EP2362070A1 - Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine - Google Patents

Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine Download PDF

Info

Publication number
EP2362070A1
EP2362070A1 EP10001722A EP10001722A EP2362070A1 EP 2362070 A1 EP2362070 A1 EP 2362070A1 EP 10001722 A EP10001722 A EP 10001722A EP 10001722 A EP10001722 A EP 10001722A EP 2362070 A1 EP2362070 A1 EP 2362070A1
Authority
EP
European Patent Office
Prior art keywords
adjusting ring
drive device
blades
blade carrier
adjusting
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Withdrawn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
EP10001722A
Other languages
German (de)
English (en)
Inventor
Markus Hofmann
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP10001722A priority Critical patent/EP2362070A1/fr
Priority to JP2012553285A priority patent/JP2013519836A/ja
Priority to RU2012139958/06A priority patent/RU2012139958A/ru
Priority to US13/579,612 priority patent/US20120308364A1/en
Priority to PCT/EP2011/052188 priority patent/WO2011101334A1/fr
Priority to CN2011800098146A priority patent/CN102762818A/zh
Priority to EP11704062A priority patent/EP2536922A1/fr
Publication of EP2362070A1 publication Critical patent/EP2362070A1/fr
Withdrawn legal-status Critical Current

Links

Images

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

Definitions

  • the invention relates to a drive device for pivoting adjustable blades of a turbomachine, comprising an annular flow channel section enclosed by a blade carrier, which extends along the central axis of the blade carrier and in which blades are provided in a radiating manner to form a ring, wherein the blades each pivot about their longitudinal axis and each having a at least in the blade carrier extending pins which are coupled to a rotatable adjusting ring in the circumferential direction.
  • a device of such type is for example from the US 5,549,448 out.
  • a concentric to the central axis of the compressor collar surrounds the inner housing.
  • Each blade of the blade ring rotatable about its longitudinal axis has a pin which extends through the blade carrier and which is connected to the adjusting ring outside the housing via a pivot lever.
  • the adjusting ring is rotatable in the circumferential direction.
  • the rotation of the adjusting ring, the pivot lever are moved, whereby the blades are pivoted about their respective longitudinal axis.
  • the adjusting ring is moved by a drive in the circumferential direction, which also supports the adjusting ring at the same time.
  • the collars are also extremely massive.
  • temperature differences between the adjusting ring and the blade carrier have an influence on the angle of attack of the compressor blades in the flow channel. These temperature differences can lead to unevenly set angles of attack of the blades of the blade ring, so that it must always be ensured that the adjusting ring and the blade carrier are mounted coaxially or concentrically to a common central axis.
  • the tangential introduction of force via push rods can cause an equally disadvantageous decentering of the adjusting ring.
  • the object of the present invention is to provide a wear-free, reliable drive device for temperature-independent adjustment of itself radially in an annular channel extending, rotatable about their respective longitudinal axis blades.
  • the generic drive device for pivoting adjustable blades of a turbomachine comprises a blade carrier, which encloses an annular flow channel section.
  • the flow channel section extends along the centerline of the blade carrier.
  • the blades each have a pin which extends at least into the blade carrier and which are respectively coupled to at least one adjusting ring rotatable in the circumferential direction, which is drivable via at least one motor.
  • the drive shaft of the motor or the motors is or are coupled to the adjusting ring or the adjusting rings via a toothed drive.
  • the invention is directed from previous designs, in which the rotation of the adjusting ring is effected by tangentially engaging push rods.
  • the introduction of force for rotating the adjusting ring takes place according to the invention instead of via push rods via at least one pinion.
  • the toothed drive is preferably designed as a crown gear or a bevel gear, wherein the drive shaft of the motor are simultaneously formed as the drive shaft of the pinion and the adjusting ring as the output shaft of the pinion. This makes it possible to obtain a much improved application of force for rotating the adjusting ring, which reduces the unwanted decentering of the adjusting ring.
  • some motors are preferably distributed over the circumference of the adjusting ring, which each have a Pinion, which are all identical, are coupled to the collar. To adjust the motors are of course controlled synchronously. All blades are then pivoted from the collar to the desired position.
  • This type of force application offers itself regardless of the type of coupling pin and collar. It can therefore be used for a lever coupling, but also for a gear-like coupling.
  • one of the pins may be part of one of the drive shafts, so that the axis of rotation of drive shaft and coincides with the axis of rotation of the respective pin.
  • drive shaft and pin can be rigidly connected together.
  • the blade corresponding to the respective pin is directly drivable by the motor.
  • the motor consequently drives the blade connected to its drive shaft and the adjusting ring simultaneously. If several equally distributed over the circumference of the adjusting ring motors are provided, so each of these motors drives the collar and one of the adjustable blade directly. The not directly driven (remaining) blades are then pivoted by means of the adjusting ring in the desired position.
  • the use of multiple motors also allows distributed over the circumference of force for adjusting the blades. The more motors are used, the lower are the forces to be introduced by each of these, which enables smaller tooth drives or toothings.
  • two adjusting rings per drive device are provided in order to drive the pins free of transverse forces.
  • a circumferential groove is provided in the blade carrier or in the housing surrounding the blade carrier shell in which the pins end and in which the adjusting ring is arranged, wherein for shielding pin, collar and their coupling to the outside, the circumferential groove by a cover at least mostly closed.
  • the coupling of adjusting ring and pin is thus embedded in the blade carrier and sunk in the circumferential groove, which - viewed in longitudinal section of the turbomachine - results in a shield on both sides.
  • the adjusting mechanism is at least covered, if not hermetically sealed, whereby the drive is largely (ie except for the implementation for the drive shaft of the motor) is displaced into the wall of the blade carrier.
  • This requires that the blade carrier in the region in which the pins protrude into it, there has at least such a large wall thickness that there can be introduced from the outside, for example by mechanical machining a circumferential groove for receiving pin ends and collar.
  • the cover of the circumferential groove by a plurality of cover segments is easy to accomplish, the attachment of the cover or cover with the usual means such as fittings is feasible.
  • a simple construction is specified, which is comparatively simple and inexpensive to implement.
  • the coupling between the adjusting ring and the respective pin is in each case designed as a toothed drive, wherein the toothed drive is preferably designed as a crown gear.
  • the collar is a crown wheel and the pin is at least over a portion of its circumference, if not interlocked over its full circumference.
  • the toothing of the crown wheel and the toothing of the pin engage each other, so that rotation of the adjusting ring in the circumferential direction the blades are turned.
  • a particularly simple and reliable mounting of the adjusting ring can be achieved if this - relative to the central axis of the blade carrier - is guided radially outwardly from the cover of the circumferential groove and radially inwardly from the groove bottom of the circumferential groove.
  • the cover then serves as a guide for the adjusting ring, since this slidably, but without play abuts both the cover and the groove bottom.
  • this embodiment allows a comparatively slim collar because its inherent rigidity can now be lower than before.
  • Another advantage of the cover is the leadership of the adjusting ring along the entire circumference, since this is composed of at least two segments.
  • the segments of the adjusting ring can be connected or screwed together due to the proposed outer guide through the cover in a comparatively simple manner.
  • An evasion of the principle Rod-shaped adjusting ring is not possible by the full-length guidance.
  • the adjusting ring of a side wall of the circumferential groove based on the center line of the blade carrier - guided axially.
  • means for pressing the adjusting ring are provided on the pins in the side wall and / or between the side wall and adjusting ring.
  • equally distributed between the side wall and the adjusting ring over the circumference spring elements are provided which exert a force acting in the axial direction of the adjusting ring.
  • the contact pressure can be reduced during the adjustment process, which is readily possible in particular when using a hydraulic fluid as a contact pressure. In this case, the adjustment process can be effected with comparatively small forces.
  • the drive device can be used both for adjusting inlet guide vanes of a compressor, but also for adjusting guide vanes of a compressor, which are mounted in a manner analogous to the inlet guide vanes about their longitudinal axis extending in the radial direction of the machine axis.
  • FIG. 1 shows a trained as a gas turbine 1 turbomachine in a longitudinal partial section. It has inside a rotatably mounted about a rotation axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 forms a combustion chamber 17 which communicates with an annular hot gas channel 18.
  • There four successive turbine stages 10 form the turbine unit 8. Each turbine stage 10 is formed of two blade rings.
  • the hot gas channel 18 When viewed in the direction of flow of a hot gas 11 produced in the annular combustion chamber 6, the hot gas channel 18 is followed by a row of blades 13, a row 14 formed of blades 15.
  • the stator blades 12 are fixed to the stator, whereas the blades 15 of a row 14 are attached to the rotor 3 by means of a turbine disk are.
  • a generator or a working machine (not shown) is coupled.
  • adjustable inlet blades 19 are provided at the intake housing side entrance of the compressor 5 adjustable inlet blades 19 .
  • the inlet blades 19 are arranged radially in the annular flow channel of the compressor 5 and can be rotated about their respective longitudinal axis by a drive device 21, for example, the gas flow flowing through the gas turbine 1 mass flow adjust.
  • a particularly large or a small mass flow can flow through the gas turbine 1 as needed.
  • all inlet blades 19 are synchronously adjusted while maintaining the same angle of attack ,
  • the drive device 21 is provided outside the flow channel and will be described in detail in the following figures.
  • a blade carrier 22 is shown, which is also configured in the concrete embodiment as a housing component of the compressor 5 of the gas turbine 1 at the same time.
  • the vane carrier 22 is also referred to as a vane carrier.
  • the guide blade carrier 22 has an increased wall thickness.
  • this axial portion 23 are provided with respect to the central axis 24 of the gas turbine 1 in an identical number as adjustable blades 19 holes 25 for receiving pins 26 which are each arranged on one of the adjustable blades 19.
  • an endless circumferential groove 27 is also provided on the shell side, in which the pins 26 end.
  • the axial position of the holes 25 is chosen so that they do not open completely in the circumferential groove 27, but only partially such that only a small circular portion of the bore 25 is located in the groove 27 in order to ensure sufficient teeth (see FIG. 3 ).
  • the required for the rotatable mounting of the pin 26 in the vane support 22 bearing (not shown) are provided for circumferential groove 27 radially inwardly adjacent in a known manner.
  • the adjusting ring 28 has - viewed in longitudinal section of the turbomachine - a rectangular sectional contour.
  • Each pin 26 has at least over part of its circumference a toothing in the manner of a gear.
  • an end wall of the adjusting ring 28 is also toothed, both gears are in the manner of a crown gear engaged with each other.
  • the side wall teeth 30 of the adjusting ring 28 extends for each pin 26 along such an arc length ( FIG. 3 ) that the blade 19 can be safely pivoted over the entire Verstellwinkel Geb.
  • the side wall teeth 30 may also be arranged endlessly over the circumference of the adjusting ring 28 as in a crown wheel.
  • the adjusting ring 28 thus forms with each pin 26 a crown gear teeth, with which the rotational movement of the adjusting ring 28 is converted to the machine axis 24 in a rotary movement of the blade 19 about its longitudinal axis 31.
  • the groove 27 is shielded by a cover 32.
  • the toothed drives and the adjusting ring 28 are in principle not accessible from outside the gas turbine 1.
  • the motor 33 can be designed as a hydraulic motor, but also as an electric motor or as a servomotor.
  • the drive shaft 35 of the motor 33 extends through an opening provided in the cover 32 for opening 37 and is rigidly connected to one of the pins 26. Both are rotatable about a common axis of rotation, which coincides with the longitudinal axis 31.
  • the motor 33 serves on the one hand for driving the adjusting ring 28 and for the direct drive of one with its drive shaft 35 via the pin 26 rigidly connected blade 19. It can also be several of the in FIG. 2 shown motors 33 distributed over the circumference of the adjusting ring 28 to its rotation be.
  • the motor or motors 33 are then fastened via brackets not shown either on the guide vane or on the foundation of the gas turbine.
  • FIG. 4 sketched, in which the rigid connection between the drive shaft 35 and pin 26 is indicated only schematically.
  • FIG. 2 Next is in FIG. 2 in a side wall 34 of the circumferential groove 27, a channel opening 38 is provided, via which a hydraulic means of the drive device 21 for pressing the adjusting ring 28 to the pin 26 is possible.
  • the required connection cables are in FIG. 2 not shown.
  • several channels for hydraulic fluid are distributed along the circumference to achieve a uniform contact pressure.
  • FIG. 3 The plan view of an uncovered crown toothing in section 23 shows FIG. 3 , wherein identical features are provided with identical reference numerals.
  • FIG. 2 alternative embodiment, which in FIG. 6 is shown, instead of a unilaterally arranged adjusting ring 28, a further adjusting ring 28 may be provided, such that between two belonging to a drive device adjusting rings 28, the pins 26 of the blades 19 are arranged and thus toothed on both sides.
  • two grooves 27 are provided on both sides of the bores 25, in each of which one of the two adjusting rings 28 is arranged.
  • the bores 25 and thus also the pins 26 can be arranged centrally in only then a wider circumferential groove.
  • the two associated to a drive device 21 adjusting rings 28 are simultaneously rotating in opposite directions.
  • FIG. 5 The basic embodiment is in FIG. 5 shown, according to this the direct drive of one or more blades 19 is not mandatory.
  • the motor 33 is then used solely for adjusting the adjusting ring 28, which for pivoting all blades 19 its rotational movement over the FIG. 2 described tooth drives between them and the pin 26 of the blades 19 transmits to the latter.
  • FIG. 5 embodiment shown may be slightly modified with respect to the number of collars 28 and the choice of the means for pressing the collars 28 to the pin 26th
  • the drive device shown in the figures is not only suitable for adjusting inlet guide vanes 19 of a compressor 5, but of course also for adjusting guide vanes of subsequent compressor stages which in modern gas turbines also about their longitudinal axis 31, which with the radial direction with respect to the machine axis 24th coincides, are pivotally mounted.
  • the invention relates to a drive device 21 for pivoting adjustable blades 19 of a turbomachine, with one of a guide vane carrier 22 enclosed annular flow channel portion 23 which extends along the central axis 24 of the vane support 22 and are provided in the radiating manner to form a ring blades 19, wherein the blades 19 are each pivotable about its longitudinal axis 31 and in each case at least in the guide vane carrier 22 extending pin 26th have, which are coupled to at least one the guide pad carrier 22 encompassing adjusting ring 28.
  • the drive shaft 35 of the motor 33 and the motors with the adjusting ring 28 and the adjusting rings 28 is coupled via a toothed drive or are.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gear Transmission (AREA)
EP10001722A 2010-02-19 2010-02-19 Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine Withdrawn EP2362070A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP10001722A EP2362070A1 (fr) 2010-02-19 2010-02-19 Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine
JP2012553285A JP2013519836A (ja) 2010-02-19 2011-02-15 ターボ機械の調整可能なブレードを回動させるための駆動デバイス
RU2012139958/06A RU2012139958A (ru) 2010-02-19 2011-02-15 Приводное устройство для поворота регулируемых лопаток турбинной машины
US13/579,612 US20120308364A1 (en) 2010-02-19 2011-02-15 Drive device for pivoting adjustable blades of a turbomachine
PCT/EP2011/052188 WO2011101334A1 (fr) 2010-02-19 2011-02-15 Dispositif d'entraînement destiné à faire pivoter les aubes réglables d'une turbomachine
CN2011800098146A CN102762818A (zh) 2010-02-19 2011-02-15 用于枢转涡轮机的能调节叶片的驱动装置
EP11704062A EP2536922A1 (fr) 2010-02-19 2011-02-15 Dispositif d'entraînement destiné à faire pivoter les aubes réglables d'une turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10001722A EP2362070A1 (fr) 2010-02-19 2010-02-19 Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine

Publications (1)

Publication Number Publication Date
EP2362070A1 true EP2362070A1 (fr) 2011-08-31

Family

ID=42122787

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10001722A Withdrawn EP2362070A1 (fr) 2010-02-19 2010-02-19 Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine
EP11704062A Withdrawn EP2536922A1 (fr) 2010-02-19 2011-02-15 Dispositif d'entraînement destiné à faire pivoter les aubes réglables d'une turbomachine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11704062A Withdrawn EP2536922A1 (fr) 2010-02-19 2011-02-15 Dispositif d'entraînement destiné à faire pivoter les aubes réglables d'une turbomachine

Country Status (6)

Country Link
US (1) US20120308364A1 (fr)
EP (2) EP2362070A1 (fr)
JP (1) JP2013519836A (fr)
CN (1) CN102762818A (fr)
RU (1) RU2012139958A (fr)
WO (1) WO2011101334A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013087863A1 (fr) * 2011-12-16 2013-06-20 Siemens Aktiengesellschaft Turbomachine et procédé pour la faire fonctionner
BE1026063B1 (fr) * 2018-03-02 2019-10-03 Safran Aero Boosters S.A. Aube motrice de systeme a calage variable de compresseur pour turbomachine
US12018403B2 (en) 2010-07-16 2024-06-25 Adimab, Llc Antibody libraries

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10094219B2 (en) 2010-03-04 2018-10-09 X Development Llc Adiabatic salt energy storage
WO2014052927A1 (fr) * 2012-09-27 2014-04-03 Gigawatt Day Storage Systems, Inc. Systèmes et procédés de récupération et de stockage d'énergie
WO2014133724A1 (fr) 2013-02-12 2014-09-04 United Technologies Corporation Actionneur rotatif pour système de réglage d'aubes variable
CN103291383B (zh) * 2013-06-26 2015-02-25 上海交通大学 含有齿轮传动的压气机多级静叶调节机构
US9784365B2 (en) 2014-01-23 2017-10-10 Pratt & Whitney Canada Corp. Variable vane actuating system
JP6104838B2 (ja) * 2014-03-17 2017-03-29 三菱日立パワーシステムズ株式会社 検出装置、回転機械、及び検出装置の取付け方法
CN104110398A (zh) * 2014-04-30 2014-10-22 哈尔滨汽轮机厂有限责任公司 一种燃气轮机压气机用的可转导叶装置
US10001066B2 (en) 2014-08-28 2018-06-19 General Electric Company Rotary actuator for variable geometry vanes
EP3067530A1 (fr) * 2015-03-09 2016-09-14 General Electric Technology GmbH Procédé d'exploitation d'une turbine à gaz
DE102015004649A1 (de) * 2015-04-15 2016-10-20 Man Diesel & Turbo Se Leitschaufelverstellvorrichtung und Strömungsmaschine
US10125622B2 (en) * 2015-08-27 2018-11-13 Rolls-Royce North American Technologies Inc. Splayed inlet guide vanes
US10233787B2 (en) 2016-12-28 2019-03-19 Malta Inc. Storage of excess heat in cold side of heat engine
US10233833B2 (en) 2016-12-28 2019-03-19 Malta Inc. Pump control of closed cycle power generation system
US11053847B2 (en) 2016-12-28 2021-07-06 Malta Inc. Baffled thermoclines in thermodynamic cycle systems
US10458284B2 (en) 2016-12-28 2019-10-29 Malta Inc. Variable pressure inventory control of closed cycle system with a high pressure tank and an intermediate pressure tank
US10221775B2 (en) 2016-12-29 2019-03-05 Malta Inc. Use of external air for closed cycle inventory control
US10801404B2 (en) 2016-12-30 2020-10-13 Malta Inc. Variable pressure turbine
US10436109B2 (en) 2016-12-31 2019-10-08 Malta Inc. Modular thermal storage
US10450890B2 (en) 2017-09-08 2019-10-22 Pratt & Whitney Canada Corp. Variable stator guide vane system
CN108131171A (zh) * 2017-12-20 2018-06-08 哈尔滨广瀚燃气轮机有限公司 一种燃气轮机进口导叶控制系统
US11678615B2 (en) 2018-01-11 2023-06-20 Lancium Llc Method and system for dynamic power delivery to a flexible growcenter using unutilized energy sources
CN108167031A (zh) * 2018-03-06 2018-06-15 哈尔滨广瀚燃气轮机有限公司 一种燃气轮机用可转导叶执行机构
GB2581964A (en) * 2019-03-04 2020-09-09 Rolls Royce Plc A turbomachine for a gas turbine engine
CN110056509B (zh) * 2019-06-09 2020-07-28 三联泵业股份有限公司 一种供水水泵
CN116575994A (zh) 2019-11-16 2023-08-11 马耳他股份有限公司 双动力系统泵送热电储存动力系统
US11486305B2 (en) 2020-08-12 2022-11-01 Malta Inc. Pumped heat energy storage system with load following
EP4193042A1 (fr) 2020-08-12 2023-06-14 Malta Inc. Intégration de système d'accumulation d'énergie thermique par pompage dans une centrale thermique
US11480067B2 (en) 2020-08-12 2022-10-25 Malta Inc. Pumped heat energy storage system with generation cycle thermal integration
US11286804B2 (en) 2020-08-12 2022-03-29 Malta Inc. Pumped heat energy storage system with charge cycle thermal integration
US11454167B1 (en) 2020-08-12 2022-09-27 Malta Inc. Pumped heat energy storage system with hot-side thermal integration
US11396826B2 (en) 2020-08-12 2022-07-26 Malta Inc. Pumped heat energy storage system with electric heating integration
CN114810222B (zh) * 2022-04-26 2023-05-23 华北电力大学（保定） 一种核电汽轮机静叶环内可调高度可加热的端壁翼刀

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE623280A (fr) *
US2500070A (en) * 1945-06-15 1950-03-07 Westinghouse Electric Corp Multistage, axial flow, gas compressor
DE1024199B (de) * 1953-10-09 1958-02-13 Sulzer Ag Mehrstufige Axialturbomaschine
GB952870A (en) * 1960-03-31 1964-03-18 Louis Rene Corvisier Improvements in or relating to variable-pitch control devices for bladed impellers and diffusers of blowers, compressors or like machines
GB1466613A (en) 1973-09-07 1977-03-09 Nissan Motor Guide vane control for an automobile gas turbine engine
GB1505858A (en) * 1976-12-08 1978-03-30 Secr Defence Axial flow rotary machines
FR2688827A1 (fr) * 1992-03-18 1993-09-24 Snecma Systeme de commande d'aubes de stator a calage variable, pour un turboreacteur.
US5549448A (en) 1995-02-08 1996-08-27 United Technolgies Corporation Variable stator vane linkage system and method
DE29917625U1 (de) * 1999-10-06 2000-03-09 IAV GmbH Ingenieurgesellschaft Auto und Verkehr, 10587 Berlin Vorrichtung zum Beeinflussen der Strömung im Einströmbereich von Strömungsmaschinen
EP1524413A2 (fr) 2003-10-15 2005-04-20 United Technologies Corporation Manchon de palier en électro-graphite pour une aube variable
EP1672180A1 (fr) * 2004-12-16 2006-06-21 Snecma Etage d'aubes de redresseur actionnées par une couronne rotative déplacée par des moyens moteurs électriques
EP2053204A2 (fr) * 2007-10-22 2009-04-29 United Technologies Corporation Moteur à turbine à gaz avec aubes variables

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1505868A (en) 1974-06-13 1978-03-30 Ciba Geigy Ag I-alkyl-i-cyanohydrazines and their use for the production of 1,2,4-triazole derivatives
US4639148A (en) * 1984-02-14 1987-01-27 Aisin Seiki Kabushiki Kaisha Thrust bearing for turbocharger
JP2006046220A (ja) * 2004-08-05 2006-02-16 Toyota Motor Corp ベーン駆動装置

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE623280A (fr) *
US2500070A (en) * 1945-06-15 1950-03-07 Westinghouse Electric Corp Multistage, axial flow, gas compressor
DE1024199B (de) * 1953-10-09 1958-02-13 Sulzer Ag Mehrstufige Axialturbomaschine
GB952870A (en) * 1960-03-31 1964-03-18 Louis Rene Corvisier Improvements in or relating to variable-pitch control devices for bladed impellers and diffusers of blowers, compressors or like machines
GB1466613A (en) 1973-09-07 1977-03-09 Nissan Motor Guide vane control for an automobile gas turbine engine
GB1505858A (en) * 1976-12-08 1978-03-30 Secr Defence Axial flow rotary machines
FR2688827A1 (fr) * 1992-03-18 1993-09-24 Snecma Systeme de commande d'aubes de stator a calage variable, pour un turboreacteur.
US5549448A (en) 1995-02-08 1996-08-27 United Technolgies Corporation Variable stator vane linkage system and method
DE29917625U1 (de) * 1999-10-06 2000-03-09 IAV GmbH Ingenieurgesellschaft Auto und Verkehr, 10587 Berlin Vorrichtung zum Beeinflussen der Strömung im Einströmbereich von Strömungsmaschinen
EP1524413A2 (fr) 2003-10-15 2005-04-20 United Technologies Corporation Manchon de palier en électro-graphite pour une aube variable
EP1672180A1 (fr) * 2004-12-16 2006-06-21 Snecma Etage d'aubes de redresseur actionnées par une couronne rotative déplacée par des moyens moteurs électriques
EP2053204A2 (fr) * 2007-10-22 2009-04-29 United Technologies Corporation Moteur à turbine à gaz avec aubes variables

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12018403B2 (en) 2010-07-16 2024-06-25 Adimab, Llc Antibody libraries
WO2013087863A1 (fr) * 2011-12-16 2013-06-20 Siemens Aktiengesellschaft Turbomachine et procédé pour la faire fonctionner
BE1026063B1 (fr) * 2018-03-02 2019-10-03 Safran Aero Boosters S.A. Aube motrice de systeme a calage variable de compresseur pour turbomachine

Also Published As

Publication number Publication date
CN102762818A (zh) 2012-10-31
US20120308364A1 (en) 2012-12-06
EP2536922A1 (fr) 2012-12-26
RU2012139958A (ru) 2014-03-27
JP2013519836A (ja) 2013-05-30
WO2011101334A1 (fr) 2011-08-25

Similar Documents

Publication Publication Date Title
EP2362070A1 (fr) Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine
EP1398463B1 (fr) Aubes de guidage variables et turbosoufflante avec ces aubes
EP1394364B1 (fr) Turbosoufflante et son anneau de guidage
DE69002523T2 (de) Einrichtung zur Veränderung der Propellersteigung.
EP2209969B1 (fr) Dispositif de suralimentation
DE69019833T2 (de) Turbolader mit verstellbaren Leitschaufeln.
DE4028328A1 (de) Vorrichtung zum steuern der spaltbreite zwischen den laufschaufelspitzen und einem stationaeren gehaeusemantelring eines gasturbinentriebwerks
EP2650490A2 (fr) Dispositif de réglage d'aube directrice d'une turbine à gaz
DE4036693A1 (de) Laufschaufelspitzenspaltbreitensteuer - vorrichtung mit mantelsegmenteinstellung durch gleichlaufring
EP1460237A1 (fr) Carter pour une turbosoufflante
EP3000984A1 (fr) Dispositif de reglage d'aube directrice d'une turbine a gaz
DE4214775A1 (de) Dampfturbine mit einem Drehschieber
EP2520767B1 (fr) dispositif de correction de balourd d'un rotor d'une turbine à gaz
DE3837994A1 (de) Vorrichtung zur verstellung der rotorschaufeln eines propfan/turboproptriebwerkes
EP2386726B1 (fr) Section de paroi de canal pour un canal d'écoulement annulaire d'une turbomachine axiale dotée d'un réglage du jeu en bout d'aube, compresseur axial et turbine à gaz associés
DE1011671B (de) Radialturbomaschine mit einstellbarem Leitapparat
EP2799776A1 (fr) Joint de brûleur pour tête de chambre de combustion de turbines à gaz et bouclier thermique
EP2617947B1 (fr) Turbine à gaz d'avion avec soufflante ajustable
EP2730751B1 (fr) Dispositif de réglage d'aubes directrices d'une turbine à gaz
EP0173803B1 (fr) Machine d'écoulement
EP3336319B1 (fr) Dispositif de réglage destiné au réglage d'aubes directrices multiples d'un groupe propulseur
EP3095957A1 (fr) Rotor pour une turbomachine thermique
EP1746256A1 (fr) Diminution des pertes dues au jeu en bout d'aubes dans les turbomachines
DE10303340A1 (de) Kühleinrichtung
DE1286333B (de) Ringfoermige Leitvorrichtung fuer Gasturbinentriebwerke mit axialer Stroemung

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20120301