 34 rises and, by its taper, spreads the ring area thus realizing the connection without play between the shell element 2 and the ring sector 6.
- a conical nut 34 is positioned astride two sectors allowing sectors to slide by compared to rings according to variations thermal.
- This sliding support 11 consists of a screw / nut system in which the nut can move on supporting parts. More precise, this screw / nut system includes an 18a screw inserted in the casing 1 and in the projection of the sole 18b.
- This sole consists of a base and of the projection located in the middle of the base. An opening 21 is produced in the core 20 of the ring 6, large enough to allow passage of the protrusion of the sole 18b which can thus be in contact with the internal wall of the casing 1.
- An 18c nut secures the screw 18a in the sole 18b.
- the base of the sole 18b is resting on two support pieces, of which only the piece support 19a is visible in this figure 8.
- the projection of the sole 18b passing through the opening 21 of the core 20 and the base of said sole 18b being able to slide on the supporting parts, a circumferential clearance of the ring 6 relative to the casing 1 is then possible.
- Such sliding supports 11 thus allow the displacement of the ring 6 and therefore of the shell 2 in function of thermal variations.
- the support piece 19a, as well as all the supporting parts in the ring 6, are maintained integral with the ring by the clamping means 14, 15 which pass through said support pieces in their outer ends.
- FIG. 9 represents a view in perspective of the support pieces and the sole of a sliding support. We therefore see, in this figure 9, the supporting parts 19a and 19b having a wall, inclined at 45 ° with respect to the radial direction, on which slides the base 18b 'of the sole 18b.
- Figure 10 shows a view in perspective of the joint between two ring sectors 6a and 6b. This joint is made in the middle of a opening 21 partly machined in the core 20 of the sector ring 6a and partly in the core 20 of the sector ring 6b.
- downstream wing 8 of the ring sector 6b has an extension tab 22b machined in said downstream wing 8; the downstream wing 8 of the ring sector 6a has a symmetrical extension tab 22a with tab 22b; legs 22a and 22b being complementary so as to fit together one inside the other.
- Such a joining of sectors ring ensures, by the covering made on the downstream wings, sealing of the ring.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- une virole constituée d'une pluralité d'éléments de virole en forme de secteurs circulaires portant, chacun sur une face intérieure, des aubes fixes ; et
- un carter circulaire entourant la virole.
- une vis introduite dans le secteur d'anneau par une ouverture réalisée dans l'âme dudit secteur d'anneau ;
- une semelle surmontée d'une saillie qui est percée d'un trou comportant sur la paroi un pas de vis pour recevoir ladite vis et qui traverse l'ouverture de l'âme pour être en contact avec le carter ;
- deux pièces d'appui disposées de part et d'autre du trou de la semelle et fixées sur le secteur d'anneau de façon à permettre un glissement de la semelle sur les pièces d'appui.
- la figure 1 représente un compresseur haute pression équipé des moyens de pilotage des jeux entre rotor et stator conformes au premier mode de réalisation de l'invention ;
- la figure 2 représente une coupe diamétrale de la turbomachine selon le premier mode de réalisation, montrant la répartition angulaire des éléments de virole et des secteurs d'anneau à l'intérieur du carter ;
- la figure 3 représente une vue en perspective d'un secteur d'anneau de la figure 2 ;
- la figure 4 représente une vue partielle de l'aile aval et de l'aile amont d'un secteur d'anneau de la figure 2 ;
- la figure 5 représente, selon une coupe axiale, les moyens de serrage assurant la solidarisation des secteurs d'anneau et des éléments de virole conformément au premier mode de réalisation ;
- la figure 6 représente, selon une coupe axiale, un point fixe conforme au premier mode de réalisation ;
- la figure 7 représente, en coupe axiale, une variante des moyens de serrage et des moyens d'étanchéité du premier mode de réalisation ;
- la figure 8 représente, en coupe axiale, un appui glissant liant le secteur d'anneau et le carter conformément au premier mode de réalisation ;
- la figure 9 représente, selon une vue en perspective, les pièces d'appui et la semelle formant l'appui glissant de la figure 8 ;
- la figure 10 représente une vue en perspective de la jointure entre deux secteurs d'anneau de la figure 2.
- deux appuis glissants répartis de part et d'autre du point fixe ; et
- deux appuis glissants situés chacun à une extrémité d'un secteur d'anneau.
Claims (15)
- Turbomachine comportant :une virole (2) constituée d'une pluralité d'éléments de virole (2a, 2b,...) en forme de secteurs circulaires portant chacun sur une face intérieure des aubes fixes (4) ; etun carter (1) circulaire entourant la virole,
- Turbomachine selon la revendication 1, caractérisée en ce que les secteurs d'anneau ont chacun une section en forme de U dont l'ouverture est dirigée vers la virole et en ce que chaque élément de virole comporte des moyens d'accrochage (9a) aptes à s'emboíter dans au moins un secteur d'anneau pour solidariser ledit secteur d'anneau et l'élément de virole.
- Turbomachine selon la revendication 2, caractérisée en ce que, chaque secteur d'anneau comportant une aile amont (8) et une aile aval (7), chacune desdites ailes amont et aval comprend des premiers évidements (13) ouverts radialement vers la virole pour assurer une souplesse circonférentielle audit secteur d'anneau.
- Turbomachine selon l'une quelconque des revendications 2 et 3, caractérisée en ce que chaque secteur d'anneau comportant une aile amont (8) et une aile aval (7), ladite aile amont comprend des seconds évidements (12).
- Turbomachine selon l'une quelconque des revendications 2 à 4, caractérisée en ce qu'elle comporte des moyens de serrage (14, 15) en appui de part et d'autre de chaque secteur d'anneau pour assurer une solidarisation dudit secteur d'anneau avec le moyen d'accrochage de l'élément de virole.
- Turbomachine selon la revendication 5, caractérisée en ce que les moyens de serrage comportent une vis (32) et un écrou (34) conique introduit à l'intérieur du secteur d'anneau et apte à s'écarter lors de l'introduction de la vis, la base dudit écrou étant alors en appui sur les faces internes du secteur d'anneau.
- Turbomachine selon l'une quelconque des revendications 3 à 6, caractérisée en ce que les moyens d'accrochage de chaque élément de virole constituent, avec les extrémités des ailes amont et aval du secteur d'anneau dans lequel il est introduit, un assemblage en queue d'aronde.
- Turbomachine selon la revendication 4, caractérisée en ce que chaque moyen de point fixe comporte un système de vis/écrou (16a, 16b) assurant une solidarisation sans jeu d'un secteur d'anneau avec le carter, l'écrou étant introduit à l'intérieur de l'anneau par le second évidement et disposé en appui sur une face interne de l'âme (20) du secteur d'anneau.
- Turbomachine selon la revendication 8, caractérisée en ce que la vis est introduite dans le secteur d'anneau avec une inclinaison voisine de 45° par rapport à la direction radiale.
- Turbomachine selon la revendication 8, caractérisée en ce que la vis est introduite radialement dans le secteur d'anneau et l'écrou a une forme conique dont la base est dirigée vers la virole.
- Turbomachine selon l'une quelconque des revendications 2 à 10, caractérisée en ce que chaque moyen d'appui glissant comporte :une vis (18a) surmontée d'une saillie (18b") qui est introduite dans le secteur d'anneau par une ouverture (21) réalisée dans l'âme dudit secteur d'anneau ;une semelle (18b) surmontée d'une saillie (18b") qui est percée d'un trou comportant sur la paroi un pas de vis pour recevoir ladite vis et qui traverse au moins en partie l'ouverture de l'âme pour être en contact avec le carter ;deux pièces d'appui (19a, 19b) disposées de part et d'autre du trou de la semelle et fixées sur le secteur d'anneau de façon à permettre un glissement de la semelle sur les pièces d'appui.
- Turbomachine selon la revendication 11, caractérisée en ce que la vis étant introduite dans le secteur d'anneau avec une inclinaison longitudinale d'angle α, les pièces d'appui comportent une surface inclinée d'un angle α par rapport à la direction radiale.
- Turbomachine selon l'une quelconque des revendications 3 à 12, caractérisée en ce que les premiers évidements de l'aile aval sont fermés par des plaques d'étanchéité (25).
- Turbomachine selon la revendication 13, caractérisée en ce que l'aile aval de chaque secteur d'anneau comporte, autour des premiers évidements, des rainures (26) dans lesquelles sont positionnées et emboítées les plaques d'étanchéité.
- Turbomachine selon l'une quelconque des revendications 3 à 14, caractérisée en ce que chaque aile aval d'un secteur d'anneau comporte, à une extrémité, une patte de prolongement (22a) et, à une autre extrémité, une patte de prolongement complémentaire (22b) assurant un emboítement avec recouvrement dudit secteur d'anneau dans les secteurs d'anneaux voisins.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9312798 | 1993-10-27 | ||
FR9312798A FR2711730B1 (fr) | 1993-10-27 | 1993-10-27 | Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator. |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0651139A1 EP0651139A1 (fr) | 1995-05-03 |
EP0651139B1 true EP0651139B1 (fr) | 1999-01-07 |
Family
ID=9452253
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP94402400A Expired - Lifetime EP0651139B1 (fr) | 1993-10-27 | 1994-10-26 | Turbomachine équipée de moyens de pilotage des jeux entre rotor et stator |
Country Status (4)
Country | Link |
---|---|
US (1) | US5616003A (fr) |
EP (1) | EP0651139B1 (fr) |
DE (1) | DE69415765T2 (fr) |
FR (1) | FR2711730B1 (fr) |
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FR2817285B1 (fr) | 2000-11-30 | 2003-06-13 | Snecma Moteurs | Virole interne de stator |
FR2829176B1 (fr) * | 2001-08-30 | 2005-06-24 | Snecma Moteurs | Carter de stator de turbomachine |
FR2875535B1 (fr) * | 2004-09-21 | 2009-10-30 | Snecma Moteurs Sa | Module de turbine pour moteur a turbine a gaz |
FR2875534B1 (fr) | 2004-09-21 | 2006-12-22 | Snecma Moteurs Sa | Module de turbine pour moteur a turbine a gaz avec rotor comportant un corps monobloc |
US9039358B2 (en) | 2007-01-03 | 2015-05-26 | United Technologies Corporation | Replaceable blade outer air seal design |
ES2705532T3 (es) | 2012-10-30 | 2019-03-25 | MTU Aero Engines AG | Anillo de turbina y turbomáquina |
EP2789804A1 (fr) * | 2013-04-11 | 2014-10-15 | Alstom Technology Ltd | Enveloppe de protection thermique de turbine à gaz présentant une durabilité améliorée |
US20180149030A1 (en) * | 2016-11-30 | 2018-05-31 | Rolls-Royce Corporation | Turbine shroud with hanger attachment |
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GB2115487B (en) * | 1982-02-19 | 1986-02-05 | Gen Electric | Double wall compressor casing |
US4728257A (en) * | 1986-06-18 | 1988-03-01 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Thermal stress minimized, two component, turbine shroud seal |
FR2683851A1 (fr) * | 1991-11-20 | 1993-05-21 | Snecma | Turbomachine equipee de moyens facilitant le reglage des jeux du stator entree stator et rotor. |
FR2695164B1 (fr) * | 1992-08-26 | 1994-11-04 | Snecma | Turbomachine munie d'un dispositif empêchant une circulation longitudinale de gaz autour des étages d'aubes de redressement. |
US5320487A (en) * | 1993-01-19 | 1994-06-14 | General Electric Company | Spring clip made of a directionally solidified material for use in a gas turbine engine |
-
1993
- 1993-10-27 FR FR9312798A patent/FR2711730B1/fr not_active Expired - Fee Related
-
1994
- 1994-10-26 US US08/330,072 patent/US5616003A/en not_active Expired - Lifetime
- 1994-10-26 DE DE69415765T patent/DE69415765T2/de not_active Expired - Lifetime
- 1994-10-26 EP EP94402400A patent/EP0651139B1/fr not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
FR2711730B1 (fr) | 1995-12-01 |
DE69415765D1 (de) | 1999-02-18 |
EP0651139A1 (fr) | 1995-05-03 |
DE69415765T2 (de) | 1999-07-29 |
FR2711730A1 (fr) | 1995-05-05 |
US5616003A (en) | 1997-04-01 |
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