GB2206381A - A variable stator vane arrangement for a compressor - Google Patents
A variable stator vane arrangement for a compressor Download PDFInfo
- Publication number
- GB2206381A GB2206381A GB08715314A GB8715314A GB2206381A GB 2206381 A GB2206381 A GB 2206381A GB 08715314 A GB08715314 A GB 08715314A GB 8715314 A GB8715314 A GB 8715314A GB 2206381 A GB2206381 A GB 2206381A
- Authority
- GB
- United Kingdom
- Prior art keywords
- control ring
- stator vane
- pieces
- variable stator
- axial flow
- 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
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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
Description
2206381 1 A VARIABLE STATOR VANE ARRANGEMENT FOR A COMPRESSOR The present
invention relates to variable stator vane arrangements for compressors, particularly axial flow compressors for gas turbine engines.
The compressors of gas turbine engines are generally provided with variable stator vanes,. especially compressors- which have relatively high pressure ratios, to ensure that the compressor will operate efficiently over its full speed range. The variable stator vanes are used to correct the angle of incidence of the air onto a stage of rotor blades to angles which they can tolerate without a break down of flow, stall or surge at relatively low compressor pressure ratios and compressor rotor speeds.
A variable stator vane's angular position is controlled by an operating lever, which is connected to a control ring positioned coaxially with the stator casing.
It is desirable to have as small a radial clearance between the stator casing and the control ring in order to minimise error or discrepancy of stator vane angular position. In operation the stator casing temperature is lower than the temperature of the air surrounding the stator casing, and in which is located the control ring.
The control ring therefore expands more than the stator casing, increasing the clearance between the control ring and stator casing and therefore increasing the error or discrepancy in the stator vane a-ngular position.
Accordingly the present invention seeks to provide a variable stator vane arrangement for an axial flow compressor in which the error or discrepancy of -the stator vane angular position is minimised.
Accordingly the present invention provides a variable stator vane arrangement for an axial flow compressor comprising a plurality of circumferentially spaced apart radially extending variable stator vanes, each variable stator vane being rotatably mounted on a stator casing, a control ring surrounding and arranged 2 coaxially with the stator casing, each variable stator vane being connected to the control ring by an operating lever, the control ring being spaced radially from the stator casing by a clearance, a plurality of pieces of material being arranged circumferentially and positioned radially between the control ring and the stator casing, the plurality of pieces of material having a relatively high coefficient of expansion to control said clearance between the control ring and the stator casing whereby the error of the variable stator vane angular position is reduced. i The plurality of pieces of material may be arranged circumferentially on the control ring, the plurality of pieces of material extending radially inwardly from the control ring towards the stator casing.
Each of the plurality of pieces of material may be positioned in a respective housing, the housings being removably secured to the control ring.
The plurality of piec-es of material may be spaced radially from the stator casing by a predetermined clearance.
The plurality of pieces of material may be equi-spaced circumferentially.
The plurality of pieces of material may be formed from a polyimide resin, or a high coefficient of expansion steel.
The present invention will be more fully explained, by way of example, with reference to the accompanying drawings, in which:- Figure 1 is a partially cut away view of a gas turbine engine showing a variable stator vane arrangement for an axial flow compressor according to the present invention.
Figure 2 is an enlarged partially cut away view of the variable stator vane arrangement in the direction of arrow A in Figure 1.
3 Figure 3 is a view in the direction of arrow B in Figure 2.
Figure 4 is a diagrammatical section through a prior art variable stator vane arrangement.
A turbofan gas turbine engine 10 is shown in Figure 1, and comprises in axial flow series a fan. section 14 which has an intake 12 at its upstream end, a compressor section 16, a combustion system 18, a turbine section 20 and an exhaust nozzle 22. The turbofan gas turbine engine 10 operates quite conventionally in that air is taken in through the intake 12, the air is compressed by the fan 14 and compressor 16 and supplied to the combustion system 18. Fuel is injected into, and burnt in, the combustion system 18 to produce hot gases which flow through and drive the turbines in the turbine section 20 before flowing through the exhaust nozzle 22 to atmosphere. The turbines in turn drive the fan 14 and compressor 16 via shafts (not shown).
The compressor 16 comprises a rotor 24, which has a plurality of axially spaced stages of rotor blades 26. The rotor blades 26 in each stage are circumferentially arranged, and extend radially outwards from the rotor 24. A stator casing 28 is arranged coaxially with, and surrounds, the rotor 24, the stator casing being spaced radially from the rotor blades by a small tip clearance. The stator casing 28 has a plurality of axially spaced stages of stator vanes 30, the stator vanes 30 in each stage are arranged circumferentially and extend radially inwards from the stator casing 28.
The stages of rotor blades and stator vanes are arranged axially alternately.
One of the stages of stator vanes, at the upstream end of the compressor, comprises variable stator vanes 32, each of which is rotatably mounted on the stator casing 28. The variable stator vanes 32 have spindles 34 at their radially outer ends which extend radially through respective apertures in the stator casing 28, to z 4 rotatably mount the variable stator vanes 32 on the stator casing 28.
A control ring 38 as shown partially in Figures 2 and 3 is arranged coaxially with, and surrounds, the stator casing 28, and each variable stator vane 32 'is connected to the control ring 38 by an operating lever 3f. The operating levers 36 are rotatably mounted on the control ring 38 by radially extending spindles 40, which extend through apertures 42 in the control ring 38, and bushes 44 and 46 are provided between the spindles 40 and control ring 38 in the apertures 42. 1 The control ring 38 is spaced radially from the stator casing 28 by a clearance, and has a plurality of circumferentially arranged housing members 48 which are removably secured to the control ring 38 by bolts 50, which extend radially through apertures 54 in the control ring 38. Bushes 56 are provided in the control ring 38 to receive the bolts 50, and spacers 52 are positioned between the control ring 38 and the housing member 48. The housing members 58 are positioned radially on the inner side of the control ring 38, and each housing member 48 has a recess 58 to receive a piece of material 60 which has a high coefficient of expansion. The pieces of material 60 extend radially inwards from the recesses 58 in the housing members 48 and protrude radially therefrom, and are arranged to form a relatively small initial clearance with the stator casing 28.
The stator casing and control ring are for example constructed of titanium, and the pieces of material of high coefficient of expansion are steels with a high coefficient of expansion or preferably are a polyimide resin sold under the Trade name VESPEL by the Du Pont Company, although any suitable material with a high coefficient of expansion may be used, i.e. higher than that of titanium or higher than that of any material from which the stator casing and control ring is made.
W The control ring 38 is rotatably mounted on the stator casing 28, and the control ring 38 is rotated by a ram (not shown) in order to vary the angular position of the variable stator vanes 32.
The variable stator vanes 32 are used to correct the angle of incidence of the air onto the downstream stage of rotor blades to angles of incidence which the rotor blades can tolerate without break down of flow, stall or surge at relatively low compressor pressure ratios and compressor rotor speeds.
The clearance between the stator casing 28 and the control ring 38 should be as small as possible to minimise the error or discrepancy of stator vanes angular position. The clearance between the stator casing 28 and the control ring 38 in the prior art arrangement allows relative movement, as shown in Figure 4., for example by arrows C, and any relative movement between the two from a coaxial position will produce variations or errors in the angular positions of the variable stator vanes 32 from the desired angular position. The relative movement does not produce a uniform variation or error in the angular positions from the desired angular position, but rather there is a range of variations from a zero variation to a maximum variation. There are two diametrically opposite positions of substantially zero error, i.e. the stator vanes on the horizontal plane in this example, and two diametrically opposite positions of maximum error, i.e. the stator vanes on the vertical plane in this example. The greater the clearance between the stator casing 28 and the control ring 38 the greater the possible variation or error in the angular position of the variable stator vanes 32.
In operation of the gas turbine engine 10 the air flowing through the compressor 16 increases in temperature as it flows axially in a downstream direction, and therefore the stator casing 28 temperature at the upstream end is less than that at the downstream 6 end. The control ring 38 is positioned in air at a relatively higher temperature than the upstream end of the stator casing 28. The control ring 38 therefore expands more than the upstream end of the stator casing 28, in which is positioned the variable stator vanes 32, and thus the clearance between the stator casing 28 and control ring 38 increases allowing increased variation in the variable stator vane 32 angular position.
The increase in clearance between the stator casing 28 and the control ring 38 is compensated for by the use of the pieces 60 of high coeffibient of expansion material which expand radially inwards as the control ring 38 expands radially outwards to minimise the effective clearance between the stator casing 28 and the control ring 38 and in turn reduce the discrepancy, variation or error in the angular position of the variable stator vanes 32.
The pieces 60 of high coefficient of expansion material also prevent reduced clearances and binding between the stator casing 28 and control ring 38 at relatively low temperatures.
A compressor may have a plurality of stages of variable stator vanes, and the principle of using the pieces of material of high coefficient of expansion may be used on all these stages of variable stator vanes.
Although the embodiment has shown the use of pieces of material of high coefficient of expansion being positioned on the control ring, it could be possible to position the pieces of material of high coefficient of expansion on the stator casing, but corresponding changes to the initial clearance between the pieces and- the control ring will be necessary and the dimensions of the pieces will be changed to allow for the axial upstream and downstream movement of the control ring as the angle of the variable stator vanes is changed.
7
Claims (10)
1. A variable stator vane arrangement for an axial flow compressor comprising a plurality of circumferentially spaced apart radially extending variable stator vanes, each variable stator vane being rotatably mounted on a stator casing, a control ring surrounding and arranged coaxially with the stator casing, each stator vane being connected to the control ring by an operating lever, the control ring being spaced radially from the stator casing by a clearance, a plurality of pieces of material arranged circumferentially and ppsitioned radially between the control ring and the stator casing, the plurality of pieces of material having a relatively high coefficient of expansion to control said clearance between the control ring and the stator casing whereby any error of the variable stator vane angular position is reduced.
2. A variable stator vane arrangement for an axial flow compressor as claimed in claim 1 in which the plurality of pieces of material are arranged circumferentially on the control ring, the plurality of pieces of material extending radially inwardly from the control ring towards the stator casing.
3. A variable stator vane arrangement for an axial flow compressor as claimed in claim 2 in which each of the plurality of pieces of material is positioned in a respective housing, the housings being removably secured to the control ring.
4. A variable stator vane arrangement for an axial flow compressor as claimed in claim 2 or claim 3 in which the plurality of pieces of material are spaced radially from the stator casing by a predetermined clearance.
5. A variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to 4 in which the plurality of pieces of material are equi-spaced circumferentially.
8
6. A variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to 5 in which the plurality of pieces of material are formed from. a polyimide resin.
7. A variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to. 5 in which the plurality of pieces of material are formed from a high coefficient of expansion steel.
8. A variable stator vane arrafigement for an axial flow compressor substantially as hereinbefore described with reference to and as shown in Figures 1 to 3.
9. A gas turbine engine comprising a variable stator vane arrangement for an axial flow compressor as claimed in any of claims 1 to 7.
10. A gas turbine engine comprising a variable stator vane arrangement for an axial flow compressor substantially as hereinbefore described with reference to and as shown in Figures 1 to 3.
IQ k Published 1988 at The Patent Office, State House, 66171 High Holborn. London WC1R 4TP. Further copies may be obtained from The Patent Offtce, Sales Branch, St Mary Cray, Orpington, KeWt. BR5 3RD. Printed by Multiplex techniques ltd, St Mary Cray, Kent. Con. 1187.
Priority Applications (6)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8715314A GB2206381B (en) | 1987-06-30 | 1987-06-30 | A variable stator vane arrangement for a compressor |
| US07/187,027 US4812106A (en) | 1987-06-30 | 1988-04-27 | Variable stator vane arrangement for a compressor |
| IT20593/88A IT1217605B (en) | 1987-06-30 | 1988-05-16 | VARIABLE DIRECTING PALETTE COMPLEX FOR COMPRESSOR |
| JP63122994A JPS6412035A (en) | 1987-06-30 | 1988-05-19 | Variable stator blade apparatus |
| FR888807338A FR2617544B1 (en) | 1987-06-30 | 1988-06-02 | VARIABLE STATOR BLADING DEVICE FOR COMPRESSOR |
| DE3819232A DE3819232C2 (en) | 1987-06-30 | 1988-06-06 | Adjustable stator blade arrangement for an axial flow compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8715314A GB2206381B (en) | 1987-06-30 | 1987-06-30 | A variable stator vane arrangement for a compressor |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB8715314D0 GB8715314D0 (en) | 1987-08-05 |
| GB2206381A true GB2206381A (en) | 1989-01-05 |
| GB2206381B GB2206381B (en) | 1991-10-09 |
Family
ID=10619812
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8715314A Expired - Lifetime GB2206381B (en) | 1987-06-30 | 1987-06-30 | A variable stator vane arrangement for a compressor |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US4812106A (en) |
| JP (1) | JPS6412035A (en) |
| DE (1) | DE3819232C2 (en) |
| FR (1) | FR2617544B1 (en) |
| GB (1) | GB2206381B (en) |
| IT (1) | IT1217605B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2699595A1 (en) * | 1992-12-23 | 1994-06-24 | Snecma | Device for guiding in rotation a control ring for pivoting vanes. |
| JP2006233969A (en) * | 2005-02-25 | 2006-09-07 | Snecma | Device for adjusting centering of ring for synchronizing control of turning vane in turbo machine |
| US7198454B2 (en) | 2003-11-14 | 2007-04-03 | Rolls-Royce Plc | Variable stator vane arrangement for a compressor |
| EP2481891A2 (en) * | 2011-02-01 | 2012-08-01 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| EP2481892A2 (en) * | 2011-02-01 | 2012-08-01 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| EP3000984A1 (en) * | 2014-09-26 | 2016-03-30 | Rolls-Royce Deutschland Ltd & Co KG | Turbine vane adjustment device for a gas turbine |
| EP3333375A1 (en) * | 2016-12-12 | 2018-06-13 | United Technologies Corporation | Sync ring assembly and associated clevis including a rib |
Families Citing this family (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4925364A (en) * | 1988-12-21 | 1990-05-15 | United Technologies Corporation | Adjustable spacer |
| JP2742101B2 (en) * | 1989-08-25 | 1998-04-22 | 三井化学株式会社 | Internal structure of fan case for turbofan engine |
| US5037269A (en) * | 1990-01-26 | 1991-08-06 | Westinghouse Electric Corp. | Self-locking nozzle blocks for steam turbines |
| US5224824A (en) * | 1990-09-12 | 1993-07-06 | United Technologies Corporation | Compressor case construction |
| US5316437A (en) * | 1993-02-19 | 1994-05-31 | General Electric Company | Gas turbine engine structural frame assembly having a thermally actuated valve for modulating a flow of hot gases through the frame hub |
| JP3285676B2 (en) | 1993-08-25 | 2002-05-27 | キヤノン株式会社 | Ink end detecting device and ink end detecting method for ink jet recording apparatus |
| DE19516382A1 (en) * | 1995-05-04 | 1996-11-07 | Deutsche Forsch Luft Raumfahrt | Adjustment ring |
| US5622473A (en) * | 1995-11-17 | 1997-04-22 | General Electric Company | Variable stator vane assembly |
| US6884025B2 (en) * | 2002-09-30 | 2005-04-26 | United Technologies Corporation | Shim lock/pin anti-rotation bumper design |
| US20050129340A1 (en) * | 2003-12-10 | 2005-06-16 | Arnold Robert A. | Hourglass bearing |
| GB0504588D0 (en) * | 2005-03-05 | 2005-04-13 | Rolls Royce Plc | Pivot ring |
| US7628579B2 (en) * | 2005-07-20 | 2009-12-08 | United Technologies Corporation | Gear train variable vane synchronizing mechanism for inner diameter vane shroud |
| US7690889B2 (en) * | 2005-07-20 | 2010-04-06 | United Technologies Corporation | Inner diameter variable vane actuation mechanism |
| US7753647B2 (en) * | 2005-07-20 | 2010-07-13 | United Technologies Corporation | Lightweight cast inner diameter vane shroud for variable stator vanes |
| US7588415B2 (en) * | 2005-07-20 | 2009-09-15 | United Technologies Corporation | Synch ring variable vane synchronizing mechanism for inner diameter vane shroud |
| FR2902454A1 (en) * | 2006-06-16 | 2007-12-21 | Snecma Sa | TURBOMACHINE STATOR COMPRISING A FLOOR OF ADJUSTERS ADJUSTED BY A ROTATING CROWN WITH AUTOMATIC CENTERING |
| US8092157B2 (en) * | 2007-12-19 | 2012-01-10 | United Technologies Corporation | Variable turbine vane actuation mechanism having a bumper ring |
| EP2107217A1 (en) * | 2008-03-31 | 2009-10-07 | Siemens Aktiengesellschaft | Unison ring assembly for an axial compressor casing |
| DE102008033560A1 (en) * | 2008-07-17 | 2010-01-21 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine engine with adjustable vanes |
| US8505304B2 (en) * | 2008-12-01 | 2013-08-13 | General Electric Company | Fuel nozzle detachable burner tube with baffle plate assembly |
| US8393857B2 (en) * | 2009-10-09 | 2013-03-12 | Rolls-Royce Corporation | Variable vane actuation system |
| US9068470B2 (en) | 2011-04-21 | 2015-06-30 | General Electric Company | Independently-controlled gas turbine inlet guide vanes and variable stator vanes |
| FR2983924B1 (en) * | 2011-12-09 | 2013-11-22 | Snecma | ANNULAR HOUSING FOR A TURBOMACHINE COMPRESSOR |
| US20140064912A1 (en) * | 2012-08-29 | 2014-03-06 | General Electric Company | Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines |
| US20140093362A1 (en) | 2012-09-28 | 2014-04-03 | United Technologies Corporation | Gas turbine engine components and method of assembly |
| US9822651B2 (en) | 2012-09-28 | 2017-11-21 | United Technologies Corporation | Synchronization ring runner with cradle |
| US9422825B2 (en) | 2012-11-05 | 2016-08-23 | United Technologies Corporation | Gas turbine engine synchronization ring |
| US9617869B2 (en) * | 2013-02-17 | 2017-04-11 | United Technologies Corporation | Bumper for synchronizing ring of gas turbine engine |
| GB201614803D0 (en) * | 2016-09-01 | 2016-10-19 | Rolls Royce Plc | Variable stator vane rigging |
| DE102016122640A1 (en) * | 2016-11-23 | 2018-05-24 | Rolls-Royce Deutschland Ltd & Co Kg | Guide vane assembly with balancing device |
| DE102016122639A1 (en) * | 2016-11-23 | 2018-05-24 | Rolls-Royce Deutschland Ltd & Co Kg | Guide vane assembly with balancing device |
| US10815820B2 (en) * | 2019-02-05 | 2020-10-27 | Raytheon Technologies Corporation | Integral shear locking bumper for gas turbine engine |
| US11125106B2 (en) * | 2019-09-05 | 2021-09-21 | Raytheon Technologies Corporation | Synchronizing ring surge bumper |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1313938A (en) * | 1969-08-14 | 1973-04-18 | Bennes Marrel | Gas turbine engines |
| US3994620A (en) * | 1975-06-30 | 1976-11-30 | Wallace-Murray Corporation | Variable exducer turbine control |
| GB1499531A (en) * | 1976-05-24 | 1978-02-01 | Secr Defence | Apparatus for varying the incidence of turbomachinery stator blades |
| GB1513688A (en) * | 1975-10-14 | 1978-06-07 | Westinghouse Canada Ltd | Gas turbine engine |
| US4502836A (en) * | 1982-07-02 | 1985-03-05 | Swearingen Judson S | Method for nozzle clamping force control |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2933234A (en) * | 1954-12-28 | 1960-04-19 | Gen Electric | Compressor stator assembly |
| CH558477A (en) * | 1972-11-27 | 1975-01-31 | Bbc Sulzer Turbomaschinen | ADJUSTMENT DEVICE FOR ROTATING GUIDE VANES. |
| DE2426824A1 (en) * | 1974-06-04 | 1976-01-02 | Ltg Lufttechnische Gmbh | Fan or blower torsion type governor - has levers attached to guide blade pins and fulcrumed lever ball heads |
| DE3623001C1 (en) * | 1986-07-09 | 1987-07-09 | Mtu Muenchen Gmbh | Adjustment device for swiveling guide vanes of turbo engines |
| US4718823A (en) * | 1987-02-24 | 1988-01-12 | United Technologies Corporation | Pitch changing mechanism for fan blades |
-
1987
- 1987-06-30 GB GB8715314A patent/GB2206381B/en not_active Expired - Lifetime
-
1988
- 1988-04-27 US US07/187,027 patent/US4812106A/en not_active Expired - Lifetime
- 1988-05-16 IT IT20593/88A patent/IT1217605B/en active
- 1988-05-19 JP JP63122994A patent/JPS6412035A/en active Pending
- 1988-06-02 FR FR888807338A patent/FR2617544B1/en not_active Expired - Lifetime
- 1988-06-06 DE DE3819232A patent/DE3819232C2/en not_active Expired - Lifetime
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1313938A (en) * | 1969-08-14 | 1973-04-18 | Bennes Marrel | Gas turbine engines |
| US3994620A (en) * | 1975-06-30 | 1976-11-30 | Wallace-Murray Corporation | Variable exducer turbine control |
| GB1513688A (en) * | 1975-10-14 | 1978-06-07 | Westinghouse Canada Ltd | Gas turbine engine |
| GB1499531A (en) * | 1976-05-24 | 1978-02-01 | Secr Defence | Apparatus for varying the incidence of turbomachinery stator blades |
| US4502836A (en) * | 1982-07-02 | 1985-03-05 | Swearingen Judson S | Method for nozzle clamping force control |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2699595A1 (en) * | 1992-12-23 | 1994-06-24 | Snecma | Device for guiding in rotation a control ring for pivoting vanes. |
| US5387080A (en) * | 1992-12-23 | 1995-02-07 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Rotationally guided control ring for pivotable vanes in a turbomachine |
| US7198454B2 (en) | 2003-11-14 | 2007-04-03 | Rolls-Royce Plc | Variable stator vane arrangement for a compressor |
| JP2006233969A (en) * | 2005-02-25 | 2006-09-07 | Snecma | Device for adjusting centering of ring for synchronizing control of turning vane in turbo machine |
| EP2481891A3 (en) * | 2011-02-01 | 2013-12-18 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| EP2481892A2 (en) * | 2011-02-01 | 2012-08-01 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| EP2481891A2 (en) * | 2011-02-01 | 2012-08-01 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| EP2481892A3 (en) * | 2011-02-01 | 2013-12-18 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| US8794910B2 (en) | 2011-02-01 | 2014-08-05 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| US8864450B2 (en) | 2011-02-01 | 2014-10-21 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| EP2824286A1 (en) * | 2011-02-01 | 2015-01-14 | United Technologies Corporation | Gas turbine engine synchronizing ring bumper |
| EP3000984A1 (en) * | 2014-09-26 | 2016-03-30 | Rolls-Royce Deutschland Ltd & Co KG | Turbine vane adjustment device for a gas turbine |
| DE102014219552A1 (en) * | 2014-09-26 | 2016-03-31 | Rolls-Royce Deutschland Ltd & Co Kg | Guide vane adjusting a gas turbine |
| US9976438B2 (en) | 2014-09-26 | 2018-05-22 | Rolls-Royce Detschland Ltd & Co KG | Stator vane adjusting device of a gas turbine |
| EP3333375A1 (en) * | 2016-12-12 | 2018-06-13 | United Technologies Corporation | Sync ring assembly and associated clevis including a rib |
Also Published As
| Publication number | Publication date |
|---|---|
| DE3819232C2 (en) | 1997-01-09 |
| IT1217605B (en) | 1990-03-30 |
| GB2206381B (en) | 1991-10-09 |
| FR2617544B1 (en) | 1990-07-20 |
| IT8820593A0 (en) | 1988-05-16 |
| US4812106A (en) | 1989-03-14 |
| JPS6412035A (en) | 1989-01-17 |
| GB8715314D0 (en) | 1987-08-05 |
| FR2617544A1 (en) | 1989-01-06 |
| DE3819232A1 (en) | 1989-01-12 |
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| Date | Code | Title | Description |
|---|---|---|---|
| PE20 | Patent expired after termination of 20 years |
Effective date: 20070629 |