EP2242909A1 - Turbomachine rotor comprising a pretensioning device for pretensioning a guide vane - Google Patents
Turbomachine rotor comprising a pretensioning device for pretensioning a guide vaneInfo
- Publication number
- EP2242909A1 EP2242909A1 EP09709892A EP09709892A EP2242909A1 EP 2242909 A1 EP2242909 A1 EP 2242909A1 EP 09709892 A EP09709892 A EP 09709892A EP 09709892 A EP09709892 A EP 09709892A EP 2242909 A1 EP2242909 A1 EP 2242909A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- blade root
- blade
- groove
- threaded hole
- 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.)
- Granted
Links
- 230000001154 acute effect Effects 0.000 claims description 10
- 238000000034 method Methods 0.000 claims description 5
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 12
- 230000036316 preload Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000001052 transient effect Effects 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000013013 elastic material Substances 0.000 description 1
- 239000002803 fossil fuel Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000014759 maintenance of location Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000006228 supernatant Substances 0.000 description 1
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/326—Locking of axial insertion type blades by other means
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49826—Assembling or joining
Definitions
- Turbomachine rotor having biasing means for biasing a blade
- the invention relates to a turbomachine rotor having biasing means for biasing a rotor blade, the blade having the biasing means, a backing plate as the biasing means, and a method of assembling the turbomachine rotor.
- a gas turbine is a thermal turbomachine in which conventionally fossil fuels, such as natural gas, are burned.
- the gas turbine can be used for example in a gas and steam power plant, which is provided to cover peak loads in a power grid.
- the gas turbine is driven in transient operation, whereby the individual components and components of the gas turbine are subjected to transient loads. Due to the high power density of the gas turbine high demands are to be met in terms of the strength of highly loaded components in order to ensure a long service life of these components and long maintenance cycles and a low spare parts requirement.
- the gas turbine has a compressor with a compressor rotor and a turbine with a turbine rotor, wherein the compressor rotor and the turbine rotor are coupled to one another in a torsionally rigid manner via a shaft.
- the compressor rotor and / or the turbine rotor are designed in axial construction, that is, on the shaft a plurality of wheel disks are threaded one behind the other.
- a blade row is attached in each case.
- Each blade row has a plurality of blades, each having an aerodynamically effective airfoil and a blade root. The blade root is inserted into a groove located on the outer circumference of the wheel disc, see above the blade is held in a form-fitting manner on the blade root, in particular in the radial direction of the gas turbine rotor.
- the blade root and the groove have corresponding dovetail profiles or fir tree profiles. These profiles are arranged to run in the axial direction of the gas turbine rotor, so that it is inserted with its fairlead in the axial direction of the gas turbine rotor in the groove for mounting the blade.
- a game is provided between the blade root and the profile of the groove so that the blade root is wear-free inserted into the groove.
- the blades can move during operation of the gas turbine, resulting in a characteristic clatter of the rotor blade. This is especially true for a large and heavy blade, as provided in particular in the first blade rows of the compressor of the gas turbine with a high performance.
- the blade is preloaded in the groove to prevent rattling.
- the blade is preloaded in the groove to prevent rattling.
- the bias voltage assembly can be difficult.
- the bias in the wheel disc and the blade root causes a mechanical stress, which is conventionally compensated by a stable and solid design of the wheel disc and the blade root.
- an axial locking plate may be provided, with which the blade is secured against axial displacement and additionally biased.
- the axial securing plate may be too weak to form.
- Such axial securing plate is known from US 2,786,648 and US 4,102,602.
- the slotted ends of the sheet protrude beyond the ends of the groove.
- the teeth formed by the slots are each mutually outwardly and inwardly bent to avoid axial displacement of the blade along the groove.
- the sheet is curved in the middle, to keep the blade biased in the groove.
- the object of the invention is to provide a turbomachine rotor, a rotor, a support plate and a method for assembling the turbomachine engine, wherein the turbomachinery rotor is operable without rattling of the rotor blades with high strength and efficiency.
- the turbomachine rotor has evenly distributed grooves along the circumference, in each of which a blade is inserted with a blade root, so that the blade is positively held with the groove in the radial direction, and a biasing device, both on a groove bottom of the groove and on the Paddle is supported and exerts on the blade root a biasing force in the radial direction, wherein the biasing means is arranged such that the biasing force is adjustable in the assembled state of the turbomachine rotor.
- the biasing force is provided as low and in the assembled state of the turbine engine rotor, the biasing force is set to be predetermined high.
- the biasing force low, so that wear on the blade root and in the groove is prevented due to the assembly of the blade.
- the force required when inserting the blade root into the groove is advantageously low, so that only slight stress peaks occur in the blade root and in the wheel disk during assembly of the blade.
- these stress peaks in the strength design of the blade root and the turbomachine rotor need as good as not to be taken into account and the mounting of the blade in the turbomachine rotor is simple.
- the biasing device also has at least one adjusting screw, with which by applying a predetermined tightening torque, the biasing force in the assembled state of the turbomachine rotor is adjustable.
- the adjusting screw By means of the adjusting screw is the setting of the predetermined biasing force on the specification of a torque of the screw allows. As a result, the preload force can be applied to the rotor via the tightening torque.
- the set screw is provided with a fine thread, so that an accurate power transmission of the screw is made possible by the tightening torque on the biasing force.
- At least one threaded hole is provided in the blade root, which opens at the bottom of the blade root facing the groove bottom of the groove, wherein at least one screw in the at least one threaded hole so is screwed that it protrudes on the blade root with its screw end and is supported on the groove base.
- the adjusting screw penetrates the blade root through the threaded hole and is fixed therein, so that the biasing force is applied by the support of the screw end against the groove bottom on the blade root in the radial direction.
- the distributed along the circumference grooves are arranged in a wheel disc of the turbomachine rotor.
- a modular turbomachinery rotor can be specified.
- the biasing means on a support plate on the groove bottom at least in the region of the one
- Adjusting screw is arranged so that the adjusting screw and the support plate are in touching contact.
- the support plate is located directly on the groove bottom in the groove, so that no additional groove needs to be provided in the groove base for the support plate.
- the groove bottom in the area of the adjusting screw is covered by the supporting plate, so that the groove base is only in indirect contact via the supporting plate with the screw end of the adjusting screw. Thus, it is prevented that the end of the screw screw, especially when turning the screw damaged the groove bottom.
- the at least one threaded hole with its end remote from the blade root underside to open outward on one of the front sides of the blade root, so that the threaded hole is inclined at an acute angle away from the longitudinal axis of the turbomachine rotor.
- the threaded hole is accessible at the end face of the blade root, so that from there the adjusting screw can be adjusted to the wheel disk after assembly of the blade. that can. Further, since the threaded hole extends from the end face of the blade root toward the blade root, the threaded hole penetrates the blade root in a mechanically little loaded area. As a result, the provision of the threaded hole in the blade root has little effect on its strength.
- the biasing force applied by the adjusting screw has an axial and a radial component. This is advantageous because it applies both the radial preload force and an axial force for locking the blade in the wheel disc. As a result, both a radial and an axial attachment of the blade is ensured.
- about the degree of inclination of the screw can the
- Division of the force transmitted by the screw force can be divided into the axial and radial attachment.
- the support plate has at least one offset with a flat edge, which is shaped such that the end of the screw of the screw abuts the end face of the flat edge.
- the end face of the screw end of the set screw is also formed flat, so that when surface concerns of the screw end on the flank, the surface pressure is low.
- the blade root has a first threaded hole with a first adjusting screw and a second threaded hole with a second adjusting screw, wherein the first threaded hole at one end face and the second
- Threaded hole on the other end side of the blade root opens outward, so that the first threaded hole at a first acute angle and the second threaded hole to a second acute angle is inclined away from the longitudinal axis of the turbomachine rotor.
- the two setscrews are inclined relative to one another so that the axial force components applied to the support plate counteract each other.
- a stable attachment of the blade root in the groove can advantageously be achieved, with little or no resulting axial force acting on the blade root.
- the support plate has the first offset with the first flank on which abuts the screw end of the first screw, and the second crank with the second flank against which abuts the screw end of the second screw.
- the blade is locked at its blade root via the adjusting screws on the flanks of the cranks of the support plate in the axial direction positively.
- first angle and the second angle have the same amount.
- the biasing means in the plane perpendicular to the axial direction of the turbomachine rotor is formed symmetrically, so that the distribution of the biasing forces in the biasing means is symmetrical.
- the pretensioning device, the blade root and the wheel disc are balanced.
- the support plate between the two cranks has a back portion which faces the blade root with its convex side.
- the support plate is made of an elastic material.
- the preload forces exerted by the set screws on the flanks of the cranks are pressed in the direction of the groove bottom.
- the back portion is curved, so that the back portion presses with its convex side on the blade root underside.
- the biasing forces that exert the set screws on the support plate transferred to the blade root.
- the bias of the blade is increased.
- the back portion is pre-curved prior to its mounting, so that the back portion in the assembled state of the turbomachine engine presses on the blade root lower side.
- the support plate has a spring action in the direction of the blade root lower side, whereby a Vorspannreserve in the case of setting, that is, when in operation increases the distance between the Schaufelfußunterseite and the groove bottom is created. Furthermore, the pre-curvature of the back section in the assembled state allows a good force closure over the surface contact formed with the adjusting screws. About the stiffness and the thickness of the support plate, the Vorspannreserve can be predefined. By adjusting the set screws, the preload reserve in the assembled state can still be varied.
- the support plate has at the first offset a first leg portion extending away from the back portion and at the second offset a second leg portion extending away from the back portion.
- the first leg section has a first projection and the second leg section has a second projection, wherein the projections protrude out of the groove beyond the edge plate.
- the support plate in the assembled state can be grasped from the outside with the projections, so that disassembly and re-assembly of the rotor blade can be carried out easily.
- the projections are arranged angled to the leg portions, so that the turbomachine rotor or the wheel disc is engaged with the support plate and thereby held in the axial direction of the turbomachine rotor.
- the support plate is fixed to the wheel disc in the axial direction, in particular, even when the rotor blade is not yet inserted into the groove of the wheel disc during assembly of the turbomachine rotor.
- the support blade placed in the groove on the groove bottom need not be retained from the outside when the blade root is inserted into the groove.
- the supernatant can be bent or rolled over.
- the at least one adjusting screw is secured against unintentional rotation by a securing means.
- the securing means may preferably be an adhesive.
- the set screw can be caulked with a grain impact in the rotor blade.
- the geometric dimensions of the support plate, the set screws and the tightening torque must be adapted to the mass of the blade.
- the rotor blade according to the invention which is provided for mounting in a groove located on the outer circumference of a turbomachinery rotor, extending in the axial direction, has a Blade root with two opposite and arranged perpendicular to the longitudinal axis of the blade root end faces and extending between the two end faces of the blade root, the blade root having a first threaded hole and a second threaded hole, the two threaded holes open on the one hand on the blade root bottom to the outside, and on the other the first threaded hole at one end face and the second threaded hole at the other end side open the blade root to the outside so that the first threaded hole is inclined at a first acute angle and the second threaded hole is inclined at a second acute angle from the longitudinal axis of the turbomachine rotor.
- the support plate according to the invention for biasing a blade of a turbomachinery rotor has a longitudinal direction and has along this two opposing cranks, each with a planar edge, between which the support plate has a back portion.
- the method of assembling a turbomachinery rotor according to the invention comprises the steps of: providing the turbomachinery rotor with circumferentially distributed grooves extending substantially in the axial direction of the turbomachine rotor and having blades therein and a support plate; Inserting the blade into the groove, so that the blade root engages in the groove and so the blade is held in the groove form-fitting in the radial direction; Push the support plate into the groove between the
- Blade foot base and groove bottom Threading the first set screw into the first threaded hole and the second set screw into the second threaded hole until the set screws contact their corresponding cranks; Tighten the two setscrews with a predetermined
- FIG. 2 shows a longitudinal section of the turbomachinery rotor in the region of the blade root
- FIG. 3 shows a support plate in the non-installed state
- a turbine engine rotor 1 has a plurality of rotor blades 2 and a wheel disk 16.
- the rotor blades 2 are attached to the circumference of the wheel disc 16, so that a rotor stage of the turbomachine rotor 1 is formed.
- the blade 2 is made in one piece and has an airfoil 3 and a blade root 4.
- the blade 3 is aerodynamically effective, for example in a compressor or a turbine of a turbomachine.
- the blade root 4 serves for fastening the blade 3 to the wheel disc 16.
- the blade root 4 has in a plane which is perpendicular to the axis of rotation of the turbomachine rotor, a Tannenbaumprofil- shaped cross-section and in a plane in which the axis of rotation of the turbomachine rotor is located, a rectangular cross-section.
- the rectangular cross-section of the blade root 4 is formed by a longitudinal side adjacent to the blade 3, two mutually facing end faces, the Weil are perpendicular to the axis of rotation of the turbomachine rotor 1, and a Schaufelfußunterseite 15, which is arranged substantially parallel to the axis of rotation of the turbomachine rotor 1 and the blade 3 away.
- the blade root 4 In the corner regions of the blade root 4, which lie in the region of the edges formed by the end faces and the underside of the blade root 15, the blade root 4 has regions 5 and 6 subjected to little mechanical stress.
- the first mechanically little loaded area 5 of the blade root 4 is of a first threaded hole 7 and the second mechanically little loaded area 6 of the blade root 4 is penetrated by a second threaded hole 8, wherein the two threaded holes 7, 8 open at the blade root bottom 15 to the outside and the first threaded hole 7 open at the one end face of the blade root 4 and the second threaded hole 8 at the other end face of the blade root 4 to the outside.
- a first screw 9 in the second threaded hole 8 a second screw 10 is screwed.
- the first adjusting screw 9 has a first screw end 11 and the second adjusting screw 10 has a second screw end 12, wherein the screw ends 11, 12 are each located on the blade root bottom side 15 outside of the blade root 4.
- the two threaded holes 7, 8 and the two adjusting screws 9, 10 are arranged pivoted against each other, so that the first threaded hole 7 with the axis of rotation of the turbomachine rotor 1 a first angle 13 and the second threaded hole 8 with the axis of rotation of the turbomachine rotor 1 a second
- angle 14 The two threaded holes 7, 8 are arranged to each other such that the two screw ends 11, 12 of the two screws 9, 10 are arranged facing each other. In each case, the first angle 13 and the second angle 14 are acute angle and the same amount.
- the wheel disc 16 has a groove 17 with a groove bottom 18, which is in engagement with the blade root 4.
- Form The groove 17 is formed such that it encloses the longitudinal sides of the blade root 4 and the blade root bottom 15 in a form-fitting manner, so that the rotor blade 2 is held in a form-fitting manner in the groove 17 in the radial direction and in the circumferential direction of the turbomachinery rotor 1 by means of the fir tree profile of the blade root 4.
- the groove 17 and the blade root 4 are designed in such a way that when the turbomachinery rotor 1 is mounted, the blade 2 with its blade root 4 can be pushed in substantially in the axial direction of the turbomachinery rotor 1. In the assembled turbomachine rotor 1, the end faces of the blade root 4 are substantially flush with the end faces of the wheel disc 16.
- the groove 17 is dimensioned such that a gap is formed between the groove bottom 18 and the blade root bottom 15.
- a support plate 19 is inserted, which has in its center a back portion 20 which is formed by a first crank 21 and a second crank 22.
- a first leg section 25 adjoins the first offset 21 and a second leg section 26 adjoins the second offset 22, wherein the leg sections 25, 26 rest against the groove base 18 and the back section 20 rests against the underside of the blade foot 15.
- the back portion 20 and the leg portions 25, 26 are arranged in alignment with each other.
- the first offset 21 has a first flank 23 and the second offset 22 has a second flank 24, the first screw end 11 abutting the first crank 21 and the second screw end 12 abutting the second crank 24.
- Both the first end of the screw 11 and the first edge 23 and the second end of the screw 12 and the second edge 24 are formed planar, so that the contact between the screws 10, 11 and the support plate 19 is made via a contact surface.
- the two setscrews 9, 10 are screwed in their threaded holes 7, 8 and with a predetermined attracted torque, so that in each case a predetermined force is exerted by the screws 9, 10 on the flanks 23, 24 and thus on the support plate 19.
- the force has a radial component and an axial component, wherein when the two setscrews 9, 10 are tightened with the same tightening torque, the axial components cancel each other.
- the radial components form a predetermined biasing force with which the blade root 4 is pre-biased in the groove 17 predetermined.
- a first projection 27 and on the second leg portion 26 a second projection 28 is provided, wherein the projections 27, 28 extend out of the groove 17 on the wheel disc 16 away.
- the two projections 27, 28 are arranged angled towards the center of the turbomachine rotor 1 to the leg portions 25, 26, so that with the projections 27, 28, the support plate 19 is arranged fixed on the groove bottom 18 in the axial direction of the turbomachine rotor 1.
- the support plate 19 is shown, wherein the first projection 27 are arranged as an extension of the first leg portion 25 and the second projection 28 as an extension of the second leg portion 26.
- the support plate 19 is shown in the unassembled state and in Figure 4 in the assembled state.
- the support plate 19 is pre-curved, so that the support plate 19 in the unassembled state has a convex contour. If the support plate 19, as shown in Figure 4, installed in the groove 17 together with the blade root 4, the support plate 19 is pressed straight, so that the support plate 19 exerts a spring force on the blade root 4 due to spring properties ,
- the blade 2 is inserted into the groove 17 substantially in the axial direction of the turbomachine rotor 1 inserted until the end faces of the blade root 4 are arranged in alignment with the end faces of the wheel disc 16.
- the support plate 19 is pushed according to the embodiment shown in FIG. 3 until the two projections 27 and 28 project from the wheel disc 16.
- the first screw 9 is screwed into the first threaded hole 7 and the second screw 12 in the second threaded hole 8 until the first end of the screw 10, the first edge 23 and the second end of the screw 12, the second edge 24 touch.
- the screws 9, 10 are tightened with the predetermined torque.
- the projections 27 and 28 are bent in the direction of the center of the wheel disc 16, so that the projections 27, 28 abut against the wheel disc.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09709892A EP2242909B1 (en) | 2008-02-14 | 2009-01-23 | Turbomachine rotor, rotor blade for such a turbomachine rotor and corresponding assembling method |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP08002768A EP2090750A1 (en) | 2008-02-14 | 2008-02-14 | Turbomachine rotor, rotor blade for such a turbomachine rotor, supporting strip for such a rotor blade in the turbomachine rotor and corresponding assembling method |
EP09709892A EP2242909B1 (en) | 2008-02-14 | 2009-01-23 | Turbomachine rotor, rotor blade for such a turbomachine rotor and corresponding assembling method |
PCT/EP2009/050781 WO2009100975A1 (en) | 2008-02-14 | 2009-01-23 | Turbomachine rotor comprising a pretensioning device for pretensioning a guide vane |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2242909A1 true EP2242909A1 (en) | 2010-10-27 |
EP2242909B1 EP2242909B1 (en) | 2013-03-13 |
Family
ID=39522377
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08002768A Withdrawn EP2090750A1 (en) | 2008-02-14 | 2008-02-14 | Turbomachine rotor, rotor blade for such a turbomachine rotor, supporting strip for such a rotor blade in the turbomachine rotor and corresponding assembling method |
EP09709892A Not-in-force EP2242909B1 (en) | 2008-02-14 | 2009-01-23 | Turbomachine rotor, rotor blade for such a turbomachine rotor and corresponding assembling method |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08002768A Withdrawn EP2090750A1 (en) | 2008-02-14 | 2008-02-14 | Turbomachine rotor, rotor blade for such a turbomachine rotor, supporting strip for such a rotor blade in the turbomachine rotor and corresponding assembling method |
Country Status (5)
Country | Link |
---|---|
US (1) | US8512001B2 (en) |
EP (2) | EP2090750A1 (en) |
JP (1) | JP5069358B2 (en) |
CN (1) | CN101946062B (en) |
WO (1) | WO2009100975A1 (en) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2299060A1 (en) * | 2009-09-17 | 2011-03-23 | Siemens Aktiengesellschaft | Blade fixation with locking device for turbine blades |
FR2975428B1 (en) * | 2011-05-17 | 2015-11-20 | Snecma | TURBOMACHINE AUBES WHEEL |
EP2562356A1 (en) * | 2011-08-24 | 2013-02-27 | Siemens Aktiengesellschaft | Blade assembly |
US10215035B2 (en) | 2014-12-29 | 2019-02-26 | Rolls-Royce North American Technologies Inc. | Turbine wheels with preloaded blade attachment |
GB201504186D0 (en) | 2015-03-12 | 2015-04-29 | Rolls Royce Plc | Chocking and retaining device |
US10815795B2 (en) * | 2018-12-20 | 2020-10-27 | General Electric Company | Pre-tension and retention structure for composite fan blade |
CN112049686A (en) * | 2019-06-05 | 2020-12-08 | 中国航发商用航空发动机有限责任公司 | Gas turbine rotor and gas turbine |
Family Cites Families (14)
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US1829881A (en) * | 1930-04-05 | 1931-11-03 | Allis Chalmers Mfg Co | Turbine blade mounting |
US2786648A (en) * | 1950-04-04 | 1957-03-26 | United Aircraft Corp | Blade locking device |
DE834408C (en) * | 1950-11-23 | 1952-03-20 | Maschf Augsburg Nuernberg Ag | Prestressed axial blade root attachment for steam and gas turbines |
US2857132A (en) * | 1952-02-19 | 1958-10-21 | Gen Motors Corp | Turbine wheel |
NL257669A (en) * | 1959-11-10 | |||
GB992973A (en) * | 1962-02-26 | 1965-05-26 | Rolls Royce | Improvements in or relating to blade assemblies for fluid flow machines |
DE2639200A1 (en) * | 1976-08-31 | 1978-03-09 | Volkswagenwerk Ag | IMPELLER FOR AXIAL TURBINES, IN PARTICULAR FOR GAS TURBINES |
GB2026101A (en) | 1978-07-22 | 1980-01-30 | Rolls Royce | Rotor blade fixing |
JPS59168878A (en) | 1983-03-14 | 1984-09-22 | 極東産機株式会社 | Portable tatami sewing machine |
JPS6184102U (en) * | 1984-11-07 | 1986-06-03 | ||
US5123813A (en) * | 1991-03-01 | 1992-06-23 | General Electric Company | Apparatus for preloading an airfoil blade in a gas turbine engine |
US5713721A (en) * | 1996-05-09 | 1998-02-03 | General Electric Co. | Retention system for the blades of a rotary machine |
US5984639A (en) * | 1998-07-09 | 1999-11-16 | Pratt & Whitney Canada Inc. | Blade retention apparatus for gas turbine rotor |
EP1905957A1 (en) * | 2006-09-27 | 2008-04-02 | Siemens Aktiengesellschaft | Locking device of a turbine blade |
-
2008
- 2008-02-14 EP EP08002768A patent/EP2090750A1/en not_active Withdrawn
-
2009
- 2009-01-23 JP JP2010545426A patent/JP5069358B2/en not_active Expired - Fee Related
- 2009-01-23 EP EP09709892A patent/EP2242909B1/en not_active Not-in-force
- 2009-01-23 US US12/867,567 patent/US8512001B2/en not_active Expired - Fee Related
- 2009-01-23 WO PCT/EP2009/050781 patent/WO2009100975A1/en active Application Filing
- 2009-01-23 CN CN200980105168.6A patent/CN101946062B/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2009100975A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2009100975A1 (en) | 2009-08-20 |
US8512001B2 (en) | 2013-08-20 |
JP5069358B2 (en) | 2012-11-07 |
US20110171031A1 (en) | 2011-07-14 |
EP2090750A1 (en) | 2009-08-19 |
EP2242909B1 (en) | 2013-03-13 |
CN101946062A (en) | 2011-01-12 |
JP2011511896A (en) | 2011-04-14 |
CN101946062B (en) | 2014-02-05 |
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