EP0488874B1 - Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken - Google Patents
Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken Download PDFInfo
- Publication number
- EP0488874B1 EP0488874B1 EP91403182A EP91403182A EP0488874B1 EP 0488874 B1 EP0488874 B1 EP 0488874B1 EP 91403182 A EP91403182 A EP 91403182A EP 91403182 A EP91403182 A EP 91403182A EP 0488874 B1 EP0488874 B1 EP 0488874B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- disc
- shoe
- blades
- shoes
- wall
- 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
Links
- 239000000945 filler Substances 0.000 title 1
- 238000005192 partition Methods 0.000 claims description 7
- 238000011144 upstream manufacturing Methods 0.000 claims description 6
- 239000012530 fluid Substances 0.000 claims description 5
- 230000014759 maintenance of location Effects 0.000 claims description 4
- 230000001747 exhibiting effect Effects 0.000 claims 2
- 238000000926 separation method Methods 0.000 claims 1
- 238000013016 damping Methods 0.000 description 4
- 239000002131 composite material Substances 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 239000006096 absorbing agent Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 210000000003 hoof Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 210000003462 vein Anatomy 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
-
- 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
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/50—Vibration damping features
Definitions
- the present invention relates to a rotor of known type of fan or compressor of a turbomachine, of the type comprising a rotor disc, a series of radial blades mounted in axial housings produced in the periphery of said disc, a series of shoes arranged between said vanes in order to maintain the spacing between said vanes and to constitute the internal profile of the annular stream of fluid circulating from upstream to downstream of said stage, means for fixing said shoes on said disc each of said shoes having an outer wall defining the internal profile of the vein and distant from the periphery of said disc, the axial ends of said external wall being located substantially in the planes of the front and rear faces of said disc.
- turbomachine rotor is particularly used in large diameter stages, because it is imperative, on the one hand, to limit the diameter of the disc carrying the blades because of the considerable centrifugal force obtained at the high rotational speeds of the turbomachine, and, on the other hand, to increase the internal diameter of the annular stream of fluid flowing upstream downstream of the stage so as to have a substantially uniform fluid flow speed throughout the cross section of the stream.
- the British document GB-2 006 883 in particular shows a rotor for a turbomachine stage of the type mentioned above.
- the shoe described in this document comprises, at the rear, a hook directed upwards which cooperates with a groove provided in correspondence in a first retaining ring fixed by a bayonet device on the rear face of the disc, and it comprises, at the front, a rib which extends towards the axis of the disc and which cooperates with the front face of the disc to prevent the axial displacement of the shoe towards the back.
- a second retaining ring, fixed by bolting, is provided on the front face of the disc to connect the front end of the shoe with said disc.
- the shoe In this method of construction and attachment, the shoe must have an internal wall which is only partially supported on the periphery of the disc so as to be able to engage the rear hook in the corresponding groove of the first retaining ring by pivoting. shoe on the periphery of the disc. This results in a complex configuration of the hoof and an increase in weight.
- the bayonet device used to fix the first retaining ring on the rear face of the disc requires delicate machining of the disc and of this ring.
- FR-A 1 134 548 shows a device in which each of the shoes has a front wall and a rear wall which extend radially towards the axis of the turbomachine from said axial ends of the external wall so as to cover at least partially the front and rear faces of said disc and, in which the means for fixing said shoes to said disc comprise, for each of said shoes, at least one front hook extending axially rearwards from its front wall and at least one rear hook which extends forward from its rear wall, and grooves formed in said disc in correspondence with said hooks, said grooves extending between the ends of the mounting housings of the two blades adjacent to said shoe, said grooves and said hooks being shaped and dimensioned so that said shoe can be mounted by presentation to the right of a mounting housing and sliding of said shoe in the plane of the disc.
- the grooves and the hooks cooperate with one another to retain the shoe radially during the rotation of the disc.
- the front and rear walls of the shoe cooperate with the disc to axially retain the shoe forwards and backwards.
- the grooves are preferably circular in shape, the center of which is on the axis of the turbomachine. But this is not compulsory. Their shape must allow the mounting of the shoe by sliding it in the plane of the disc.
- each shoe has at least one cleat which extends from its rear wall to at least partially cover a mounting housing adjacent to said shoe and has a locking tab extending radially towards the axis of the turbomachine from its front wall, said locking tab being spaced from the front face of said disc and cooperating with an additional groove of the disc, means of axial retention of the blades in their respective housings being provided, the means of axial retention of said series of blades being formed, upstream of said stage, by said tabs and, downstream of said stage, by an annular segment interposed between the front face of said disc and said locking tabs.
- each shoe also has a central partition which extends from its external wall towards the periphery of the disc and is substantially parallel to the plane of the adjacent blades, said partition having a slot in the vicinity of said external wall, and it is equipped with a vibration damper formed by a spring leaf passing through said slot and damping plates provided at the ends of said spring leaf.
- each shoe also has additional walls extending from the underside of the external wall and serving as a stop for shock absorber pads.
- the drawing shows a rotor 1 of a stage of a turbomachine, in which the blades 2 are fixed in axial housings 3 provided on the periphery 4 of a disc 5.
- the blades 2 are of the type without platform.
- the internal profile of the stream of fluid flowing upstream downstream of the blade stage is obtained by the external wall 6 of shoes 7 arranged between the blades 2 and fixed to the disc 5. Each shoe 7 further maintains the spacing between two adjacent blades 2.
- Each shoe 7 has a front wall 8 which extends radially towards the axis of the turbomachine from the front end 9 of the external wall 6 and which at least partially covers the front face 10 of the disc 5. It has in addition, a rear wall 11 which extends radially towards the axis of the turbomachine from the rear end 12 of the external wall 6 and which at least partially covers the rear face 13 of the disc 5.
- the portions of the front 8 and rear 11 walls which cover the front 10 and rear 13 faces of the disc 5 have each at least one hook which extends axially towards the disc 5 and cooperates with a groove formed in correspondence in the wall of the disc 5.
- the front wall 8 thus comprises at least one front hook 14 which extends towards the rear and cooperates with the groove 15, and the rear wall 11 has at least one hook 16 which extends forward and cooperates with the groove 17.
- the front grooves 15 and rear 17 of the disc 5 extend between the axial housings 3 used for mounting the two blades 2 adjacent to the corresponding shoe 7.
- the circumferential width of the hooks 14 and 16 must be less than the width of an axial housing 3 in line with the grooves 15 and 17 to allow the mounting of the stage vanes 1 as explained below.
- the rear wall 11 of the shoe 7 is extended in the direction of the circumference of the disc 5 by at least one cleat 18 which at least partially closes the rear end of a mounting housing 3 adjacent to said shoe 7
- a stopper 18 is provided on each side of the shoe 7.
- the shoe 7 also has on its front face a locking tab 19 which extends towards the axis of the turbomachine and which is spaced from the front face. 10 of the disc 5. This locking tab 19 cooperates with an additional groove 20.
- An annular segment 21 is interposed between the front face 10 of the disc 5 and all of the locking tabs 19 of the shoes 7.
- the annular segment 21 covers the at least partially the front ends of the housings 3 for mounting the blades 2.
- the annular segment 21 and the cleats 18 of the shoes 7 thus constitute the means of axial retention of the blades 2.
- Each shoe 7 further has on the underside of its outer wall 6 a central partition 22 which extends parallel to the adjacent vanes 2 towards the periphery 4 of the disc 5.
- This central partition 22 has in the vicinity of the outer wall 6 a slot 23 through which passes a spring leaf 24 provided at each of its ends with damper plates 25.
- the assembly 26 constituted by the spring leaf 24 and damper plates 25 constitutes a vibration damper.
- the leaf spring 24 is of curvilinear shape, so that, when the rotor 1 stops, the plates 25 are in the vicinity of the periphery 4 of the disc 5. The action of the centrifugal force will force the plates 25 to move away from the periphery 4 of the disk 5 against the bending force of the spring leaf 24. The plates 25 then come to bear on the adjacent vanes 2 thus promoting vibration damping.
- Each shoe 7 also has additional walls 27 which extend from the underside of the external wall 6 perpendicular to the central partition 22 and which serve as a stop for the plates 25.
- the shoe 7 is made of a composite material.
- the vibration damper 25 can be produced by mounting the damper plates 25 on the spring leaf 24, but it can also be produced in one piece, in which case it will be put in place when the composite shoe is manufactured. .
- the mounting of a blade 2 and a shoe 7 adjacent to the disc 5 is done as follows: the blade 2 is mounted in a housing 3 by sliding it in a direction parallel to the axis of this housing 3; the shoe 7 is mounted by positioning its base in the housing 3 adjacent to the already mounted blade 2, by sliding it in the plane of the disc 5, the two hooks 14 and 16 being introduced into the corresponding grooves 15 and 17, and by pressing it against the already mounted blade 2.
- the annular segment 21 is rotated between the front face 10 of the disc 5 and the locking tabs 19 after each assembly of a blade-shoe pair. We continue this assembly operation until the last dawn 2.
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)
Claims (3)
- Rotor einer Stufe eines Gebläses oder eines Turbomaschinenkompressors des Typs mit einer Rotorscheibe (5), einer Reihe von radialen Schaufeln (2), die in axialen Halterungen (3) angebracht sind, die in dem Umfangsbereich (4) der Scheibe (5) ausgeführt sind, einer Reihe von Zwischenstücken (7), die zwischen den Schaufeln (2) zur Abstandshaltung zwischen den Schaufeln (2) und zur Bildung des inneren Strömungsprofils des Fluids dienen, das von vorne nach hinten in der Stufe strömt, und Mitteln zur Befestigung der Zwischenstücke (7) an der Scheibe (5),
wobei jedes der Zwischenstücke (7) eine Außenwand (6) aufweist, die das innere Strömungsprofil begrenzt und abgelegen von dem Umfangsbereich der Scheibe (5) ist,
wobei die axialen Enden (9, 12) der Zwischenstücke (7) im wesentlichen jeweils in den Ebenen der Vorderseite (10) und der Rückseite (13) der Scheibe (5) liegen, und jedes Zwischenstück (7) eine Vorderwand (8) und eine Rückwand (11) aufweist, die sich radial in Richtung der Achse der Turbomaschine erstrecken ausgehend von den axialen Enden (9, 12) der Außenwand, so daß sie wenigstens teilweise die vordere Seite (10) und die Rückseite (13) der Scheibe bedecken, wobei die Mittel zur Befestigung der Zwischenstücke (7) an der Scheibe (5) für jedes Zwischenstück (7) wenigstens einen vorderen Haken (14), der sich axial nach hinten ausgehend von dessen Vorderwand (8) erstreckt, wenigstens einen rückseitigen Haken (16), der sich axial nach vorne ausgehend von dessen Rückwand (11) erstreckt und Vertiefungen (15, 17) aufweisen, die in der Scheibe (5) entsprechend den Haken (14, 16) angeordnet sind, wobei die Vertiefungen (15, 17) sich zwischen den Enden der Montage-Halterungen (3) der beiden Schaufeln (2) erstrecken, die an das Zwischenstück (7) angrenzen, wobei die Vertiefungen (15, 17) und die Haken (14, 16) solche Formen und Abmessungen aufweisen, daß das Zwischenstück (7) angebracht werden kann durch Anlegen rechts von einer Montage-Halterung (3) und Einschieben des Zwischenstücks (7) in die Ebene der Scheibe (5),
dadurch gekennzeichnet,
daß jedes Zwischenstück (7) wenigstens ein Anschlagsteil (18) aufweist, das sich ausgehend von dessen Rückwand (11) erstreckt und wenigstens teilweise eine Montage-Halterung (3) bedeckt, die an das Zwischenstück (7) angrenzt, und eine Verriegelungsklammer (19), die sich radial in Richtung der Achse der Turbomaschine erstreckt ausgehend von dessen Vorderwand (8), wobei die Verriegelungsklammer (19) von der Vorderseite (10) der Scheibe (5) beabstandet ist und mit einer zusätzlichen Vertiefung (20) der Scheibe (5) zusammenwirkt, und
daß Mittel zur axialen Halterung der Schaufel (2) in ihren jeweiligen Halterungen (3) vorgesehen sind, und dadurch die Mittel zur axialen Halterung der Reihe von Schaufeln (2) an der Vorderseite der Stufe durch die Anschlagsteile (18) und auf der Rückseite der Stufe durch ein ringförmiges Element (21) gebildet sind, das zwischen der Vorderseite (10) der Scheibe (5) und den Verriegelungsklammern (19) liegt. - Rotor gemäß Anspruch 1,
dadurch gekennzeichnet,
daß jedes Zwischenstück (7) weiterhin eine mittlere Zwischenwand (22) aufweist, die sich ausgehend von dessen Außenwand (6) in Richtung des Umfangsbereichs (4) der Scheibe (5) erstreckt und im wesentlichen parallel zu der Ebene der angrenzenden Schaufeln (2) ist, wobei die Zwischenwand (22) einen Schlitz (23) in der Nähe der Außenwand (6) aufweist, und daß es mit einem Vibrationsdämpfer (26) versehen ist, der durch ein Federblatt (24), das durch den Schlitz (23) hindurchgeht, und Dämpfungsplatten (25) gebildet ist, die an den Enden des Federblatts (24) vorgesehen sind. - Rotor nach Anspruch 2,
dadurch gekennzeichnet,
daß jedes Zwischenstück (7) ferner zusätzliche Wände (27) aufweist, die sich ausgehend von der unteren Seite der Außenwand (6) erstrecken und als Anschlag für die Dämpfungsplatten (25) dienen.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9014850 | 1990-11-28 | ||
FR909014850A FR2669686B1 (fr) | 1990-11-28 | 1990-11-28 | Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine. |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0488874A1 EP0488874A1 (de) | 1992-06-03 |
EP0488874B1 true EP0488874B1 (de) | 1994-11-09 |
Family
ID=9402665
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP91403182A Expired - Lifetime EP0488874B1 (de) | 1990-11-28 | 1991-11-26 | Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken |
Country Status (4)
Country | Link |
---|---|
US (1) | US5161949A (de) |
EP (1) | EP0488874B1 (de) |
DE (1) | DE69105099T2 (de) |
FR (1) | FR2669686B1 (de) |
Families Citing this family (42)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5277548A (en) * | 1991-12-31 | 1994-01-11 | United Technologies Corporation | Non-integral rotor blade platform |
GB9208409D0 (en) * | 1992-04-16 | 1992-06-03 | Rolls Royce Plc | Rotors for gas turbine engines |
FR2716502B1 (fr) * | 1994-02-23 | 1996-04-05 | Snecma | Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires. |
FR2739136B1 (fr) * | 1995-09-21 | 1997-10-31 | Snecma | Agencement amortissant pour des aubes de rotor |
FR2739135B1 (fr) * | 1995-09-21 | 1997-10-31 | Snecma | Agencement amortisseur monte entre des aubes de rotor |
US6447250B1 (en) * | 2000-11-27 | 2002-09-10 | General Electric Company | Non-integral fan platform |
JP4807113B2 (ja) * | 2006-03-14 | 2011-11-02 | 株式会社Ihi | ファンのダブテール構造 |
GB0614640D0 (en) * | 2006-07-22 | 2006-08-30 | Rolls Royce Plc | An annulus filler seal |
US7762781B1 (en) | 2007-03-06 | 2010-07-27 | Florida Turbine Technologies, Inc. | Composite blade and platform assembly |
US7766609B1 (en) * | 2007-05-24 | 2010-08-03 | Florida Turbine Technologies, Inc. | Turbine vane endwall with float wall heat shield |
CN101255873B (zh) * | 2008-02-28 | 2010-06-09 | 大连海事大学 | 压气机动叶叶尖小翼 |
GB0814718D0 (en) * | 2008-08-13 | 2008-09-17 | Rolls Royce Plc | Annulus filler |
US8137072B2 (en) * | 2008-10-31 | 2012-03-20 | Solar Turbines Inc. | Turbine blade including a seal pocket |
US8393869B2 (en) * | 2008-12-19 | 2013-03-12 | Solar Turbines Inc. | Turbine blade assembly including a damper |
US8616849B2 (en) * | 2009-02-18 | 2013-12-31 | Pratt & Whitney Canada Corp. | Fan blade platform |
US8568102B2 (en) | 2009-02-18 | 2013-10-29 | Pratt & Whitney Canada Corp. | Fan blade anti-fretting insert |
US8066479B2 (en) * | 2010-04-05 | 2011-11-29 | Pratt & Whitney Rocketdyne, Inc. | Non-integral platform and damper for an airfoil |
FR2965843B1 (fr) * | 2010-10-06 | 2012-11-09 | Snecma | Rotor pour turbomachine |
US8827651B2 (en) | 2010-11-01 | 2014-09-09 | Rolls-Royce Plc | Annulus filler |
US10036261B2 (en) * | 2012-04-30 | 2018-07-31 | United Technologies Corporation | Blade dovetail bottom |
US9650901B2 (en) | 2012-05-31 | 2017-05-16 | Solar Turbines Incorporated | Turbine damper |
US9279332B2 (en) | 2012-05-31 | 2016-03-08 | Solar Turbines Incorporated | Turbine damper |
US9528376B2 (en) * | 2012-09-13 | 2016-12-27 | General Electric Company | Compressor fairing segment |
US9303519B2 (en) * | 2012-10-31 | 2016-04-05 | Solar Turbines Incorporated | Damper for a turbine rotor assembly |
US9347325B2 (en) * | 2012-10-31 | 2016-05-24 | Solar Turbines Incorporated | Damper for a turbine rotor assembly |
FR3003294B1 (fr) * | 2013-03-15 | 2018-03-30 | Safran Aircraft Engines | Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante |
WO2014149366A1 (en) * | 2013-03-15 | 2014-09-25 | United Technologies Corporation | Injection molded composite fan platform |
FR3021691B1 (fr) * | 2014-06-03 | 2016-06-24 | Snecma | Rotor pour turbomachine comportant des aubes a plates-formes raportees |
US10197009B2 (en) * | 2014-07-30 | 2019-02-05 | Pratt & Whitney Canada Corp. | Gas turbine engine ejector |
US9995162B2 (en) * | 2014-10-20 | 2018-06-12 | United Technologies Corporation | Seal and clip-on damper system and device |
US10156151B2 (en) | 2014-10-23 | 2018-12-18 | Rolls-Royce North American Technologies Inc. | Composite annulus filler |
FR3035677B1 (fr) * | 2015-04-29 | 2017-05-12 | Snecma | Aube munie de plateformes possedant des portions d'accrochage |
FR3038653B1 (fr) * | 2015-07-08 | 2017-08-04 | Snecma | Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante |
US10662784B2 (en) | 2016-11-28 | 2020-05-26 | Raytheon Technologies Corporation | Damper with varying thickness for a blade |
US10677073B2 (en) | 2017-01-03 | 2020-06-09 | Raytheon Technologies Corporation | Blade platform with damper restraint |
US10731479B2 (en) * | 2017-01-03 | 2020-08-04 | Raytheon Technologies Corporation | Blade platform with damper restraint |
EP3477048B1 (de) * | 2017-10-27 | 2021-08-18 | MTU Aero Engines AG | Kombination zum abdichten eines spalts zwischen turbomaschinenschaufeln und zum reduzieren von schwingungen der turbomaschinenschaufeln |
FR3091563B1 (fr) * | 2019-01-04 | 2023-01-20 | Safran Aircraft Engines | Joint d’étanchéité amélioré de plateforme inter-aubes |
CN114439551B (zh) * | 2020-10-30 | 2024-05-10 | 中国航发商用航空发动机有限责任公司 | 航空发动机 |
CN113217461B (zh) * | 2021-05-12 | 2022-08-16 | 中南大学 | 一种叶片、其造型方法和制造方法及压气机 |
FR3126446A1 (fr) * | 2021-09-01 | 2023-03-03 | Safran Aircraft Engines | Amortisseur déformable pour roue mobile de turbomachine |
US20230194096A1 (en) * | 2021-12-17 | 2023-06-22 | Pratt & Whitney Canada Corp. | Exhaust system for a gas turbine engine and method for using same |
Family Cites Families (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE540433A (de) * | 1954-08-12 | |||
US3294364A (en) * | 1962-01-02 | 1966-12-27 | Gen Electric | Rotor assembly |
GB981476A (en) * | 1963-11-04 | 1965-01-27 | Rolls Royce | Gas turbine engine vane assembly |
CH494896A (de) * | 1968-08-09 | 1970-08-15 | Sulzer Ag | Halterung von Laufschaufeln im Rotor einer Turbomaschine |
GB1259750A (en) * | 1970-07-23 | 1972-01-12 | Rolls Royce | Rotor for a fluid flow machine |
BE791375A (fr) * | 1971-12-02 | 1973-03-01 | Gen Electric | Deflecteur et amortisseur pour ailettes de turbomachines |
GB2006883B (en) * | 1977-10-27 | 1982-02-24 | Rolls Royce | Fan or compressor stage for a gas turbine engine |
GB2171151B (en) * | 1985-02-20 | 1988-05-18 | Rolls Royce | Rotors for gas turbine engines |
FR2639402B1 (fr) * | 1988-11-23 | 1990-12-28 | Snecma | Disque ailete de rotor de turbomachine |
US4872810A (en) * | 1988-12-14 | 1989-10-10 | United Technologies Corporation | Turbine rotor retention system |
-
1990
- 1990-11-28 FR FR909014850A patent/FR2669686B1/fr not_active Expired - Fee Related
-
1991
- 1991-11-26 EP EP91403182A patent/EP0488874B1/de not_active Expired - Lifetime
- 1991-11-26 DE DE69105099T patent/DE69105099T2/de not_active Expired - Fee Related
- 1991-11-27 US US07/799,326 patent/US5161949A/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
FR2669686B1 (fr) | 1994-09-02 |
US5161949A (en) | 1992-11-10 |
DE69105099D1 (de) | 1994-12-15 |
FR2669686A1 (fr) | 1992-05-29 |
EP0488874A1 (de) | 1992-06-03 |
DE69105099T2 (de) | 1995-04-20 |
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