EP2703606A1 - Systèmes et procédé permettant de contrôler les aubes de stator dans des turbine à gaz - Google Patents

Systèmes et procédé permettant de contrôler les aubes de stator dans des turbine à gaz Download PDF

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Publication number
EP2703606A1
EP2703606A1 EP13180525.1A EP13180525A EP2703606A1 EP 2703606 A1 EP2703606 A1 EP 2703606A1 EP 13180525 A EP13180525 A EP 13180525A EP 2703606 A1 EP2703606 A1 EP 2703606A1
Authority
EP
European Patent Office
Prior art keywords
unison ring
variable stator
stator vanes
unison
ring
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Withdrawn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
EP13180525.1A
Other languages
German (de)
English (en)
Inventor
Harry McFarland Jarrett Jr.
Jayakrishna Velampati
Andrew John Lammas
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2703606A1 publication Critical patent/EP2703606A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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

Definitions

  • Embodiments of the present application relate generally to gas turbine engines and more particularly to systems and methods to control variable stator vanes in gas turbine engines.
  • a turbine rotor is turned at high speeds by a turbine so that air is continuously induced into the compressor.
  • the air is accelerated by rotating blades and swept rearwards onto adjacent rows of variable stator vanes.
  • Each rotor blade/variable stator vane stage increases the pressure of the air.
  • variable stator vanes In addition to translating the kinetic energy of the air into pressure, the variable stator vanes also serve to correct the deflection given to the air by the rotor blades and to present the air at the correct angle to the next stage of rotor blades. Pivoting the variable stator vanes permits the flow capacity of the compressor or turbine to be changed, thereby ensuring that the flow capacity is always at an optimum value for the particular operating conditions of the gas turbine engine. Accordingly, there is a need to control the angle of the variable stator vanes.
  • a variable stator vanes control mechanism for a gas turbine engine.
  • the control mechanism includes a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring.
  • the control mechanism also includes a linkage in operative communication with the first unison ring and a second unison ring such that movement of the first unison ring drives the second unison ring.
  • a method to control variable stator vanes in a gas turbine engine includes actuating a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring.
  • the method also includes driving a linkage in operative communication with the first unison ring and a second unison ring such that movement of the first unison ring drives the second unison ring.
  • a variable stator vanes control mechanism for a gas turbine engine.
  • the gas turbine engine may include a compressor having a compressor casing.
  • the control mechanism may include a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring about the compressor casing.
  • the control mechanism may also include a linkage in operative communication with the first unison ring and a second unison ring such that movement of the first unison ring about the compressor casing drives the second unison ring about the compressor casing.
  • Illustrative embodiments are directed to, among other things, systems and methods to control variable stator vanes in gas turbine engines.
  • Fig. 1 shows a schematic view of a gas turbine engine 10 as may be used herein.
  • the gas turbine engine 10 may include a compressor 12.
  • the compressor 12 compresses an incoming flow of air 14.
  • the compressor 12 delivers the compressed flow of air 14 to a combustor 16.
  • the combustor 16 mixes the compressed flow of air 14 with a pressurized flow of fuel 18 and ignites the mixture to create a flow of combustion gases 20.
  • the gas turbine engine 10 may include any number of combustors 16.
  • the flow of combustion gases 20 is in turn delivered to a turbine 22.
  • the flow of combustion gases 20 drives the turbine 22 so as to produce mechanical work.
  • the mechanical work produced in the turbine 22 drives the compressor 12 via a shaft 24 and an external load 26 such as an electrical generator and the like.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
  • the gas turbine engine 10 may have different configurations and may use other types of components.
  • gas turbine engines also may be used herein.
  • Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
  • Fig. 2 depicts a section of the compressor 12 of the gas turbine engine 10 of Fig. 1 .
  • the compressor 12 includes a tubular casing 28.
  • Sets of variable stator vanes 30 are mounted within the casing 28 circumferentially about the central axis of the compressor 12.
  • Corresponding sets of rotor vanes 32 are mounted downstream of each set of variable stator vanes 30.
  • Each variable stator vane 30 terminates at the casing 28 in a stem 34.
  • the stem 34 is rotatable in a bush bearing 36 on the outside of the casing 28.
  • each set of variable stator vanes 30 Located externally of the casing 28 and adjacent to each set of variable stator vanes 30 are unison rings 38 extending circumferentially about the casing 28.
  • the vane stems 34 of each set of variable stator vanes 30 are connected to the corresponding unison ring 38 by a respective lever 40.
  • One end of the lever 40 is clamped to the end of the vane stem 34 by a bolt 42 so that there is no relative movement between the stem 34 and the lever 40.
  • the other end of the lever 40 is connected to the unison ring 38 by a pin 44 rotatable in a bush bearing located in the unison ring 38.
  • the unison ring 38 is arranged so that it may be rotated about the central axis of the compressor section 12 in either direction of arrow 9. Consequently, rotation of the unison ring 38 causes rotation of each variable stator vane 30 via the levers 40 and thus enables the variable stator vanes 30 to assume required angles of incidence to the incoming air.
  • Figs. 3 and 4 depict an embodiment of a variable stator vanes control mechanism 100.
  • the variable stator vanes control mechanism 100 enables the transfer of motion from one unison ring to another using only one actuator.
  • the variable stator vanes control mechanism 100 may include a moveable actuation rod 102.
  • the moveable actuation rod 102 may be in operative communication with a first unison ring 104 such that movement of the actuation rod 102 drives the first unison ring 104 in a first direction 106 about the central axis of the casing 108.
  • Rotation of the first unison ring 104 causes rotation of each variable stator vane 110 connected to the first unison ring by the levers 112.
  • the variable stator vanes control mechanism 100 may also include a bell crank mechanism 114.
  • the bell crank mechanism 114 may be in operative communication with the first unison ring 104.
  • the bell crank mechanism 114 may also be in operative communication with a second unison ring 116 such that movement of the first unison ring 104 in the first direction 106 translates movement, by way of the bell crank mechanism 114, to the second unison ring 116 in a second direction 118 that is opposite the first direction 106 of the first unison ring 104.
  • Rotation of the second unison ring 116 causes rotation of each variable stator vane 110 connected to the second unison ring 116 by the levers 112.
  • the bell crank mechanism 114 may include a pivot 120, a first turnbuckle 122, and a second turnbuckle 124.
  • the first turnbuckle 122 operatively connects the first unison ring 104 to the pivot 120.
  • the second turnbuckle 124 operatively connects the second unison ring 116 to the pivot 120.
  • the first turnbuckle 122 and the second turnbuckle 124 are attached to the pivot 120 such that rotation of the pivot 120 drives the first turnbuckle 122 and the second turnbuckle 124 in opposite directions.
  • the movable actuator rod 102 actuates the first unison ring 104 thereby rotating the first unison ring 104 in the first direction 106 about the casing 108.
  • the first unison ring 104 rotates about the casing 108 in the first direction 106, it drives the first turnbuckle 122.
  • the first turnbuckle 122 then applies a pivoting force to the pivot 120.
  • the pivoting of the pivot 120 causes the second turnbuckle 124 to drives the second unison ring 116 thereby causing the second unison ring 116 to rotate in the second direction 118 about the casing 108.
  • the second direction 118 and the first direction 106 are opposite of each other.
  • the rotation of the first unison ring 104 and the second unison ring 116 causes the respective variable stator vanes 110 attached to each unison ring to rotate in opposite directions due to the movement of the levers 112. Accordingly, the angle of the variable stator vanes 110 may be adjusted with the variable stator vanes control mechanism 100.
  • the first direction 106 and the second direction 118 are relative to each other. Accordingly, the first direction 106 and the second direction 118 may be any direction about the casing 108.
  • the moveable actuation rod 102 may be in operative communication with the first unison ring 104, the second unison ring 106, or the bell crank mechanism 114.
  • the bell crank mechanism 114 may be at least partially secured to the casing 108 of the compressor. In other embodiments, the moveable actuator rod 102 may be at least partially secured to the casing 108 of the compressor. One will appreciate, however, that the bell crank mechanism 114 and the moveable actuator rod 102 may be at least partially secured at any location on or about the gas turbine engine.
  • a relative movement between the first unison ring 104 and the second unison ring 116 and the angle of the variable stator vanes 110 may be adjusted by varying the dimensions of the pivot 12, the first turnbuckle 122, and the second turnbuckle 124. Moreover, the angle of the variable stator vanes 110 may be varied by varying the length of the levers 112.
  • variable stator vanes control mechanism 100 may enable the transfer of motion from one unison ring to another using only one actuator.
  • the first unison ring and the second unison ring may rotate in the same direction.
  • the bell crank mechanism 114 may include a pivot 120, a first turnbuckle 122, and a second turnbuckle 124.
  • the first turnbuckle 122 operatively connects the first unison ring 104 to the pivot 120.
  • the second turnbuckle 124 operatively connects the second unison ring 116 to the pivot 120.
  • the first turnbuckle 122 and the second turnbuckle 124 may be attached to the pivot 120 such that rotation of the pivot 120 drives the first turnbuckle 122 and the second turnbuckle 124 in the same direction. Accordingly, in operation, the movable actuator rod actuates the first unison ring 104 thereby rotating the first unison ring 104 in a first direction 106 about the casing 108. As the first unison ring 104 rotates about the casing 108 in the first direction 106, it drives the first turnbuckle 122. The first turnbuckle 122 then applies a pivoting force to the pivot 120.
  • the pivoting of the pivot 120 causes the second turnbuckle 124 to drive the second unison ring 116 thereby causing the second unison ring 116 to rotate in the first direction about the casing 108.
  • the rotation of the first unison ring 104 and the second unison ring 116 causes the respective variable stator vanes 110 attached to each unison ring to rotate in the same direction due to the movement of the levers 112.
  • the embodiments as depicted in Figs. 3-5 may include one or more additional unison rings in operative communication with the bell crank mechanism such that movement of the first unison ring in the first direction drives the one or more additional unison rings in the first or second direction respectively.
  • Fig. 6 depicts an embodiment of a variable stator vanes control mechanism 200.
  • the variable stator vanes control mechanism 200 enables the transfer of motion from one unison ring to another using only one actuator.
  • the variable stator vanes control mechanism 200 may include a moveable actuation rod 202 in operative communication with a first unison ring 204.
  • the moveable actuation rod 202 may actuate the first unison ring 204.
  • the variable stator vanes control mechanism 200 may also include a linkage 206 in operative communication with the first unison ring 204 and a second unison ring 208 such that movement of the first unison ring 204 drives the second unison ring 208.
  • This embodiment is similar to the previously described embodiments, except that it does not include the bell crank mechanism. Instead, this embodiment provides a direct linkage 206 between the unison rings 204 and 208. Accordingly, in this embodiment, the linkage 206 translates movement from the actuated first unison ring 204 to the second unison ring 208 in the same direction. In certain aspects, the linkage 206 may pull the second unison ring 208. In other aspects, the linkage 206 may push the second unison ring 208.
  • the movable actuator rod 202 is attached to the casing 210 and actuates the first unison ring 204 thereby rotating the first unison ring 204 about the casing 210.
  • the linkage 206 may be a turnbuckle.
  • the linkage 206 then applies a force to the second unison ring 208 thereby causing the second unison ring 208 to rotate about the casing 210.
  • the first unison ring 204 and the second unison ring 206 rotate in the same direction about the casing 210.
  • the rotation of the first unison ring 204 and the second unison ring 206 causes the respective variable stator vanes attached to each unison ring by way of the respective levers 212 to rotate. Accordingly, the angle of the variable stator vanes may be adjusted with the variable stator vanes control mechanism 200.
  • the embodiment as depicted in Fig 6 may include one or more additional unison rings in operative communication with one or more additional linkages such that movement of the first unison ring in the first direction drives the one or more additional unison rings respectively.
  • Figs. 7 and 8 depict an embodiment of a variable stator vanes control mechanism 300.
  • the variable stator vanes control mechanism 300 enables the actuation of multiple unison rings using only one actuator.
  • the variable stator vanes control mechanism 300 may include a moveable actuation rod 302.
  • the moveable actuation rod 302 may be in operative communication with a torque shaft 304 such that the movable actuation rod 302 rotates the torque shaft 304.
  • a first unison ring 306 may be in operative communication with the torque shaft 304 via a turnbuckle 305 such that rotation of the torque shaft 304 drives the first unison ring 306 in a first direction 308 about a central axis of the casing 310.
  • Rotation of the first unison ring 306 causes rotation of each variable stator vane 312 connected to the first unison 306 ring by the levers 314.
  • a second unison ring 316 may be in operative communication with the torque shaft 304 via a turnbuckle 307 such that rotation of the torque shaft 304 drives the second unison ring 316 in a second direction 318 about the central axis of the casing 310. Rotation of the second unison ring 316 causes rotation of each variable stator vane 312 connected to the second unison 316 ring by the levers 314.
  • the first direction 308 and the second direction 318 are relative.
  • the first direction 308 and the second direction 318 may be the same direction or different directions about the casing 310.
  • the turnbuckles 305 and 307 may be attached on the same side of the torque shaft.
  • the turnbuckles 305 and 307 may be attached on opposite sides of the torque shaft.
  • the first direction 308 and the second direction 318 may be any direction about the casing 310.
  • the moveable actuation rod 302 may be in operative communication with the first unison ring 306, the second unison ring 316, or the torque shaft 304.
  • the movable actuator rod 302 is attached to the casing 310 and actuates the torque shaft 304 thereby rotating the torque shaft 304.
  • the turnbuckle 305 connects the first unison ring 306 to the torque shaft 304
  • the turnbuckle 307 connects the second unison ring 316 to the torque shaft 304.
  • the turnbuckles 305 and 307 drive the first unison ring 306 and the second unison ring 316 about the compressor casing 310.
  • the rotation of the first unison ring 306 and the second unison ring 316 causes the respective variable stator vanes attached to each unison ring by the respective levers 314 to rotate. Accordingly, the angle of the variable stator vanes may be adjusted with the variable stator vanes control mechanism 300.
  • one or more additional unison rings may be in communication with the torque shaft by one or more respective turnbuckles.
  • the moveable actuator rod 302 may be at least partially secured to the casing 310 of the compressor.
  • the moveable actuator rod 302 may be at least partially secured at any location on or about the gas turbine engine.
  • the torque shaft 304 may be rotatably supported about the casing 310 of the compressor by a support structure 320.
  • the support structure 320 may be any configuration that facilitates the rotation of the torque shaft about the compressor casing 310.
  • Figs. 9 and 10 depict an embodiment of a variable stator vanes control mechanism 400.
  • the variable stator vanes control mechanism 400 enables the actuation of two variable stator vanes stages using only one actuator and a system of gears.
  • the actuator engages the gear system which engages the two stages of variable stator vanes thereby adjusting the variable stator vanes.
  • the variable stator vanes control mechanism 400 may include a moveable actuation rod 402.
  • the moveable actuation rod 402 may be attached to the casing 404 or any other location on or about the gas turbine engine.
  • the moveable actuation rod 402 may also be attached to a gear ring 406.
  • the gear ring 406 may be disposed about the compressor casing 404 such that the gear ring 406 rotates about the compressor casing 404 when actuated by the moveable actuation rod 402.
  • a rub block 408 may be disposed between the casing 404 and the gear ring 406 to facilitate smooth rotation of the gear ring 406 about the casing 404.
  • variable stator vanes 410 may be disposed on a first side 412 and a second side 414 of the gear ring 406.
  • the variable stator vanes 410 form a first compressor stage and a second compressor stage respectively on each side of the gear ring 406.
  • the variable stator vanes 410 may include gear stems 416.
  • the gear stems 416 may be in operative communication with the gear ring 406.
  • the movable actuation rod 402 is attached to the casing 404 and actuates the gear ring 406 thereby rotating the gear ring 406 about the casing 404.
  • the gear stems 416 of the variable stator vanes 410 are in operative communication with the gear ring 406 such that as the gear ring 406 rotates about the casing 404, the gear stems 416 of the variable stator vanes 410 are rotated. The rotation of the gear stems 416 adjusts the angle of the variable stator vanes 410.
  • the rotation of the variable stator vanes 410 may be controlled by the addition of gears or gear train type mechanisms operatively disposed between the gear stems and the gear ring.
  • additional gears 418 are operatively disposed between the gear ring 406 and the respective gear stems 416 of the first compressor stage.
  • the addition of additional gears 418 enables the first compressor stage of variable stator vanes and the second compressor stage of variable stator vanes to rotate in the same direction.
  • the gear stems 416 of the variable stator vanes 410 were in direct communication with the gear ring 406, the variable stator vanes 410 would rotate in opposite directions.
  • gear ratio and the number of gear teeth may be adjusted to control the schedule between variable stator vane stages.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13180525.1A 2012-08-29 2013-08-15 Systèmes et procédé permettant de contrôler les aubes de stator dans des turbine à gaz Withdrawn EP2703606A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/598,059 US20140064911A1 (en) 2012-08-29 2012-08-29 Systems and Methods to Control Variable Stator Vanes in Gas Turbine Engines

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EP2703606A1 true EP2703606A1 (fr) 2014-03-05

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EP13180525.1A Withdrawn EP2703606A1 (fr) 2012-08-29 2013-08-15 Systèmes et procédé permettant de contrôler les aubes de stator dans des turbine à gaz

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US (1) US20140064911A1 (fr)
EP (1) EP2703606A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2519551A (en) * 2013-10-24 2015-04-29 Rolls Royce Deutschland A variable stator vane arrangement
EP2949878A1 (fr) * 2014-05-28 2015-12-02 Rolls-Royce Deutschland Ltd & Co KG Ensemble d'aube de stator variable
EP3336319A1 (fr) * 2016-12-19 2018-06-20 Rolls-Royce Deutschland Ltd & Co KG Dispositif de réglage destiné au réglage d'aubes directrices multiples d'un groupe propulseur

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10415596B2 (en) * 2016-03-24 2019-09-17 United Technologies Corporation Electric actuation for variable vanes

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EP1207271A2 (fr) * 2000-11-08 2002-05-22 General Electric Company Arbre d'actionnement composé
EP1724472A2 (fr) * 2005-05-17 2006-11-22 Snecma Système de commande d'étages d'aubes de stator à angle de calage variable de turbomachine
EP1724471A2 (fr) * 2005-05-17 2006-11-22 Snecma Système de commande d'étages d'aubes de stator à angle de calage variable de turbomachine

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EP1207271A2 (fr) * 2000-11-08 2002-05-22 General Electric Company Arbre d'actionnement composé
EP1724472A2 (fr) * 2005-05-17 2006-11-22 Snecma Système de commande d'étages d'aubes de stator à angle de calage variable de turbomachine
EP1724471A2 (fr) * 2005-05-17 2006-11-22 Snecma Système de commande d'étages d'aubes de stator à angle de calage variable de turbomachine

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2519551A (en) * 2013-10-24 2015-04-29 Rolls Royce Deutschland A variable stator vane arrangement
EP2949878A1 (fr) * 2014-05-28 2015-12-02 Rolls-Royce Deutschland Ltd & Co KG Ensemble d'aube de stator variable
US9890656B2 (en) 2014-05-28 2018-02-13 Rolls-Royce Deutschland Ltd & Co Kg Variable stator vane arrangement
EP3336319A1 (fr) * 2016-12-19 2018-06-20 Rolls-Royce Deutschland Ltd & Co KG Dispositif de réglage destiné au réglage d'aubes directrices multiples d'un groupe propulseur
EP3530885A1 (fr) * 2016-12-19 2019-08-28 Rolls-Royce Deutschland Ltd & Co KG Dispositif de réglage destiné au réglage d'une pluralité d'aubes directrices d'un groupe propulseur
US10578029B2 (en) 2016-12-19 2020-03-03 Rolls-Royce Deutschland Ltd & Co Kg Adjustment device for adjusting several guide vanes of an engine

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