EP2233701A1 - Axialturbomaschine mit axial verschiebbarem Leitschaufelträger - Google Patents

Axialturbomaschine mit axial verschiebbarem Leitschaufelträger Download PDF

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Publication number
EP2233701A1
EP2233701A1 EP09004409A EP09004409A EP2233701A1 EP 2233701 A1 EP2233701 A1 EP 2233701A1 EP 09004409 A EP09004409 A EP 09004409A EP 09004409 A EP09004409 A EP 09004409A EP 2233701 A1 EP2233701 A1 EP 2233701A1
Authority
EP
European Patent Office
Prior art keywords
axial turbomachine
housing
ring
adjusting ring
axial
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Withdrawn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
EP09004409A
Other languages
German (de)
English (en)
French (fr)
Inventor
Francois Dr. Benkler
Andreas Dr. Böttcher
Uwe Kahlstorf
Torsten Matthias
Dieter Minninger
Oliver Dr. Schneider
Peter Schröder
Vyacheslav Veitsman
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP09004409A priority Critical patent/EP2233701A1/de
Priority to CN201080013989.XA priority patent/CN102365426B/zh
Priority to EP10713598.0A priority patent/EP2411632B1/de
Priority to PL10713598T priority patent/PL2411632T3/pl
Priority to JP2012501266A priority patent/JP5346118B2/ja
Priority to PCT/EP2010/053663 priority patent/WO2010108876A1/de
Priority to US13/260,406 priority patent/US9057281B2/en
Publication of EP2233701A1 publication Critical patent/EP2233701A1/de
Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • 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
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position

Definitions

  • the invention relates to an axial turbomachine with an axially displaceable vane carrier.
  • radial gaps between blades and the housing lead to significant losses in thermal efficiency.
  • the axial turbomachine is, for example, a gas turbine.
  • the gas turbine When starting and stopping the gas turbine, the radial gaps change over time.
  • the radial gaps change when switching from part load operation to full load operation of the gas turbine.
  • the gas turbine is designed so that the radial gap for the operating case in which the radial gaps are the smallest set, are sufficiently large, so that there is virtually no contact between the blades and the housing. This has the consequence that in continuous operation of the gas turbine unnecessarily large radial gaps must be kept for this operating condition, which is associated with a significant loss of efficiency.
  • the temporal change of the radial gaps is the result of different thermal inertia behavior of the individual components of the gas turbine, in particular the rotor, the blades and the housing.
  • the temporal change of the radial gap causes the centrifugal force expansion, in particular of the blades, a transverse contraction of the rotor, a possible play in the thrust bearing of the rotor, in particular in connection with the reversal of axial thrust under appropriate operating conditions of the gas turbine, a possibly occurring ovalization of the housing due to montage charitableer Preload and uneven heating of the housing.
  • the object of the invention is to provide an axial turbomachine with a high thermal efficiency.
  • the axial turbomachine comprises a blade grid, which is formed by blades, each with a radially outer, free-standing and inclined to the axis of the axial turbomachine blade tip, a housing in which the blade grid is installed and defines the inside of the main flow channel of the axial turbine, and a vane grille sheathing and integrated into the inside of the housing with a radially inner ring inner side, with the inside of the housing of the main flow channel is continued and the vane support immediately adjacent to the blade tips to form a radial gap between the envelope of the blade tips and the ring inside is arranged, wherein the inner ring side is substantially parallel to the blade tip and the Leitschaufelitati in the housing parallel to the axis of the axial turbomachine
  • 29ie Bbar is mounted and has a collar which is supported on the housing and on the vane support on contact surfaces and is rotatable about the axis of the axial turbomachine, wherein the contact surfaces of the adjusting ring and the housing and /
  • the critical operating state with regard to the radial gap during hot start is. If the axial turbomachine is, for example, an axial turbine, then the critical operating state with regard to the radial gaps is the cold start. Until the components of the housing after starting accordingly have warmed through and thermally expanded to a larger diameter, there is a risk that the blades with their blade tips to the housing.
  • the critical phase of operation which can be expected with small radial gaps, is about 5 to 10 minutes.
  • the guide blade carrier provided according to the invention in the axial turbomachine which is axially displaceable by means of the adjusting ring, remedies this problem.
  • the dimension of the radial gap can be adapted to the prevailing operating state of the axial turbomachine for a short time, with the smallest possible radial gap always being sought.
  • the thermal efficiency is high in all operating conditions of the axial turbomachine.
  • the axial turbomachine according to the invention may also additionally comprise a known device for adjusting the radial gaps during operation of the axial turbomachine, so that the conventional device and the actuation of the adjusting ring according to the invention for suitable axial displacement of the guide blade carrier can be operated simultaneously.
  • the conventional device and the actuation of the adjusting ring according to the invention for suitable axial displacement of the guide blade carrier can be operated simultaneously.
  • the vane carrier has a radially outwardly extending, circumferential vane carrier web with an outwardly open annular groove into which an inward radial extends extending, circumferential housing web, wherein in the annular groove between the Leitschaufelanisteg and the housing web of the adjusting ring is arranged.
  • the adjusting ring is preferably located at the bottom of the annular groove, whereby the adjusting ring is mounted radially from the annular groove during rotation. It is preferred that a fixing ring is provided between the adjusting ring and the housing web, which is fastened to the housing web and interacts with the adjusting ring for axial displacement of the guide blade carrier.
  • the fixing ring has on its side facing the adjusting ring a first sawtooth profile and the adjusting ring preferably has on its side facing the fixing ring a second sawtooth profile, the sawtooth profiles meshing with each other and can slide together, that when the collar is axially rotated, the guide vane is moved axially.
  • the sawtooth profiles of the two rings results between the housing bar and the Leitschaufelanisteg an axially modifiable measure.
  • the guide vane carrier is axially displaceable by the actuation of the adjusting ring.
  • the fixing ring is preferably fixed in a form-fitting manner to the housing web.
  • the positive fixing of the fixing ring can, for example, by a radially extending groove which is provided in the housing web and in which engages a correspondingly shaped nose of the fixing ring. As a result, the fixing ring is fixed to the housing web in the circumferential direction.
  • the adjusting ring is mounted on the fixing ring with a roller bearing provided between the sawtooth profiles.
  • a roller bearing provided between the sawtooth profiles.
  • a biasing device is preferably provided, which is supported on the housing and acts on the guide blade carrier web counteracting the adjusting ring, so in that the guide blade carrier web is always pressed against the adjusting ring by the pretensioning device.
  • the biasing means is preferably a coil spring.
  • the ring inner side preferably tapers and preferably the adjusting ring is arranged on the housing web upstream of the ring.
  • the biasing device is preferably arranged on the housing web.
  • FIG. 2 A conventional axial turbomachine 101 is shown.
  • the axial turbomachine 101 has a housing 2 with an inner side 3, with which a main flow channel 4 is defined.
  • a blade ring is arranged which is formed from a plurality of rotor blades 5 arranged distributed over the circumference.
  • Each of the blades 5 faces upstream of a leading edge 6 and downstream of a trailing edge 7. Radially outward, the blade 5 is bounded by a blade tip 8.
  • the main flow channel 4 is in FIG. 2 flows through from left to right in the main flow direction, wherein the main flow channel 4 widens in the main flow direction.
  • the inner side 3 of the housing 2 is arranged inclined relative to the axis 22 of the axial turbomachine 101.
  • a guide blade carrier 10 is provided in the housing 2.
  • the guide blade carrier 10 has the axis 22 of the axial turbomachine 101 facing a ring inner side 11 which extends parallel to the blade tip 8. Between the ring inner side 11 and the blade tip 8, a radial gap 12 is formed.
  • the vane support 10 has a radially outwardly extending vane support web 13, which has an outwardly opening, circumferential annular groove 9.
  • a housing web 14 is provided on the housing 2, which extends radially inward and is circumferential. The vane support 10 is secured to the housing web 14 with attachment means so that the vane support 10 is stationary.
  • FIG. 1 a section of an axial turbomachine according to the invention is shown.
  • the axial turbomachine according to the invention differs from the conventional axial turbomachine 101 as shown in FIG. 2 is shown in that the guide blade carrier 10 is arranged axially displaceably on the housing web 14.
  • the annular groove 9 is formed axially wider, wherein additionally in the annular groove 9 upstream of the housing web 14, a fixing ring 15 and a collar 16 are arranged.
  • the fixing ring 15 and the adjusting ring 16 are provided side by side lying in the annular groove 9, wherein the fixing ring 15 and the adjusting ring 16 are mounted at their inner diameters at the bottom of the annular groove 9 in the radial direction.
  • the fixing ring 15 has on its adjusting ring 16 facing, annular side formed a first sawtooth profile 17, the edges of which extend radially.
  • a second sawtooth profile 18 is formed as the correspondence to the first sawtooth profile 17.
  • the adjusting ring 16 has on its side remote from the second sawtooth profile 18 on a flat annular surface which rests flat against a side wall of the annular groove 9.
  • the fixing ring 15 has on its side facing away from the sawtooth profile 17 on a flat annular surface which bears against the housing web 14, wherein protrudes from this annular surface a nose 21 which engages in a groove 20 provided in the housing web.
  • the groove 20 and the nose 21 form a positive connection in the circumferential direction, so that is fixed by the nose 21 of the fixing ring 15 in the circumferential direction of the housing web 14.
  • the adjusting ring 16 is rotatably mounted relative to the fixing ring 15 in the annular groove 9.
  • the second sawtooth profile 18 is added to the first sawtooth profile 17. Due to the obliquely employed flanks of the sawtooth profiles 17 and 18 results in the rotation of the adjusting ring 16 is a changing axial position of the fixing ring 15 relative to the adjusting ring 16.
  • the fixing ring 15 is supported on the housing web 14 axially in the main flow direction, is by the against each other Displacement of the sawtooth profiles 17 and 18 of the adjusting ring 16 axially displaced from the fixing ring 15 counter to the main flow direction. Due to the axial support of the adjusting ring 16 on the guide blade carrier web 13 in the annular groove 9, the guide blade carrier 10 is displaced in the housing 2 axially against the main flow direction. As a result, the radial gap 12 increases.
  • the base of the annular groove 9 is formed parallel to the axis of the axial turbomachine 1 and the radially inner edge of the housing web 14 abuts the bottom of the annular groove 9, so that when the guide blade carrier 10 caused by an adjustment of the adjusting ring 16 is axially displaced back and forth , the guide vane carrier 10 is mounted radially on the housing web 14.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP09004409A 2009-03-26 2009-03-26 Axialturbomaschine mit axial verschiebbarem Leitschaufelträger Withdrawn EP2233701A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP09004409A EP2233701A1 (de) 2009-03-26 2009-03-26 Axialturbomaschine mit axial verschiebbarem Leitschaufelträger
CN201080013989.XA CN102365426B (zh) 2009-03-26 2010-03-22 具有可轴向移动的导向叶片支架的轴流式涡轮机
EP10713598.0A EP2411632B1 (de) 2009-03-26 2010-03-22 Axialturbomaschine mit axial verschiebbarem leitschaufelträger
PL10713598T PL2411632T3 (pl) 2009-03-26 2010-03-22 Osiowa maszyna wirnikowa z przemieszczalnym osiowo wspornikiem łopatki kierowniczej
JP2012501266A JP5346118B2 (ja) 2009-03-26 2010-03-22 軸方向に変位可能なガイドベーンキャリアを有する軸流ターボ機械
PCT/EP2010/053663 WO2010108876A1 (de) 2009-03-26 2010-03-22 Axialturbomaschine mit axial verschiebbarem leitschaufelträger
US13/260,406 US9057281B2 (en) 2009-03-26 2010-03-22 Axial turbomachine having an axially displaceable guide-blade carrier

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09004409A EP2233701A1 (de) 2009-03-26 2009-03-26 Axialturbomaschine mit axial verschiebbarem Leitschaufelträger

Publications (1)

Publication Number Publication Date
EP2233701A1 true EP2233701A1 (de) 2010-09-29

Family

ID=41327688

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09004409A Withdrawn EP2233701A1 (de) 2009-03-26 2009-03-26 Axialturbomaschine mit axial verschiebbarem Leitschaufelträger
EP10713598.0A Not-in-force EP2411632B1 (de) 2009-03-26 2010-03-22 Axialturbomaschine mit axial verschiebbarem leitschaufelträger

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10713598.0A Not-in-force EP2411632B1 (de) 2009-03-26 2010-03-22 Axialturbomaschine mit axial verschiebbarem leitschaufelträger

Country Status (6)

Country Link
US (1) US9057281B2 (pl)
EP (2) EP2233701A1 (pl)
JP (1) JP5346118B2 (pl)
CN (1) CN102365426B (pl)
PL (1) PL2411632T3 (pl)
WO (1) WO2010108876A1 (pl)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3078815A1 (en) * 2015-04-09 2016-10-12 United Technologies Corporation Active clearance control for axial rotor systems
CN110374685A (zh) * 2019-07-17 2019-10-25 中国航发沈阳发动机研究所 锯齿冠转子叶片非工作面侧向间隙控制方法及航空发动机

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2623717A1 (de) * 2012-02-02 2013-08-07 Siemens Aktiengesellschaft Schaufelkranz für eine Axialturbomaschine und Verfahren zum Justieren der Schluckfähigkeit des Schaufelkranzes
DE102012215413B4 (de) * 2012-08-30 2020-04-02 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine
EP2711504A1 (de) * 2012-09-19 2014-03-26 Siemens Aktiengesellschaft Vorrichtung zum Überbrücken eines Spiels
EP3049638B1 (en) * 2013-09-27 2022-01-19 Raytheon Technologies Corporation Gas turbine engine rapid response clearance control system and corresponding method
WO2018093429A1 (en) * 2016-08-10 2018-05-24 In2Rbo, Inc. Multistage radial compressor and turbine
KR102047328B1 (ko) * 2017-12-21 2019-11-21 두산중공업 주식회사 가스터빈의 블레이드 팁 간극 제어장치
CN111980969B (zh) * 2020-08-07 2022-09-23 中国人民解放军63837部队 用于超低温轴流压缩机的双层壳体
FR3161450B1 (fr) * 2024-04-19 2026-03-06 Safran Aircraft Engines Ensemble d’arbres d’une turbomachine comprenant un systeme de controle actif de translations axiales inter-abres d’un corps et procede de controle actif des jeux axiaux entre un5 element de rotor et un element de stator d’une turbine

Citations (6)

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DE1426818A1 (de) * 1963-07-26 1969-03-13 Licentia Gmbh Einrichtung zur Radialverstellung von Segmenten eines Ringes einer Axialturbomaschine,insbesondere -gasturbine,der Leitschaufeln traegt und/oder Laufschaufeln umgibt
US4932835A (en) * 1989-04-04 1990-06-12 Dresser-Rand Company Variable vane height diffuser
US6158956A (en) * 1998-10-05 2000-12-12 Allied Signal Inc. Actuating mechanism for sliding vane variable geometry turbine
EP1900907A2 (en) * 2006-09-08 2008-03-19 Siemens Power Generation, Inc. Turbine blade tip gap reduction system for a turbine engine
US20080131270A1 (en) * 2006-12-04 2008-06-05 Siemens Power Generation, Inc. Blade clearance system for a turbine engine
DE102007003028A1 (de) * 2007-01-20 2008-07-24 Mtu Aero Engines Gmbh Turbomaschine

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US3227418A (en) * 1963-11-04 1966-01-04 Gen Electric Variable clearance seal
ATE42211T1 (de) 1983-12-05 1989-05-15 Monsanto Co Hochleistungskristallisationskolonne.
JPS60187302U (ja) * 1984-05-22 1985-12-12 株式会社東芝 蒸気タ−ビン
DE50112597D1 (de) * 2001-04-12 2007-07-19 Siemens Ag Gasturbine mit axial verschiebbaren Gehäuseteilen
JP2003286992A (ja) * 2002-03-28 2003-10-10 Mitsubishi Heavy Ind Ltd ターボ分子ポンプ及びその調整方法
JP3907635B2 (ja) * 2004-04-16 2007-04-18 ファナック株式会社 電動機

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1426818A1 (de) * 1963-07-26 1969-03-13 Licentia Gmbh Einrichtung zur Radialverstellung von Segmenten eines Ringes einer Axialturbomaschine,insbesondere -gasturbine,der Leitschaufeln traegt und/oder Laufschaufeln umgibt
US4932835A (en) * 1989-04-04 1990-06-12 Dresser-Rand Company Variable vane height diffuser
US6158956A (en) * 1998-10-05 2000-12-12 Allied Signal Inc. Actuating mechanism for sliding vane variable geometry turbine
EP1900907A2 (en) * 2006-09-08 2008-03-19 Siemens Power Generation, Inc. Turbine blade tip gap reduction system for a turbine engine
US20080131270A1 (en) * 2006-12-04 2008-06-05 Siemens Power Generation, Inc. Blade clearance system for a turbine engine
DE102007003028A1 (de) * 2007-01-20 2008-07-24 Mtu Aero Engines Gmbh Turbomaschine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3078815A1 (en) * 2015-04-09 2016-10-12 United Technologies Corporation Active clearance control for axial rotor systems
US20160298483A1 (en) * 2015-04-09 2016-10-13 United Technologies Corporation Active clearance control for axial rotor systems
US10323536B2 (en) 2015-04-09 2019-06-18 United Technologies Corporation Active clearance control for axial rotor systems
CN110374685A (zh) * 2019-07-17 2019-10-25 中国航发沈阳发动机研究所 锯齿冠转子叶片非工作面侧向间隙控制方法及航空发动机

Also Published As

Publication number Publication date
EP2411632A1 (de) 2012-02-01
US9057281B2 (en) 2015-06-16
JP5346118B2 (ja) 2013-11-20
EP2411632B1 (de) 2013-06-19
JP2012521511A (ja) 2012-09-13
PL2411632T3 (pl) 2013-11-29
US20120076638A1 (en) 2012-03-29
CN102365426B (zh) 2015-09-02
CN102365426A (zh) 2012-02-29
WO2010108876A1 (de) 2010-09-30

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