GB2410530A - Electrically actuated stator vane arrangement - Google Patents

Electrically actuated stator vane arrangement Download PDF

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Publication number
GB2410530A
GB2410530A GB0401663A GB0401663A GB2410530A GB 2410530 A GB2410530 A GB 2410530A GB 0401663 A GB0401663 A GB 0401663A GB 0401663 A GB0401663 A GB 0401663A GB 2410530 A GB2410530 A GB 2410530A
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GB
United Kingdom
Prior art keywords
arrangement
stator vane
shaft
electric motor
gear
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.)
Withdrawn
Application number
GB0401663A
Other versions
GB0401663D0 (en
Inventor
Caetano Peng
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB0401663A priority Critical patent/GB2410530A/en
Publication of GB0401663D0 publication Critical patent/GB0401663D0/en
Publication of GB2410530A publication Critical patent/GB2410530A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/10Final actuators
    • F01D17/12Final actuators arranged in stator parts
    • F01D17/14Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162Final 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
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00Regulating or controlling by varying flow
    • F01D17/20Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
    • F01D17/22Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical
    • F01D17/24Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical electrical
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/52Casings; Connections of working fluid for axial pumps
    • F04D29/54Fluid-guiding means, e.g. diffusers
    • F04D29/56Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00Application
    • F05D2220/30Application in turbines
    • F05D2220/32Application in turbines in gas turbines
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/40Transmission of power
    • F05D2260/403Transmission of power through the shape of the drive components
    • F05D2260/4031Transmission of power through the shape of the drive components as in toothed gearing

Abstract

A stator vane arrangement comprises an electric motor 100 which acts through an inter engagement between gears 101 104 in order to provide for more accurate orientation and configuration of stator vanes. The stator vanes are secured to shafts 103 with a gear 104 engaging with ring gear 101 in order that rotation of the ring gear 101 causes a rotation of gear 104 and therefore adjustment in the orientation of the stator vane. Typically, adjustments in the stator vanes are co-ordinated together by ring gear 104 as part of a turbine engine. Each stator vane may be selectively associated or disassociated with the ring gear 104, in order that the vanes can be adjusted independently.

Description

A STATOR VANE ARRANGEMENT
The present invention relates to stator vane arrangements for turbine engines and more particularly to such engines used with regard to aircraft where high- pressure ratios are necessary.
Referring to Fig. 1, a gas turbine engine is generally indicated at 10 and comprises, in axial flow series, an air intake 11, a propulsive fan 12, an intermediate pressure compressor 13, a high pressure compressor 14, a combustor 15, a turbine arrangement comprising a high pressure turbine 16, an intermediate pressure turbine 17 and a low pressure turbine 18, and an exhaust nozzle 19.
The gas turbine engine 10 operates in a conventional manner so that air entering the intake 11 is accelerated by the fan 12 which produce two air flows: a first air flow into the intermediate pressure compressor 13 and a second air flow which provides propulsive thrust. The intermediate pressure compressor compresses the air flow directed into it before delivering that air to the high pressure compressor 14 where further compression takes place.
The compressed air exhausted from the high pressure compressor 14 is directed into the combustor 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive, the high, intermediate and low pressure turbines 16, 17 and 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low pressure turbines 16, 17 and 18 respectively drive the high and intermediate pressure compressors 14 and 13 and the fan 12 by suitable interconnecting shafts.
It will be understood from the above description
relative to Fig. 1 that control air fluid flow through a turbine engine is important in order to achieve desired operational performance and efficiency. One requirement to achieve these objectives is a highpressure ratio in the compressor side of an engine. Unfortunately, in order to achieve such high-pressure ratios it is a necessity to provide for greater airflow control.
One approach to airflow control is to provide variable geometry stator vanes between compressor stages, that is to say variable inlet guide vanes. Previously, such variable geometry may be achieved by mounting the stator vanes upon mountings whereby each vane can be rotated through a socalled unison ring as required. The unison ring rotates itself and in that rotation takes with it the individual stator vanes in order to alter their geometry.
A problem with mounting stator vanes in the way described above for variable geometry in assembly may be relatively complicated with less than desirable reliability, consistency and robustness. There may also be problems with mechanical hysteresis and a high component count.
Furthermore, it would be desirable to provide higher accuracy of stator vane control, possibly collectively and individually, and improved, higher resolution angular vane displacements.
Fig. 2 illustrates a typical known stator vane arrangement in which stator vanes 21 are mounted through stubs 22 such that via arms 23 adjustment of each stator vane 21 orientation can be performed through displacement of a unison ring 24. It will be appreciated that this unison ring 24 rotates about the central axis whereby through the arms 23 and stubs 22, all of the vanes 21 can be angularly adjusted and orientated as required by particular operational conditions. Nevertheless, it will be appreciated that individual orientation of vanes is not possible and, as indicated above, there can be a significant degree of mechanical hysteresis In accordance with the present invention there is provided a stator vane arrangement for a turbine engine, the arrangement comprising a stator vane coupled through inter engagement means with an electric motor, the stator vane being rotatable to vary its orientation and the electric motor allowing selective variation in that orientation by displacement of a shaft which forms at least part of the inter-engagement means.
Generally, displacement of the shaft will be angular or linear in order to drive rotation of the stator vane.
Normally, the shaft and the electric motor inter-engage by gear tooth engagement. Possibly, the electric motor acts to turn an orbital gear with the shaft including a planet gear engaging the orbital gear. Alternatively, the electric motor acts to turn a drive shaft which in turn rotates a spur gear.
Possibly, the electric motor is an electrical linear motor.
Possibly, the shaft is also associated with a regulating or governor unison ring. Advantageously, the unison ring is selectively associated or dis-associated with the shaft.
Possibly, the arrangement includes means to determine the orientation of the stator vane and means to adjust that orientation through control of the electric motor to the specific orientation desired.
Also, in accordance with the present invention there is provided a stator vane assembly including a plurality of stator vane arrangements as described above.
Possibly, the assembly includes a drive shaft for a plurality of stator vane arrangements positioned as respective arrangement stages in the assembly. Typically, each stage is coupled to the drive shaft by a gear tooth engagement.
Further in accordance with the present invention there is provided a turbine engine including an arrangement or assembly as described above.
Embodiments of the present invention will now be described by way of example and with reference to the accompanying drawings in which: Fig. 3 is a schematic illustration of a first embodiment of a stator vane arrangement; Fig. 4 is a schematic illustration of a second embodiment of a stator arrangement; and, Fig. 5 is a schematic illustration of a simple control regime for the present invention.
The present invention relates to stator vanes such as those illustrated in Fig. 1 as vanes 30, 31. These stator vanes 30, 31 act between compressor stages within a turbine engine in order to control air flow. It will be understood that the necessary geometry and configuration for the stator vanes 30, 31 in order to achieve optimum performance in terms of high pressure differentials may vary through the operational cycles of the engine. In such circumstances it is advantageous to allow for variation in stator vane geometry. As indicated previously, typically this variation was achieved through use of a unison ring which extends circumferentially about the engine and is coupled through appropriate mountings whereby the stator vanes 30, 31 can be adjusted as required. Such assembly of individual mountings upon the unison ring as well as rotation of that ring as indicated causes problems with respect to mechanical hysteresis limiting the accuracy with which the individual and collective stator vanes can be positioned for best performance, as well as increasing the component number resulting in assembly manufacturing difficulties.
The present invention provides a means by which individual as well as collective adjustment of stator vane position in an arrangement or assembly can be achieved. In short, an electric motor is utilised through an appropriate engagement with a shaft mounting for each individual stator vane in order to adjust that vane's position. Generally, the electric motor inter engages with the shaft through a gear tooth interlocking relationship. The electric motor drives rotation which then creates rotation of the shaft for appropriate vane adjustment. Figs. 2 and 3 respectively show alternative embodiments of the present invention.
Fig. 2 illustrates an electric motor 100 which is coupled to an orbital crown gear 101 which engages a planet gear 102 secured to a shaft 103. Normally, the electric motor 100 drives a unison ring 104 incorporating the orbital gear 101 or a segment of that orbital gear 101. In such circumstances rotation of the unison ring 104 causes rotation in the direction of arrowheads 105 which in turn displaces the orbital gear 101 such that through gear tooth inter-engagement with the planet gear 102 there is rotation of the shaft 103 and therefore the underlying stator vane secured through that shaft 103.
It will be appreciated normally there will be a relatively large number of stator vanes arranged in a side by side relationship about the circumference of a turbine engine. The unison ring 104 through respective orbital gear segments 101 engages each of these stator vanes through respective planet gears 102 and shafts 103. In such circumstances, reciprocal and mutual adjustments in the respective stator vanes is achieved through the rotation of the unison ring 104 caused by the electric motor 100. There is collective adjustment of the stator vane arrangement as required within a turbine engine in order to ensure that the assembly of stator vane arrangements as depicted in Fig. 2, that is to say orbital gear segment 101, planet gear 102 and shaft 103, are all orientated and configured for best airflow control within a turbine engine. Alternatively, a respective electric motor could be provided for a specific group or even individual stator vanes, whereby through appropriate control regimes, that particular group or stator vane may be adjusted by it's respective electric motor.
However, it will be understood that such an arrangement adds additional complexity (both mechanical and in terms of control) to an eventual stator vane assembly incorporating stator vane arrangements in accordance with the present invention, and this is contrary to one benefit of the present invention, that is to say reduced complexity and component count.
Normally, the accuracy with which the respective stator vanes can be adjusted in terms of orientation and configuration in accordance with an arrangement or assembly of the present invention is particularly dependent upon the stepping nature of the electric motor 100, that is to say the particular control of angular rotation and also the distribution, size and number of gear teeth in the respective orbital gear 101 and planet gear 102. It will also be understood that the unison ring 104 itself will generally be driven by a driving gear 106 engaging a peripheral gear 107 of the unison ring 104 in order to drive the rotation in the direction of arrowheads 105. In such circumstances the electric motor can be positioned towards the outside of a stator vane arrangement or assembly in accordance with the present invention. It will be understood with regard to a turbine engine, such positioning of the electric motor 100 at an outer location will allow easier accommodation. Furthermore, where desirable, it may be possible to provide several electric motors and drive gears 106 associated with respective peripheral gears 107 in order that through appropriate control mechanisms, respectively coarse and finite adjustments in stator vane position may be achieved. Thus, for example, a first electric motor may allow a more limited number of rotational steps and/or have coarser gear tooth engagement between its respective drive gear 106 and peripheral gear 107 such that under appropriate control, relatively rapid alterations in stator vane orientation may be achieved. A second electric motor with more finite incremental rotational steps and/or finer gear teeth engagement between its respective drive gear and peripheral gear may then be utilised for more finite adjustments of stator vane orientation.
As indicated above, individual stator vanes and/or groups of stator vanes may be independently adjusted. In such circumstances, each respective stator vane or group of stator vanes may be selectively disengaged from the unison ring 104 to allow respective drive to its orbital gear 101 engagement with planet gear 102 for specific adjustment of the associated stator vane. In such circumstances rather than all stator vanes being collectively adjusted throughout the circumference of a stator vane assembly, it will be understood that particular positions, such as top and/or bottom segments may be individually adjusted and therefore airflow is more appropriately controlled at the segments where there may be pylons or other structures which may cause non uniform air flow at those segments.
Fig. 3 provides a schematic illustration of a second embodiment of the present invention. As previously, a unison ring 214 is provided with an orbital gear segment 201 which inter engages with a planet gear 204 upon a shaft 203 associated with a stator vane. Drive for rotation in the direction of arrowheads 205 is achieved through a drive shaft 210 which in turn is rotated by an electrical linear motor 200 about that shaft 210. As the shaft 210 is displaced, either by axial shift rotation, the gear segments 211 at respective spaced positions engage their respective planet gear 204 to cause rotation of that planet gear 204 and therefore the shaft 203 in order to adjust the associated stator vane orientation. As indicated above, the planet gear 204 is also associated with the unison ring 214 through orbital gear segments 201 such that there is rotation in the direction of arrowheads 205 whereby similar orbital gear inter engagement with planet gear associations causes rotation and therefore adjustment of associated stator vanes in a stator vane assembly. As an alternative to axial shift by a linear motor 200 it will be understood that rotation in the manner of a worm gear may also cause the desired axial displacement.
Generally, as indicated above, a turbine engine will incorporate a number of compressor stages, and each compressor stage will have its own stator vane assembly.
Thus, the respective worm gears 211 will be associated with each such stator vane assembly in order that the electrical linear motor 200 through the drive shaft 210 can precipitate adjustments in the stator vane orientations as required at each compressor stage. It will be understood that the variations in the stator vane orientation is achieved through the drive shaft 210 and will be dependent upon the degree of accuracy with which displacement of the shaft 210 can be achieved and the nature of worm gear 211 to planet gear 204 engagement. Less accurate control of electrical linear motor rotation will result in a reduced accuracy with regard to stator vane orientation control. Similarly, coarser gear tooth engagement between the worm gears 211 and the planet gears 204 will similarly normally reduce the accuracy with which stator vane orientation can be set.
As indicated above it is possible to provide for differential stator vane orientation control dependent upon the rapidity with which such alterations are required.
Normally, for mechanical convenience, gear tooth engagement will be permanent such that if two or more electric motors with two or more different gear tooth engagement relationships are utilised, then the inactive combination will provide drag upon the active stator vane adjustment driving mechanism. Nevertheless, this drag may assist with respect to 'bounce" in such orientation adjustment and also act as a brake to provide enhanced stability with regard to maintaining such orientation, particularly at high air flow rates. Alternatively, other means for retaining position may be used particularly if there is loose or a disengageable gear combination is used.
As indicated above, normally all stator vanes in a stator vane assembly incorporating stator vane arrangements in accordance with the present invention will be adjusted in unity. This unity of adjustment will be achieved through the use of a unison ring with gear tooth engagement as described. Similarly through use of a driving shaft 210, adjustments in successive compressor stages in terms of their respective stator vane assemblies within a turbine engine can also be unified.
Fig. 4 provides a simple illustration of a control regime for a stator vane arrangement or assembly in accordance with the present invention. Thus, a control 30 is coupled to an electric motor 31 and a sensor 32. The sensor 32 in turn is connected to a stator vane assembly 33 and a turbine engine compressor stage 34. The orientation of the stator vanes in the assembly 33 and necessary parameters of the turbine engine 34 are determined by the sensor 32 and signals provided to the controller 30 indicative of their status. The controller 30 thereupon stimulates the electric motor 31 in order to alter as described above the orientation and configuration of the stator vanes in the assembly 33 in accordance with that necessary or desirable for air flow control requirements to achieve the desired performance in the turbine engine compressor 34.
The control regime utilised may be open loop or closed loop. Thus, the controller 30 may simply stimulate the electric motor 31 in order to precipitate the desired adjustments determined through the sensor 32 in an open loop regime. Alternatively, and preferably, a closed loop control regime is utilised in which by a combination of sensed parameter performance of the stator vane assembly 33 and turbine engine 34 is determined through the sensor 32.
Adjustments to the stator vane arrangement/assembly 33 are achieved through the electric motor 31 and repeated corrections occur until the desired operational performance is obtained. In order to perform this closed loop control regime, the controller 30 will normally periodically interrogate the sensor 32 rather than passively receive signals from that sensor 32. In these circumstances, through the controllability of an electric motor in order to determine stator vane configuration and orientation, more accurate positioning of stator vanes within a stator vane assembly can be achieved in order to provide better air flow control and therefore performance within a turbine engine.
Whilst endeavouring in the foregoing specification to draw attention to those features of the invention believed to be of particular importance it should be understood that the Applicant claims protection in respect of any patentable feature or combination of features hereinbefore referred to and/or shown in the drawings whether or not particular emphasis has been placed thereon.

Claims (16)

1. A stator vane arrangement for a turbine engine, the arrangement comprising a stator vane coupled through inter- engagement means with an electric motor, the stator vane being rotatable to vary its orientation and the electric motor allowing selective variation in that orientation by displacement of a shaft which forms at least part of the inter-engagement means.
2. An arrangement as claimed in claim 1 wherein displacement of the shaft is angular or linear in order to drive rotation of the stator vane.
3. An arrangement as claimed in claim 1 or claim 2 wherein interengagement means comprises a gear tooth engagement.
4. An arrangement as claimed in any of claims 1 to 3 wherein the electric motor acts to turn an orbital gear with the shaft including a planet gear engaging the orbital gear.
5. An arrangement as claimed in any of claims 1 to 3 wherein the electric motor acts to cause displacement of a drive shaft which in turn rotates a spur gear inter-engaging with the shaft.
6. An arrangement as claimed in claim 5 wherein the electric motor is an electrical linear motorfor axial displacement.
7. An arrangement as claimed in any preceding claim wherein the shaft is also associated with a regulating or governor unison ring.
S. An arrangement as claimed in claim 7 wherein the unison ring is selectively associated or dis-associated with the shaft.
9. An arrangement as claimed in any preceding claim wherein the arrangement includes means to determine the orientation of the stator vane and means to adjust that orientation through control of the electric motor to the specific orientation desired.
10. A stator vane arrangement substantially as hereinbefore described with reference to Fig. 3 or Fig. 4.
11. A stator vane assembly including a stator vane arrangement as claimed in any preceding claim.
12. An assembly as claimed in claim 11 wherein the assembly includes a drive shaft for a plurality of stator vane arrangements positioned as respective arrangement stages in the assembly.
13. An assembly as claimed in claim 13 wherein each stage is coupled to the drive shaft by a gear tooth engagement.
14. A stator vane assembly substantially as hereinbefore described with reference to the accompanying drawings.
15. A turbine engine including an arrangement as claimed in any of claims 1 to 9 or an assembly as claimed in any of claims 11 to 14.
16. Any novel subject matter or combination including novel subject matter disclosed herein, whether or not within the scope of or relating to the same invention as any of the preceding claims.
GB0401663A 2004-01-27 2004-01-27 Electrically actuated stator vane arrangement Withdrawn GB2410530A (en)

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Application Number Priority Date Filing Date Title
GB0401663A GB2410530A (en) 2004-01-27 2004-01-27 Electrically actuated stator vane arrangement

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GB2410530A true GB2410530A (en) 2005-08-03

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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006059999A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
EP1867877A1 (en) * 2006-06-16 2007-12-19 Ansaldo Energia S.P.A. Gas turbine compressor
FR2914944A1 (en) * 2007-04-13 2008-10-17 Snecma Sa High pressure compressor for e.g. jet prop engine of aircraft, has blades each including pivot connected to actuating ring by toothed wheel, where wheel is rotatably connected to pivot and engaged with corresponding gear teeth of ring
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8177493B2 (en) 2007-03-30 2012-05-15 Snecma Airtight external shroud for a turbomachine turbine wheel
WO2013087863A1 (en) * 2011-12-16 2013-06-20 Siemens Aktiengesellschaft Turbomachine and method for the operation thereof
CN103291383A (en) * 2013-06-26 2013-09-11 上海交通大学 Gas-compressor multistage stationary-blade regulating mechanism allowing gear transmission
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
WO2014044446A1 (en) * 2012-09-18 2014-03-27 Siemens Aktiengesellschaft Adjustable diffuser
US8905887B2 (en) 2012-02-13 2014-12-09 Rolls-Royce Plc Unison ring gear assembly
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
EP2557276A3 (en) * 2011-08-08 2017-04-05 General Electric Company Variable stator vane control system
EP3263907A1 (en) * 2016-06-27 2018-01-03 Rolls-Royce North American Technologies, Inc. Singular stator vane control
US10364826B2 (en) 2013-02-20 2019-07-30 Carrier Corporation Inlet guide vane mechanism
DE102007021483B4 (en) 2006-05-18 2022-08-04 Man Energy Solutions Se Control device for an exhaust gas turbocharger of a reciprocating piston internal combustion engine operated with heavy oil and method for ensuring the function of such a control device

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* Cited by examiner, † Cited by third party
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US8276362B2 (en) 2004-12-01 2012-10-02 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
WO2006059999A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
DE102007021483B4 (en) 2006-05-18 2022-08-04 Man Energy Solutions Se Control device for an exhaust gas turbocharger of a reciprocating piston internal combustion engine operated with heavy oil and method for ensuring the function of such a control device
US8075253B2 (en) 2006-06-16 2011-12-13 Ansaldo Energia S.P.A. Gas turbine compressor
EP1867877A1 (en) * 2006-06-16 2007-12-19 Ansaldo Energia S.P.A. Gas turbine compressor
WO2007144430A1 (en) * 2006-06-16 2007-12-21 Ansaldo Energia S.P.A. Gas turbine compressor
US8177493B2 (en) 2007-03-30 2012-05-15 Snecma Airtight external shroud for a turbomachine turbine wheel
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