EP3000984B1 - Dispositif de reglage d'aube directrice d'une turbine a gaz - Google Patents

Dispositif de reglage d'aube directrice d'une turbine a gaz Download PDF

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Publication number
EP3000984B1
EP3000984B1 EP15186174.7A EP15186174A EP3000984B1 EP 3000984 B1 EP3000984 B1 EP 3000984B1 EP 15186174 A EP15186174 A EP 15186174A EP 3000984 B1 EP3000984 B1 EP 3000984B1
Authority
EP
European Patent Office
Prior art keywords
guide vane
vane adjustment
bushing
spacer
housing
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.)
Active
Application number
EP15186174.7A
Other languages
German (de)
English (en)
Other versions
EP3000984A1 (fr
Inventor
Dr. Thomas KLAUKE
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 Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP3000984A1 publication Critical patent/EP3000984A1/fr
Application granted granted Critical
Publication of EP3000984B1 publication Critical patent/EP3000984B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/171—Steel alloys
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/174—Titanium alloys, e.g. TiAl
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/40—Organic materials
    • F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
    • F05D2300/434—Polyimides, e.g. AURUM
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced

Definitions

  • the invention relates to a guide vane adjusting device for a compressor or a turbine of a gas turbine according to the preamble of claim 1.
  • the invention relates to a Leitschaufelverstellvorraum for a compressor or a turbine having a plurality of each pivotable about a radial axis guide vanes, which are arranged in at least one radial plane.
  • the guide vanes thus form a disk-shaped arrangement, wherein upstream and downstream rotor blades are arranged in the flow direction, as is known from the prior art.
  • a Leitschaufelverstellring is provided, which is rotatable in the circumferential direction.
  • the vane adjusting ring is coupled to the respective vane via a lever mechanism such that upon rotation of the vane adjusting ring, the vanes are pivoted about their radial axes.
  • the vane adjusting ring is coupled to a suitable actuator.
  • the Leitschaufelverstellring which is rotatable for precise adjustment of the vanes by means of a drive mechanism in the circumferential direction relative to a housing is supported according to the prior art by means of spacers, which are arranged uniformly distributed around its circumference, against the housing and centered to this.
  • the housing heats up more than the Leitschaufelverstellring. This reduces the radial distance between the housing and the spacers connected to the vane adjusting ring.
  • a game or Provided cold gap which is present in the cold operating condition of the components.
  • both radial and tangential misalignments of the vane adjusting ring relative to the housing occur under certain operating conditions. This in turn leads to misalignment of the stator blades or vanes over the circumference of the vane assembly. This results in an incorrect setting of the vanes. Furthermore, the blade misalignment can lead to increased aerodynamic excitations of adjacent rotor and / or stator blades.
  • the actuating device By means of the actuating device, it is thus possible to adapt the angle of attack of the respective guide vane to the operating conditions of the compressor or of the turbine.
  • the disadvantage may arise that the adjustment of the guide vanes becomes imprecise due to thermal effects.
  • the GB 2 206 381 A shows a Leitschaufelverstellvorraum, wherein a housing member is arranged with a recess on the inner circumference of the Leitschaufelverstellrings. In the recess, an insert is used, which is made of polyimide. There is thus disclosed a fixedly installed plastic spacer which, when heated, reduces the gap between the vane adjusting ring and the housing when the vane adjusting ring heats up more than the housing.
  • US 4,925,364 A an adjustable spacer screw for a spacer.
  • two concentric with the shaft of the spacer arranged threaded bushes cooperate so that the spacer is adjustable in the radial direction.
  • the antirotation described in this document does not compensate for thermal expansion or contractions.
  • An adjustable support of a Leitschaufelverstellrings shows the GB 2 273 744 A ,
  • a support shoe is mounted by means of a shoe holder so that a radial adjustability is ensured.
  • the EP 2 481 892 A2 discloses a stop element of a synchronizing ring, which is mounted by means of a holder.
  • the invention has for its object to provide a Leitschaufelverstellvorraum for a compressor or a turbine of a gas turbine of the type mentioned above, which avoids the disadvantages of the prior art with a simple structure and simple, cost manufacturability and precise adjustment of the vanes, even with different thermal Expansions allows.
  • a sleeve made of a plastic is attached, on which the spacer is mounted.
  • the bush is made of a plastic material having a high thermal expansion coefficient. Due to the high thermal expansion, the spacer (centraliser) is moved radially outward by a greater amount during heating than the surrounding vane adjustment ring (unison ring). According to the invention, therefore, the radial expansion of the housing, which is stronger in comparison to the adjusting ring, can be compensated for during heating of the housing during operation by the spacer being moved radially outwards in accordance with this thermal expansion of the housing.
  • the amount of thermal expansion of the sleeve and thus the radial movement of the spacer can be adjusted according to the invention over the length of the socket, on the socket material and on the material of the spacer.
  • the solution according to the invention thus has the advantage that misalignments of the guide vanes or stator blades can be reduced or completely avoided. This leads to a more precise flow of both the vanes and the blades and thus to a lower fuel consumption. Furthermore, both the aerodynamic excitation of adjacent rotor and / or stator blades is reduced, and also reduces the adjustment of the adjustment by avoiding the jamming of the spacers on the housing.
  • the bushing is tube-like and that the spacer has a shaft which is fastened centrally in the bush.
  • the shaft can thus be stored at a suitable location in the socket, while the remaining length of the shaft in the socket in the radial direction (axial direction of the socket) can slide.
  • the shaft is attached to the radially outer portion of the sleeve, while the sleeve is preferably attached to a radially inner side of the Leitschaufelverstellrings to this or otherwise fixed.
  • the shaft is screwed to the socket. By a rotation of the shaft thus the gap between the spacer and the surface of the housing can be adjusted.
  • the thermal expansion coefficient of the sleeve is higher than a thermal expansion coefficient, the spacer and / or a thermal expansion coefficient of the housing.
  • the thermal expansion coefficient of the plastic bushing is at least twice as large as the thermal expansion coefficient of the vane adjusting ring and / or the spacer and / or the housing.
  • the bushing is preferably made of polyimide.
  • the gas turbine engine 10 is an example of a turbomachine to which the invention may find application. However, it will be understood from the following that the invention can be used with other turbomachinery as well.
  • the engine 10 is formed in a conventional manner and comprises in succession an air inlet 11, a fan 12 circulating in a housing, a medium pressure compressor 13, a high pressure compressor 14, combustion chambers 15, a high pressure turbine 16, a medium pressure turbine 17 and a low pressure turbine 18 and an exhaust nozzle 19, which are all arranged around a central engine axis 1.
  • the intermediate-pressure compressor 13 and the high-pressure compressor 14 each comprise a plurality of stages, each of which has a circumferentially extending array of fixed stationary vanes 20, commonly referred to as stator vanes, extending radially inward from the engine casing 21 in an annular flow passage through the compressors 13, 14 project.
  • the compressors further include an array of compressor blades 22 projecting radially outwardly from a rotatable drum or disc 26 coupled to hubs 27 of high pressure turbine 16 and mid pressure turbine 17, respectively.
  • the turbine sections 16, 17, 18 have similar stages, comprising an array of vanes 23 projecting radially inward from the housing 21 into the annular flow passage through the turbines 16, 17, 18, and a subsequent array of turbine blades 24 following projecting externally from a rotatable hub 27.
  • the compressor drum or compressor disk 26 and the vanes 22 disposed thereon and the turbine rotor hub 27 and the turbine blades 24 disposed thereon rotate about the engine axis 1 during operation.
  • the Fig. 2 shows a partial perspective view of a compressor with multiple rows of adjustable vanes 20, between each of which compressor blades 22 are arranged.
  • the individual vanes 20 are each pivotable about a radial axis 33. They are connected to a lever 34 which is rotatably coupled at its opposite end portion with a Leitschaufelverstellring 29. By a rotation of the Leitschaufelverstellrings 29 in the circumferential direction is a pivoting of the individual lever 34. This causes a rotation of the vanes 20 about the respective axis 33 causes.
  • An actuating device which is designed for example as a piston-cylinder unit is coupled via a coupling rod (not shown) with a crankshaft 36, as in Fig. 3 is shown.
  • the crankshaft 36 is supported by bearings 37.
  • the crankshaft 36 is further coupled by means of coupling rods 35 with the Leitschaufelverstellringen 29.
  • An actuation of the actuating device thus leads to a rotation or pivoting of the crankshaft 36, which in turn leads to a rotation of the respective Leitschaufelverstellrings 29, since the crankshaft 36 is connected via a coupling rod 35 with the Leitschaufelverstellring 29.
  • the Fig. 3 further shows a plurality of spacers 30 distributed around the circumference, which (see also the below-described FIGS Fig. 4 ) have a shaft 32 which is adjustably mounted on the Leitschaufelverstellring 29.
  • the spacer abuts the surface of the housing 38 and is moved together with the Leitschaufelverstellring 29 in the circumferential direction.
  • the spacer centers the vane adjusting ring 29 in the radial direction relative to the housing 38 Fig. 3 has the housing 38 at the areas where the spacer 30 abuts, suitable pedestals or contact surfaces or the like.
  • the Fig. 4 shows an embodiment of the inventive solution in detail in a sectional view of a radial plane.
  • the housing 38 is shown only schematically and has over the spacer 30 an oversized for the purpose of clarity on distance.
  • a made of a plastic material bushing 31 is mounted at the Leitschaufelverstellring 29 .
  • This bush is in the form of a sleeve and has a central recess in which the shaft 32 of the spacer 30 is mounted is.
  • the bearing of the shaft 32 takes place at a radially outer region of the bushing 31 by means of a thread 39. By rotation of the shaft 32, it is thus possible to adjust the radial position of the spacer 30.
  • the housing expands the example shown radially by 0.3 mm.
  • the Fig. 5 shows a further embodiment, wherein like parts are provided with the same reference numerals.
  • the shank 32 has a thread at its end and is adjustably secured by means of a nut 40, which is connected to the bush 31.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (10)

  1. Dispositif de positionnement d'aubes directrices d'une turbine à gaz comprenant une pluralité d'aubes directrices (20) pouvant respectivement pivoter autour d'un axe radial (33), lesquelles sont disposées dans au moins un plan radial, et comprenant au moins un anneau de positionnement d'aubes directrices (29), lequel est couplé avec les aubes directrices (20) respectives et peut être amené en rotation dans la direction périphérique au moyen d'au moins un dispositif d'actionnement, l'anneau de positionnement d'aubes directrices (29) étant soutenu dans le sens radial contre un boîtier (38) centré au moyen de plusieurs entretoises (30) distribuées autour du pourtour et supportées contre l'anneau de positionnement d'aubes directrices (29), caractérisé en ce qu'une douille (31), contre laquelle est supportée l'entretoise (30), fabriquée en une matière plastique ayant un coefficient de dilatation thermique supérieur à un coefficient de dilatation thermique de l'anneau de positionnement d'aubes directrices (29) est fixée à l'anneau de positionnement d'aubes directrices (29) pour chaque entretoise (30), la douille (31) étant configurée en forme de tube et l'entretoise possédant une tige (32) fixée de manière centrée dans la douille (31).
  2. Dispositif de positionnement d'aubes directrices selon la revendication 1, caractérisé en ce que la tige (32) est fixée au niveau de la zone radialement extérieure de la douille (31).
  3. Dispositif de positionnement d'aubes directrices selon l'une des revendications 1 ou 2, caractérisé en ce que la tige (32) est vissée avec la douille (31).
  4. Dispositif de positionnement d'aubes directrices selon l'une des revendications 1 à 3, caractérisé en ce que la douille (31) est fixée à l'anneau de positionnement d'aubes directrices (29) au niveau de son côté intérieur dans le sens radial.
  5. Dispositif de positionnement d'aubes directrices selon l'une des revendications 1 à 4, caractérisé en ce que la tige (32) est réglable dans la direction radiale par rapport à la douille (31).
  6. Dispositif de positionnement d'aubes directrices selon l'une des revendications 1 à 5, caractérisé en ce que la tige (32) est fabriquée dans un matériau métallique ayant un coefficient de dilatation thermique similaire ou identique à celui du boîtier (38) et/ou de l'anneau de positionnement d'aubes directrices (29).
  7. Dispositif de positionnement d'aubes directrices selon l'une des revendications précédentes, caractérisé en ce que le coefficient de dilatation thermique de la douille (31) est supérieur à un coefficient de dilatation thermique de l'entretoise (30) et/ou du boîtier (38).
  8. Dispositif de positionnement d'aubes directrices selon la revendication 7, caractérisé en ce que le coefficient de dilatation thermique de la douille (31) est au moins égal au double du coefficient de dilatation thermique de l'anneau de positionnement d'aubes directrices (29) et/ou de l'entretoise (30) et/ou du boîtier (38).
  9. Dispositif de positionnement d'aubes directrices selon l'une des revendications précédentes, caractérisé en ce que la douille (31) est fabriquée en polyimide.
  10. Dispositif de positionnement d'aubes directrices selon l'une des revendications précédentes, caractérisé en ce que l'anneau de positionnement d'aubes directrices (29) et l'entretoise (30) et le boîtier (38) sont fabriqués dans un alliage d'acier à haute résistance ou un alliage de titane.
EP15186174.7A 2014-09-26 2015-09-22 Dispositif de reglage d'aube directrice d'une turbine a gaz Active EP3000984B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102014219552.7A DE102014219552A1 (de) 2014-09-26 2014-09-26 Leitschaufelverstellvorrichtung einer Gasturbine

Publications (2)

Publication Number Publication Date
EP3000984A1 EP3000984A1 (fr) 2016-03-30
EP3000984B1 true EP3000984B1 (fr) 2019-11-20

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EP15186174.7A Active EP3000984B1 (fr) 2014-09-26 2015-09-22 Dispositif de reglage d'aube directrice d'une turbine a gaz

Country Status (3)

Country Link
US (1) US9976438B2 (fr)
EP (1) EP3000984B1 (fr)
DE (1) DE102014219552A1 (fr)

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FR3029562B1 (fr) * 2014-12-09 2016-12-09 Snecma Anneau de commande d’un etage d’aubes a calage variable pour une turbomachine
GB2557565A (en) * 2016-07-18 2018-06-27 Rolls Royce Plc Variable stator vane mechanism
BE1024523B1 (fr) 2016-08-30 2018-03-29 Safran Aero Boosters S.A. Stator a aubes ajustables pour compresseur de turbomachine axiale
DE102016122639A1 (de) 2016-11-23 2018-05-24 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelbaugruppe mit Ausgleichseinrichtung
DE102016122640A1 (de) 2016-11-23 2018-05-24 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelbaugruppe mit Ausgleichseinrichtung
EP3530764B1 (fr) 2018-02-26 2020-08-26 Roller Bearing Company of America, Inc. Materiau composite a base d'aluminide de titane auto-lubrifiant
US10487681B1 (en) 2018-08-07 2019-11-26 Eyal Ezra Variable geometry turbocharger adjustment device
CN109129250B (zh) * 2018-10-18 2020-05-19 北京动力机械研究所 一种涡轮发动机导向器流通能力调节工装
CN110617117B (zh) * 2019-08-02 2022-04-08 中国航发贵阳发动机设计研究所 一种涡轮导向器喉道面积调节方法
CN112282923B (zh) * 2020-11-12 2021-11-16 湖南路捷道夫涡轮增压***有限公司 一种可变截面涡轮增压器
BR112023026171A2 (pt) * 2021-06-30 2024-03-05 Saint Gobain Performance Plastics Corp Casquilho de cerâmica variável de palheta do estator

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US20160090856A1 (en) 2016-03-31
EP3000984A1 (fr) 2016-03-30
DE102014219552A1 (de) 2016-03-31
US9976438B2 (en) 2018-05-22

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