EP2411632A1 - Turbomachine axiale à support d'aubes fixes déplaçable axialement - Google Patents

Turbomachine axiale à support d'aubes fixes déplaçable axialement

Info

Publication number
EP2411632A1
EP2411632A1 EP10713598A EP10713598A EP2411632A1 EP 2411632 A1 EP2411632 A1 EP 2411632A1 EP 10713598 A EP10713598 A EP 10713598A EP 10713598 A EP10713598 A EP 10713598A EP 2411632 A1 EP2411632 A1 EP 2411632A1
Authority
EP
European Patent Office
Prior art keywords
adjusting ring
axial turbomachine
ring
housing
leitschaufeltrager
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.)
Granted
Application number
EP10713598A
Other languages
German (de)
English (en)
Other versions
EP2411632B1 (fr
Inventor
Francois Benkler
Andreas Böttcher
Uwe Kahlstorf
Torsten Matthias
Dieter Minninger
Oliver 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
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 PL10713598T priority Critical patent/PL2411632T3/pl
Priority to EP10713598.0A priority patent/EP2411632B1/fr
Publication of EP2411632A1 publication Critical patent/EP2411632A1/fr
Application granted granted Critical
Publication of EP2411632B1 publication Critical patent/EP2411632B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 Leitschaufeltrager.
  • radial gaps between blades and the housing lead to significant losses in thermal efficiency.
  • the axial turbomachine is for example a
  • the gas turbine When starting and stopping the gas turbine, the radial gaps change over time. In addition, 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 set as the smallest, 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 of the rotor, of the rotor blades and of 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 clearance in the axial bearing of the rotor, in particular in connection with the reversal of axial thrust under corresponding operating conditions of the gas turbine, a possibly occurring ovalization of the housing due to montagebe- permanent pretension and uneven heating of the housing.
  • Offenlegungssch ⁇ ft DE 1 426 818 discloses an adjustment mechanism for moving the Leitschaufeltragers in Radial ⁇ chtung.
  • eight longitudinally extending I-shaped segment carriers are distributed over the circumference of the axial turbine, at the inner end of the Leitschaufeltrager is hooked form fit.
  • the mutually contacting surfaces of the flanges of the segment carriers and the Leitschaufeltrager are formed like a saw tooth to synchronous Langsverschiebung all Segmenttrager in a radial displacement of
  • Ubersch ⁇ ng is also internally conical. Between two conical surfaces cylindrical Walzkorper are provided, which are aligned obliquely relative to the axial direction. By a relative rotation of the coupling ring against the shroud, the radial gap between the blade tips of the blades and the shroud can be adjusted.
  • the Ubersch ⁇ ng executed in a relatively thick wall thickness deforms the in a relatively thin wall running executed collar ring in terms of elastic deformation, so adapted by turning the diameter of the shroud and thus the gap between the shroud and the blade ring can be adjusted. It is disadvantageous that the shroud is elastically deformed. Even over the circumference uniform gap setting is only partially possible due to the spaced apart with each other rolling body.
  • the object of the invention is to provide a Axialturbomaschme with a high thermal efficiency, the device for Radialspaltem ein is relatively simple, reliable and accurate.
  • the axial-turbomachinery has a rotor blade grille formed by rotor blades each having a radially outer, free-standing blade tip extending obliquely to the axis of the axial turbine cylinder, a housing in which the rotor blade grille is installed and which with its inner side forms the main flow channel of the axial flow belt. Bine defined, and the blade shroud enclosing and m the inside of the housing integrated Leitschaufel- carrier with a radially inner ring inside lying on the inside of the housing, the main flow channel is continued and the Leitschaufeltrager immediately adjacent to the blade tips to form a
  • Radial gap between the envelope of the blade tips and the ring inner side is arranged, wherein the Rmgmnen- side substantially parallel to the blade tip and the Leitschaufeltrager is slidably mounted in the housing parallel to the axis of the Axialturbomaschme and has a collar which on the housing and on the Leitschau- feltrager truncated on contact surfaces and is rotatable about the axis of Axialturbomaschme, wherein the contact surfaces of the adjusting ring and of the housing and / or of the Leitsch Kirs are so employed to a plane perpendicular to the axis of the axial turbomachine plane, that when the adjusting ring is rotated about the axis of the axial turbomachine, the Leitschaufeltrager is axially displaceable by the adjusting ring.
  • the critical operating state with regard to the radial gap during hot start is. If the axial turbomachine at ⁇ play, a Axialturbme, the critical operating condition is in terms of radial gaps during cold starts. Until the components of the housing have warmed up properly after starting and thermally expanded to a larger diameter, there is a risk that the blades will touch the housing with their blade tips. The critical phase of operation, which can be expected with small radial gaps, is about 5 to 10 minutes. To remedy the erfmdungsgeINE axially slidably provided in the axial turbomachine Leitschaufeltrager, which is axially displaceable by means of the adjusting ring.
  • Characterized in that the ring inner side and the blade tips are arranged inclined to the axis of the axial ⁇ turbomachinery, can be produced by a corresponding axial displacement of the Leitschaufeltragers a change of the radial gap.
  • the measure of the radial gap can be adapted to the correspondingly prevailing operating state of the axial turbomachine for a short time, whereby the smallest possible radial gap is always desired.
  • the thermal efficiency is high in all operating states of the axial turbomachine.
  • the axial turbomachine according to the invention may additionally have a known device for adjusting the radial gaps during operation of the axial turbomachine, so that the The device and the actuation of the adjusting ring according to the invention for the suitable axial displacement of the vane carrier can be operated simultaneously at the same time.
  • After overcoming the starting phase of the axial turbomachine can be brought by appropriate actuation of the adjusting ring in its original starting position after the components have been thoroughly heated by the Leitschaufeltra ⁇ ger. Only during critical operating phases, for example, the Leitschaufeltrager can be moved accordingly.
  • the Leitschaufeltrager has an outwardly radially extending, rotating Leitschaufeltragersteg with an outwardly open annular groove, m engages a radially inwardly extending, circumferential Gehausesteg, wherein in the annular groove between the Leitschaufeltragersteg and the
  • the collar 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 Gehausesteg, which is attached to the Gehausesteg and is in axial motion for the Leitschaufeltragers with the adjusting ring in interaction.
  • the fixing ring has on its side facing the adjusting ring side a first sawtooth profile and the adjustment ring preferably has, on its side facing the fixing ring side a second sawtooth profile, wherein the sawtooth profile in such a can nested grei ⁇ fen and slide against each other that when the adjusting ring is rotated axially is moved axially, the Leitschaufeltrager.
  • the sawtooth profile in such a can nested grei ⁇ fen and slide against each other that when the adjusting ring is rotated axially is moved axially, the Leitschaufeltrager.
  • the fixing ring is preferably fixed form fit to the Gehausesteg.
  • the form gleichige fixing of the fixing ring for example, by a radially extending groove in the Gehausesteg is provided and engages in a corresponding pas ⁇ send trained nose of the fixing ring.
  • the fixing ring is fixed to the Gehausesteg in memoris ⁇ chtung.
  • the adjusting ring is mounted on the fixing ring with a roller bearing provided between the sawtooth profiles.
  • the axes of rotation of the rolling bearings are in Radial ⁇ chtung the turbomachine. Due to the rolling bearings, the friction and wear on the sawtooth profiles during actuation of the adjusting ring is minimized, as a result of which the adjusting ring and the fixing ring have a long service life.
  • a biasing device is preferably provided, which is truncated on the housing and acting on the Leitschaufeltragersteg counteracting the adjusting ring, so that is printed by the biasing device, the Leitschaufeltragersteg always on the adjusting ring.
  • the biasing means is preferably a coil spring.
  • the inside of the ring preferably curves, and preferably the upstream side of the ring
  • Adjusting ring arranged on the Gehausesteg As a result, a compressive force can be exerted in the main flow direction when the guide blade carrier is displaced into the main flow direction by the adjusting ring.
  • the biasing device is preferably arranged on the Gehausesteg.
  • Adjusting the adjusting ring are preferably provided an adjusting rod and / or a hydraulic ram.
  • FIG. 2 shows a longitudinal section through a conventional axial turbomaschme.
  • a conventional Axialturbomaschme 101 ge ⁇ shows.
  • the Axialturbomaschme 101 has a housing 2 with an inner side 3, with 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 rotor blades 5 has upstream of a front 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 traversed in Figure 2 from left to right in the main flow direction, wherein the main flow channel 4 expands in the main flow direction.
  • the inner side 3 of the housing 2 is arranged inclined relative to the axis 22 of the Axialturbomaschme 101.
  • a Leitschaufeltrager 10 Radially in the region of the blade tip 8, a Leitschaufeltrager 10 is provided in the housing 2.
  • the Leitschaufeltrager 10 facing the axis 22 of the Axialturbomaschme 101 facing a ring inner side 11, which runs parallel to the blade tip 8. Between the ring inner side 11 and the blade tip 8, a radial gap 12 is formed.
  • the Leitschaufeltrager 10 has a radially outwardly extending Leitschaufeltragersteg 13, which has an outwardly opening, circumferential annular groove 9.
  • a Gehausesteg 14 is provided on the housing 2, which extends radially inwardly and is circumferential.
  • the vane trolley 10 is secured to the housing ridge 14 with fasteners such that the vane carrier 10 is stationary.
  • 1 shows a section of a Erflndungsgeclaren Axialtur- bomaschine shown.
  • the inventive axial flow turbomachine is different from the conventional axial flow turbomachine 101, as shown in FIG 2, is that the guide vane is axially slidably feltrager ⁇ arranges the Gehausesteg 14 10th
  • the annular groove 9 is of an axially wider design, with an additional annular groove 9 upstream of the housing web 14
  • the fixing ring 15 has, on its annular ring-shaped side facing the adjusting ring 16, a first saw tooth 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 facing away from the second sawtooth profile 18 a flat annular surface which lies flat against a side wall of the annular groove 9.
  • the fixing ring 15 has at its the
  • the adjusting ring 16 is rotatably mounted relative to the fixing ring 15 in the annular groove 9.
  • the second sawtooth profile 18 is joined to the first sawtooth profile 17. puts. Due to the obliquely set flanks of the saw tooth profile 17 and 18, a changing axial position of the fixing ring 15 relative to the adjusting ring 16 results when the adjusting ring 16 is rotated.
  • the compressive force serves as a restoring force for the Leitschaufeltrager 10, so that when the axial extent of the fixing ring 15 is reduced together with the adjusting ring 16 by the rotation of the adjusting ring 16, the Leitschaufeltrager 13 may follow the adjusting ring 16.
  • the Leitschaufeltrager 10 is moved in the Hauptstromungs ⁇ chtung and the radial gap 12 verklemert.
  • the base of the annular groove 9 is formed parallel to the axis of the axial bomax 1 and the radially inner edge of the housing web 14 rests against the bottom of the annular groove 9, so that when the Leitschaufeltrager 10 caused by an adjustment of the adjusting ring 16 axially back and forth is shifted, the Leitschaufeltrager 10 is mounted radially on the Gehausesteg 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)

Abstract

L'invention concerne une turbomachine axiale présentant une grille d'aubes mobiles, un boîtier (2) dans lequel est montée la grille d'aubes mobiles, et un support d'aubes fixes (19) qui enveloppe la grille d'aubes mobiles et est intégré au côté intérieur (3) du boîtier (2), le support d'aubes fixes (10) étant agencé directement à proximité des extrémités d'aubes (8) en formant un espace radial (12). Le support d'aubes fixes (10) est monté dans le boîtier (2) de manière à pouvoir être déplacé parallèlement à l'axe de la turbomachine axiale (1), et présente une bague de réglage (16) qui appuie sur le boîtier (2) et le support d'aubes fixes (10), au niveau de surfaces de contact, et qui peut tourner autour d'un axe de la turbomachine axiale (1). Les surfaces de contact de la bague de réglage (16) et du boîtier (2) et/ou du support d'aubes fixes (10) sont agencées selon un plan perpendiculaire à l'axe de la turbomachine axiale (1), de telle sorte que, lorsque la bague de réglage (16) est mise en rotation autour de l'axe de la turbomachine axiale (1), le support d'aubes fixes (10) puisse être déplacé axialement par la bague de réglage (16).
EP10713598.0A 2009-03-26 2010-03-22 Turbomachine axiale avec support d'aube directrice axialement mobile Not-in-force EP2411632B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PL10713598T PL2411632T3 (pl) 2009-03-26 2010-03-22 Osiowa maszyna wirnikowa z przemieszczalnym osiowo wspornikiem łopatki kierowniczej
EP10713598.0A EP2411632B1 (fr) 2009-03-26 2010-03-22 Turbomachine axiale avec support d'aube directrice axialement mobile

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09004409A EP2233701A1 (fr) 2009-03-26 2009-03-26 Turbomachine axiale avec support d'aube directrice axialement mobile
EP10713598.0A EP2411632B1 (fr) 2009-03-26 2010-03-22 Turbomachine axiale avec support d'aube directrice axialement mobile
PCT/EP2010/053663 WO2010108876A1 (fr) 2009-03-26 2010-03-22 Turbomachine axiale à support d'aubes fixes déplaçable axialement

Publications (2)

Publication Number Publication Date
EP2411632A1 true EP2411632A1 (fr) 2012-02-01
EP2411632B1 EP2411632B1 (fr) 2013-06-19

Family

ID=41327688

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09004409A Withdrawn EP2233701A1 (fr) 2009-03-26 2009-03-26 Turbomachine axiale avec support d'aube directrice axialement mobile
EP10713598.0A Not-in-force EP2411632B1 (fr) 2009-03-26 2010-03-22 Turbomachine axiale avec support d'aube directrice axialement mobile

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09004409A Withdrawn EP2233701A1 (fr) 2009-03-26 2009-03-26 Turbomachine axiale avec support d'aube directrice axialement mobile

Country Status (6)

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

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EP2623717A1 (fr) * 2012-02-02 2013-08-07 Siemens Aktiengesellschaft Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube
DE102012215413B4 (de) * 2012-08-30 2020-04-02 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine
EP2711504A1 (fr) * 2012-09-19 2014-03-26 Siemens Aktiengesellschaft Dispositif destiné au pontage d'un jeu
EP3049638B1 (fr) * 2013-09-27 2022-01-19 Raytheon Technologies Corporation Système de contrôle des jeux à réponse rapide de turbine à gaz et procédé associé
US10323536B2 (en) * 2015-04-09 2019-06-18 United Technologies Corporation Active clearance control for axial rotor systems
WO2018093429A1 (fr) * 2016-08-10 2018-05-24 In2Rbo, Inc. Compresseur radial à plusieurs étages et turbine
KR102047328B1 (ko) * 2017-12-21 2019-11-21 두산중공업 주식회사 가스터빈의 블레이드 팁 간극 제어장치
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
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

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Also Published As

Publication number Publication date
EP2411632B1 (fr) 2013-06-19
PL2411632T3 (pl) 2013-11-29
JP2012521511A (ja) 2012-09-13
EP2233701A1 (fr) 2010-09-29
JP5346118B2 (ja) 2013-11-20
CN102365426B (zh) 2015-09-02
US9057281B2 (en) 2015-06-16
WO2010108876A1 (fr) 2010-09-30
US20120076638A1 (en) 2012-03-29
CN102365426A (zh) 2012-02-29

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