EP2087208B1 - Turbomachine - Google Patents

Turbomachine Download PDF

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Publication number
EP2087208B1
EP2087208B1 EP07846281A EP07846281A EP2087208B1 EP 2087208 B1 EP2087208 B1 EP 2087208B1 EP 07846281 A EP07846281 A EP 07846281A EP 07846281 A EP07846281 A EP 07846281A EP 2087208 B1 EP2087208 B1 EP 2087208B1
Authority
EP
European Patent Office
Prior art keywords
ring
bellows
rotor
turbo
cavity
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.)
Not-in-force
Application number
EP07846281A
Other languages
German (de)
English (en)
Other versions
EP2087208B9 (fr
EP2087208A1 (fr
Inventor
Alexander Böck
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP2087208A1 publication Critical patent/EP2087208A1/fr
Publication of EP2087208B1 publication Critical patent/EP2087208B1/fr
Application granted granted Critical
Publication of EP2087208B9 publication Critical patent/EP2087208B9/fr
Not-in-force 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • 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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated
    • F05D2250/611—Structure; Surface texture corrugated undulated

Definitions

  • the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1.
  • a turbomachine including a stator and a rotor wherein the rotor includes rotor blades and the stator includes a housing and vanes.
  • the rotor-side blades form at least one blade ring, which is adjacent at a radially outer end to a radially inner housing wall of the housing, is surrounded by the same and defines a radial gap with the same.
  • the radially inner housing wall of the housing is also referred to as inner ring or shroud and serves in particular as a carrier for an inlet lining.
  • the gap between the casing ring of the housing and the radially outer end of the or each blade ring for providing a so-called Active Clearance Control can be adjusted or adjusted via adjusting devices in its gap, so as to automatically influence the gap and on all Operating conditions to ensure optimum cleavage. It is after the DE 10 2004 037 955 A1 the radially inner housing wall or the shroud segmented in the circumferential direction, wherein preferably each segment is associated with a separate adjusting device.
  • the adjusting devices are preferably designed as electro-mechanical actuators.
  • the DE 101 17 231 A1 discloses a turbomachine with a stator and a rotor, wherein the gap between radially outer ends of the blades and the radially inner housing wall by means of a pneumatic, so compressed air operated, actuator unit of a rotor gap control module can be adjusted.
  • the pneumatic actuator unit of the disclosed therein rotor gap control module has an actuator chamber, a pressure chamber and the actuator chamber and the pressure chamber connecting valves, which are inflated depending on the prevailing pressure in the actuator chamber sealing elements of the rotor gap control module, so in the sense of a pneumatic active clearance Control to adjust or adjust the gap of the gap between radially outer ends of blades and the outer ring of the housing.
  • the DE 29 22 835 C2 and the US 5,211,534 reveal further turbomachinery with a pneumatic or pneumatic Active Clearance Control.
  • the turbomachine according to DE 29 22 835 C2 via a stator and a rotor, wherein the gap between radially outer ends of the blades and an inner ring or shroud of a housing wall can be adjusted pneumatically.
  • the shroud ring is connected via resilient side walls with a support ring, wherein the shroud, the support ring and the side walls form a bellows-like structure.
  • the gap between radially outer ends of the blades and the shroud can be adjusted.
  • the flexible side walls arched several times.
  • the side walls are after the DE 29 22 835 C2 Accordingly, seen in the axial direction in sections, inwardly into the cavity and partially outwardly curved out of the cavity.
  • the document US-A-5,344,284 protects a pneumatic Active Clearance Control System with a rigid, sheet-like, circumferentially multi-segmented squelch, with each pad segment radially movable via a separate, flexible, rubber-like bellows.
  • the bellows at the upstream and downstream end simply in the cavity of the bellows in curved walls. From the vertex of the curvature to the radially inner end of the bellows wall, a sealing overlap of the bellows wall with a radially outwardly projecting edge of the rigid Anstreifbelags is present. In this area, the bellows wall in the axial direction to the outside is not or only very limited mobility.
  • the structure according to US-A-5344284 is a so-called composite consisting of bellows and shell ring without connection to benochbarten Leitschautelkränzen.
  • the present invention is based on the problem to provide a novel turbomachine with a pneumatic Active Clearance Control.
  • each wall connecting the jacket ring to the support ring is, seen in the axial direction, exclusively inwardly inward arched into the respective cavity.
  • each curved wall is designed in the manner of a toggle lever, wherein the wall sections include an obtuse angle greater than 90 ° and are suitable for receiving pressure forces.
  • Fig. 1 shows a partial cross-section through a stator of a compressor 10 of a turbomachine, wherein the stator comprises a housing 11 and a plurality of stationary vanes 12.
  • the stator-side guide vanes 12 form so-called vane rings which, viewed in the axial direction, are arranged one behind the other.
  • a total of four fixed, stator vane rings 13, 14, 15 and 16 are shown.
  • the compressor 10 comprises an in Fig. 1 Rotor, not shown, wherein the rotor of a plurality of axially arranged behind the other, not shown rotor disks is formed, each rotor disk in the circumferential direction next to each other several, also not shown blades carries.
  • the rotor blades associated, circumferentially juxtaposed blades form so-called blade rings, wherein between each two adjacent vane rings 13 and 14, 14 and 15 and 15 and 16 are each a non-illustrated blade ring is arranged.
  • the housing 11 of the stator of the compressor 10 comprises a radially inner housing wall, wherein the radially inner housing wall in the region of each rotor-side, in Fig. 1 not shown blade ring forms a so-called inner ring or shroud 17 and surrounds the respective blade ring radially on the outside.
  • the housing 11 further comprises a radially outer housing wall 18th
  • each non-illustrated, rotor-side blade ring forms the radially inner housing wall in the region of each non-illustrated, rotor-side blade ring a so-called shroud ring 17 which surrounds the blade ring radially outward.
  • shroud ring 17 which surrounds the blade ring radially outward.
  • a radial gap is formed, which is subject to considerable changes during operation of the compressor, since on the one hand the blades and the respective shrouds have a different thermal behavior and on the other hand, the blades subject to a change in length due to the centrifugal forces or centrifugal forces acting during operation.
  • the present invention now relates to such details, with the aid of which radial gaps between radially outer ends of blade rings and the respective shroud 17 can be accurately maintained.
  • Fig. 1 are the shrouds 17, which extend between the vane rings 13 and 14 and 15 and 16, connected via curved and resilient walls 19 with a support ring 20, wherein the respective support ring 20 between the respective shroud 17 and the radially outer housing wall 18 is arranged ,
  • the respective shroud 17, the support ring 20 and the between the respective shroud 17 and the respective support ring 20 extending, curved walls 19 each form a bellows-like structure 21, which has a cavity 22.
  • the respective bellows-like structure 21 and thus the cavity 22 surrounds in the circumferential direction completely and thus closed the respective blade ring.
  • the gap between the respective shroud 17 and the radially outer end of the respective blade ring is pneumatically adjustable.
  • the respective radially inner shroud 17 can be pressed radially inward and the respective radially outer support ring 20 radially outward.
  • an opposite deformation of the respective bellows-like structure 21 can be realized.
  • Fig. 1 In the preferred embodiment of Fig. 1 are the curved, elastically yielding walls 19 of the bellows-like structures 21 seen in the axial direction only curved inwardly into the respective cavity 22 into it. In the region of a vertex of the curvature wall sections of the respective wall 19 close a relatively obtuse angle ⁇ of greater than 90 °.
  • Fig. 2 shows a schematic representation of a bellows-like structure 21, described.
  • Fig. 2 shows Fig. 2 in that, in the region of a vertex 29 of the curvature, the wall sections of the respective wall 19 enclose an obtuse angle ⁇ .
  • curved walls 19 are superimposed at an increase in pressure in the corresponding cavity 22 of the respective bellows-like structure 21, two effects.
  • the respective bellows-like structure 21 has a greater radial extent than axial extent.
  • the walls 19 of the respective bellows-type structure 21 have a greater radial extent than axial extent.
  • each bellows-like structures 21 seen in the radial direction have an approximately constant wall thickness.
  • the curved walls 19 seen in the radial direction have a variable wall thickness.
  • each bellows-like structure 21 has a smaller wall thickness than the respective radially outer support ring 20.
  • the support ring 20 of each bellows-like structure 21 is therefore designed with a thicker wall thickness than the respective shroud 17. This is guaranteed in that deformation of the bellows-like structure 21 caused by variation of the pressure prevailing in the respective cavity 22 primarily acts on the shroud 17.
  • Fig. 1 can be further seen that the shroud 17 of each bellows-like structure 21 in a center region seen in the axial direction has a radially outwardly curved, projecting into the respective cavity 22 contour 23.
  • Each bellows-like structure 21 is in each case assigned at least one compressed-air line 24 in order to either introduce compressed air into the respective cavity 22 of the respective bellows-like structure 21 or to discharge it from the same compressed air.
  • a simpler representation shows Fig. 1 such a compressed-air line 24 exclusively for the bellows-like structure 21 positioned in the axial direction between the two guide-blade rings 13 and 14.
  • Each bellows-like structure 21 is assigned at least one such compressed air line 24. The more such compressed air lines 24 per bellows-like structure 21 are present, the faster compressed air can be introduced into the respective cavity 24 or derived from the same.
  • a sensor unit 25 In the embodiment of Fig. 1 is between the two Leitschaufelkränzen 13 and 14 and between the two Leitschaufelkränzen 15 and 16 each a bellows-like structure 21 arranged between the two Leitschaufelkränzen 14 and 15, however, no such bellows-like structure is present. Rather, according to Fig. 1 between the two Leitschaufelkränzen 14 and 15 and thus arranged in the region of a rotor blade ring arranged between the same, a sensor unit 25.
  • the sensor unit 25 With the sensor unit 25, at least the radial dimension of the gap between the corresponding rotor blade ring and the outer ring 17 surrounding this blade ring can be measured. Via a signal line 26, the sensor unit 25 transmits a corresponding actual value to a control device, not shown, wherein the control device compares the actual value with a desired value and depending on the pressure prevailing in the cavities 22 of the bellows structures 21 set pressure such that the actual value approaches the target value ,
  • the compressed air supply into the cavities 22 and the compressed air discharge from the cavities 22 of the bellows-like structures 21 is adjustable via individual valves, so as to adjust the pressure prevailing in the cavities 22 of the two bellows-like structures 21 pressure individually and so each Dimension of the radial gap between the shroud 17 and the corresponding blade ring depending on the respective radial extent of the blade ring individually set.
  • the compressed air supply into the cavities 22 of the bellows-like structures 21 or the Diruck povertyabschreib from the same via a common valve By different radial extensions of the respective blade rings of the compressor 10 required, different deformations of the bellows-like structures 21 are then achieved by an adapted curvature of the curved walls 19 and / or an adapted wall thickness of the curved walls 19 and / or by an adapted radial extent of the bellows-like structures 21 ,
  • the two bellows-like structures 21 are each divided by axially extending parting planes in the axial direction, wherein during manufacture, the two axial halves of the bellows-like structures 21 are welded together. Alternatively, it is also possible to divide the bellows-like structures in the radial direction.
  • Fig. 1 and 2 is in the region of each bellows-like structure 21 each wall 19 seen in the axial direction only curved inwardly into the respective cavity 22 into it.
  • the bellows-type structure 30 according to FIG. 3 has a greater axial extent than radial extent, in particular the walls 19 of the bellows-type structure 30 have a greater axial extent than radial extent.

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)

Claims (9)

  1. Turbomachine avec un stator et un rotor, le rotor comportant des aubes mobiles et le stator comportant un carter (11) et des aubes directrices (12), les aubes mobiles du côté rotor formant au moins une couronne d'aubes mobiles, la ou chaque couronne d'aubes mobiles étant adjacente avec une extrémité radialement extérieure à un anneau intérieur ou frette (17), du côté stator, du carter (11), étant entourée par celui-ci et délimitant avec celui-ci une fente, la frette (17) respective étant reliée à une couronne d'appui (20) par l'intermédiaire de parois (19) cintrées qui, conjointement avec la frette (17) et la couronne d'appui (20), délimitent une cavité (22) et forment une structure (21) du type soufflet, la fente entre la frette (17) et l'extrémité radialement extérieure de la couronne d'aubes mobiles respective pouvant être réglée par voie pneumatique sous l'effet de la variation d'une pression régnant dans la cavité (22) de la structure (21) de type soufflet respective, et chaque paroi dans la zone de la ou de chaque structure (21) de type soufflet étant, vue dans la direction axiale, cintrée exclusivement une fois vers l'intérieur de la cavité (22) respective, sachant que chaque paroi (19), avant l'action d'une surpression par rapport à l'environnement, est réalisée à la manière d'un levier coudé, sachant que dans la zone d'un sommet (29) du cintrage, des parties de la paroi (19) respective forment un angle obtus de plus de 90° et les parties de paroi étant aptes à absorber des forces de pression, caractérisée en ce que la frette (17), conjointement avec la couronne d'appui (20) et les parois cintrées (19) constituent, dans une coupe axiale-radiale, une entité intégrale qui est assemblée par conjugaison de forme, sur au moins un côté dans la zone de la frette, avec une couronne d'aubes directrices.
  2. Turbomachine selon la revendication 1, caractérisée en ce que les parois (19) ont une épaisseur constante.
  3. Turbomachine selon la revendication 1, caractérisée en ce que les parois, vues dans la direction radiale, ont une épaisseur variable.
  4. Turbomachine selon l'une quelconque des revendications 1 à 3, caractérisée en ce que dans la zone de la ou de chaque structure (21) de type soufflet, la frette (17) a une épaisseur de paroi inférieure à celle de la couronne d'appui (20).
  5. Turbomachine selon l'une quelconque des revendications 1 à 4, caractérisée en ce que dans la zone de la ou de chaque structure (21) de type soufflet, la frette (17), dans une zone médiane vue dans la direction axiale, possède un contour (23) cintré vers l'intérieur de la cavité (22).
  6. Turbomachine selon l'une quelconque des revendications 1 à 5, caractérisée en ce qu'à la ou à chaque structure de type soufflet est associée dans chaque cas au moins une conduite d'air comprimé (24), pour introduire l'air comprimé dans la cavité (22) respective et pour l'évacuer hors de celle-ci.
  7. Turbomachine selon l'une quelconque des revendications 1 à 6, caractérisée en ce que, dans chaque cas, une structure (21) de type soufflet est associée à au moins deux couronnes d'aubes mobiles, et en ce qu'entre les deux couronnes d'aubes mobiles, auxquelles est associée respectivement une structure (21) de type soufflet, est agencée au moins une couronne d'aubes mobiles à laquelle est associée une unité de détection (25), la ou chaque unité de détection (25) mesurant la dimension radiale de la fente dans la zone de la couronne d'aubes mobiles respective et transmettant une valeur réelle correspondante à un dispositif de réglage, et ledit dispositif de réglage comparant la valeur réelle à une valeur de consigne et réglant, en fonction de cela, la pression qui règne dans les cavités (22) de la structure (21) de type soufflet respective, de telle sorte que la valeur réelle s'approche de la valeur de consigne.
  8. Turbomachine selon la revendication 7, caractérisée en ce que l'admission d'air comprimé dans les cavités (22) et l'évacuation de l'air comprimé hors des cavités (22) peuvent être réglées par l'intermédiaire d'une vanne commune, sachant que différentes déformations des structures (21) de type soufflet, nécessaires en raison des différentes dimensions radiales des couronnes d'aubes mobiles respectives, peuvent être obtenues par un cintrage adapté et/ou une épaisseur de paroi adaptée des parois cintrées des structures (21) de type soufflet respectives.
  9. Turbomachine selon la revendication 7, caractérisée en ce que l'admission d'air comprimé dans les cavités (22) et l'évacuation de l'air comprimé hors des cavités (22) peuvent être réglées par l'intermédiaire de vannes individuelles, sachant que différentes déformations des structures (21) de type soufflet, nécessaires en raison des différentes dimensions radiales des couronnes d'aubes mobiles respectives, peuvent être obtenues par une admission individuelle d'air comprimé ou une évacuation individuelle d'air comprimé.
EP07846281A 2006-11-09 2007-10-30 Turbomachine Not-in-force EP2087208B9 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102006052786A DE102006052786B4 (de) 2006-11-09 2006-11-09 Turbomaschine
PCT/DE2007/001946 WO2008055474A1 (fr) 2006-11-09 2007-10-30 Turbomachine

Publications (3)

Publication Number Publication Date
EP2087208A1 EP2087208A1 (fr) 2009-08-12
EP2087208B1 true EP2087208B1 (fr) 2011-01-26
EP2087208B9 EP2087208B9 (fr) 2012-04-25

Family

ID=39167469

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07846281A Not-in-force EP2087208B9 (fr) 2006-11-09 2007-10-30 Turbomachine

Country Status (6)

Country Link
US (1) US8608435B2 (fr)
EP (1) EP2087208B9 (fr)
AT (1) ATE497088T1 (fr)
CA (1) CA2666200A1 (fr)
DE (2) DE102006052786B4 (fr)
WO (1) WO2008055474A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2218880A1 (fr) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Système de contrôle actif de jeu pour turbine à gaz
FR3024492B1 (fr) * 2014-07-29 2019-08-23 Safran Aircraft Engines Element comprenant un stator et un rotor de turbomachine avec un joint d'etancheite et test de ce joint
US10794213B2 (en) * 2016-06-21 2020-10-06 Rolls-Royce North American Technologies Inc. Blade tip clearance control for an axial compressor with radially outer annulus
US10851712B2 (en) 2017-06-27 2020-12-01 General Electric Company Clearance control device

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2922835C2 (de) 1979-06-06 1985-06-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Umfangsspaltdichtung an Axialströmungsmaschinen
US4329114A (en) * 1979-07-25 1982-05-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active clearance control system for a turbomachine
JPS5741407A (en) * 1980-08-22 1982-03-08 Hitachi Ltd Sealing mechanism on top of turbine rotor blade
GB2103294B (en) * 1981-07-11 1984-08-30 Rolls Royce Shroud assembly for a gas turbine engine
JPS5820904A (ja) * 1981-07-29 1983-02-07 Hitachi Ltd ガスタ−ビン動翼先端シ−ル構造
GB2169962B (en) * 1985-01-22 1988-07-13 Rolls Royce Blade tip clearance control
JPS62142808A (ja) * 1985-12-18 1987-06-26 Toshiba Corp ガスタ−ビンの間隙制御装置
US4784569A (en) * 1986-01-10 1988-11-15 General Electric Company Shroud means for turbine rotor blade tip clearance control
GB2195715B (en) * 1986-10-08 1990-10-10 Rolls Royce Plc Gas turbine engine rotor blade clearance control
DE3830762C2 (de) * 1988-09-09 1994-08-18 Mtu Muenchen Gmbh Einrichtung zur Halterung eines Mantelringes in Gasturbinen
US5048288A (en) * 1988-12-20 1991-09-17 United Technologies Corporation Combined turbine stator cooling and turbine tip clearance control
US4971517A (en) * 1988-12-27 1990-11-20 Allied-Signal Inc. Turbine blade clearance controller
GB9103809D0 (en) * 1991-02-23 1991-04-10 Rolls Royce Plc Blade tip clearance control apparatus
US5344284A (en) * 1993-03-29 1994-09-06 The United States Of America As Represented By The Secretary Of The Air Force Adjustable clearance control for rotor blade tips in a gas turbine engine
DE10117231A1 (de) 2001-04-06 2002-10-31 Hodson Howard Rotorspalt-Steuermodul
US6918743B2 (en) * 2002-10-23 2005-07-19 Pratt & Whitney Canada Ccorp. Sheet metal turbine or compressor static shroud
DE102004037955A1 (de) 2004-08-05 2006-03-16 Mtu Aero Engines Gmbh Turbomaschine, insbesondere Gasturbine

Also Published As

Publication number Publication date
WO2008055474A1 (fr) 2008-05-15
DE102006052786B4 (de) 2011-06-30
EP2087208B9 (fr) 2012-04-25
EP2087208A1 (fr) 2009-08-12
ATE497088T1 (de) 2011-02-15
US20100003122A1 (en) 2010-01-07
DE102006052786A1 (de) 2008-05-15
CA2666200A1 (fr) 2008-05-15
DE502007006392D1 (de) 2011-03-10
US8608435B2 (en) 2013-12-17

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