EP2194234A1 - Anneau d'isolation thermique pour contrôle passif de jeu dans une turbine à gaz - Google Patents

Anneau d'isolation thermique pour contrôle passif de jeu dans une turbine à gaz Download PDF

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Publication number
EP2194234A1
EP2194234A1 EP20080020995 EP08020995A EP2194234A1 EP 2194234 A1 EP2194234 A1 EP 2194234A1 EP 20080020995 EP20080020995 EP 20080020995 EP 08020995 A EP08020995 A EP 08020995A EP 2194234 A1 EP2194234 A1 EP 2194234A1
Authority
EP
European Patent Office
Prior art keywords
heat insulating
insulating ring
gas turbine
wall portion
blade tip
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Withdrawn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
EP20080020995
Other languages
German (de)
English (en)
Inventor
Francois Dr. Benkler
Karl Dr. Klein
Torsten Matthias
Achim Schirrmacher
Oliver Dr. Schneider
Vadim Shevchenko
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 EP20080020995 priority Critical patent/EP2194234A1/fr
Priority to EP09759708.2A priority patent/EP2358979B1/fr
Priority to US13/132,126 priority patent/US20110236184A1/en
Priority to PCT/EP2009/065359 priority patent/WO2010063575A1/fr
Publication of EP2194234A1 publication Critical patent/EP2194234A1/fr
Withdrawn legal-status Critical Current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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/025—Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations
    • 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
    • F05D2230/90—Coating; Surface treatment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50211—Expansivity similar

Definitions

  • the invention relates to a heat-insulating ring for passive gap control in a gas turbine, a gas turbine blade unit for the gas turbine with the heat insulating ring and an axial compressor with at least one Verêtrnachach #2, which is designed as the Leitschaufelkranzech.
  • a gas turbine has a turbocompressor, for example, in axial construction.
  • the turbocompressor has a housing with attached stators and a rotor which is surrounded by the housing.
  • the rotor has a shaft on which the rotor is driven in rotation.
  • a shaft cover Surrounding the shaft, a shaft cover is provided whose outer contour, together with the inner contour of the housing, forms a flow channel through the turbocompressor.
  • the flow channel has a cross section which widens in the flow direction, so that the flow channel is designed as a diffuser.
  • the rotor has a plurality of rotor stages, each formed by a row of rotor blades. Further, the stator has a plurality of rows of vanes, which are arranged in the axial direction alternately arranged to the rotor blade rows. Conventionally, seen in compressors in the flow direction after the last row of rotor blades still a row of vanes and then a Nachleitschaufelsch arranged.
  • the rows of vanes have a plurality of vanes, which are fixed with their outer end respectively to the housing and point with its inner end in the direction of the shaft.
  • a blade tip is formed facing and facing the shaft cover.
  • the distance between the blade tips and the shaft cover is formed as a radial gap which is dimensioned such that on the one hand the blade tips do not abut the shaft cover during operation of the gas turbine and on the other hand the leakage flow through the radial gap that occurs during operation of the gas turbine is as low as possible. Therefore, this gap should be interpreted as low as possible, so that a high efficiency achieved and exhausted both the full blading potential of the compressor and the highest possible pressure gain in the downstream diffuser can be achieved.
  • the casing of the turbo-compressor is massively designed to withstand the pressure and temperature stresses in the operation of the gas turbine.
  • the housing is rigid, so that the load application to the housing during operation of the gas turbine has only a small deformation of the housing result.
  • the shaft cover is exposed to lower mechanical stresses during operation of the gas turbine, whereby the shaft cover is made thinner and less massive than the housing.
  • the shaft cover is formed with smaller wall thicknesses compared to the housing and typically has different material properties than the housing, the shaft cover heats up faster than the housing with the guide blade rows attached thereto. This has the consequence that when starting and stopping the gas turbine, the shaft cover and the housing have a different thermal expansion rate, so that when starting and stopping the gas turbine, the size of the radial gap changes, the radial gap when starting is temporarily smaller and larger when starting.
  • the radial gap is such dimensioned minimum height provided that in each operating state of the gas turbine - stationary and unsteady - the blade tips the wave cover almost never touch. This has the consequence that at the blade tips a correspondingly sized radial gap is maintained, which leads to a reduction of the efficiency of the gas turbine.
  • the blockage caused by the radial gap leads to a reduction of the main flow component, whereby the pressure recovery in the diffuser is reduced and disadvantageous detachment phenomena may occur.
  • the object of the invention is to provide a heat insulation ring for passive gap control in a gas turbine, a gas turbine engine blade guide unit and an axial compressor with at least one compressor follower row, which is designed as the Leitschaufelkranziki, wherein the gas turbine has a high efficiency.
  • the heat insulation ring according to the invention for passive gap control in a gas turbine which can be attached between a blade tip and a blade tip arranged opposite wall portion and on this is tuned in its heat insulating effect on the wall portion such that the radial position of the blade tip on the heat insulating ring during operation of the gas turbine via the time is essentially constant.
  • the gas turbine fan blade ring unit comprises a plurality of stator vanes mounted on the housing side and having a blade tip on the hub side, a hub side wall portion adjacent to and forming a radial gap with the blade tips, and a heat insulating ring interposed between the blade tip and the blade tip Wall section and is mounted on this, wherein the heat insulating ring is tuned in its heat insulating effect on the wall portion such that the passive Gap control of the radial gap during operation of the gas turbine over time is substantially constant.
  • the axial compressor according to the invention has at least one row of guide vanes, which is designed as the Leitschaufelkranzech.
  • the housing with the guide vane ring attached thereto and the wall section are in contact with a hot gas stream.
  • the heat insulating ring when mounted on the wall portion, causes the wall portion to be thermally insulated from the hot gas flow.
  • the heat input from the hot gas flow into the wall section is reduced with the heat insulation ring.
  • the heat input into the wall section can be determined such that both the housing with its vane ring and the wall section have a similar thermal expansion behavior.
  • the radial gap is approximately constant in its height over time, as a result of which, when the gas turbine starts up, for example, the wall section moves synchronously at a constant distance from the blade tip.
  • the radial gap can be provided with a lower height, without the blade tip abuts the heat insulation ring during operation of the gas turbine. As a result, a high reliability of the gas turbine is achieved, which has a high efficiency.
  • the heat insulation ring may be segmented by the provision of circumferential segments.
  • the heat insulating ring may have sealing elements which are provided between the peripheral segments.
  • the heat insulation ring between the peripheral segments is advantageously sealed, so that the leakage rate through the radial gap is low.
  • the heat insulating ring is attachable to the wall portion.
  • the heat insulation ring can be fastened to the wall section by means of a hooking means and / or a screwing means.
  • the Wäremeisolationsring is stably fixed to the wall portion, so that the heat insulating ring during operation of the gas turbine can not change its position relative to the wall portion.
  • a shaft cover has the wall portion. It is also preferred that with the guide vanes at least two adjacent vane rings are formed, whose radial gaps are controlled by the heat insulation ring.
  • an axial compressor 1 has a housing 2 which has a housing contour 3 on its inside. Further, the axial compressor 1 has a shaft (not shown) covered by a shaft cover 4 radially outward. Both the shaft cover 4 and the housing contour 3 form a flow channel, which is formed as a diffuser 5. In addition, the axial compressor 1 has a rotor with a rotor blading 6, wherein the rotor is rotationally rigidly connected to the shaft.
  • a stator blading 7 is provided, which is located upstream of the rotor blading 6. Downstream of the rotor blading 6, a guide grid 8 and downstream of a Nachleitgitter 9 is arranged, wherein the guide grid 8 and the Nachleitgitter 9 form the outflow region of the axial compressor 1. Both the guide grid 8 and the guide grid 9 are formed by a plurality of stator blades, which extend radially in the axial compressor 1. The stator blades have a radially outer end and a radially inner end, wherein the stator blades are attached to the housing 2 at its radially outer end.
  • a blade tip 14 is formed, which points to the center of the shaft.
  • the blade tips 14 is a non-rotatably arranged shaft cover 4 opposite, so that between the blade tips 14 and the shaft cover 4, a radial gap 10 is formed.
  • a heat insulating ring 11 is mounted on the shaft cover 4, for example, by screwing.
  • the heat insulating ring 11 extends in the axial direction of the axial compressor 1 both via the guide grid 8 as on the Nachleitgitter 9 away.
  • FIG. 2 the cut A is off Fig. 1 shown, wherein the shaft cover 4 and the heat insulating ring 11 are shown.
  • the heat insulating ring 11 is mounted on the shaft cover 4 and includes circumferentially distributed peripheral segments 12 so that the heat insulating ring 11 has a segmented structure. Between the peripheral segments 12 intermediate spaces are formed, in each of which a sealing element 13 is inserted. The sealing elements 13 are introduced braced between the peripheral segments 12.
  • the heat insulating ring 11 is made of a material and dimensioned geometrically such that in the region of the guide grid 8 and the Nachleitgitters 9, the shaft cover 4 is thermally insulated from the diffuser 9, so that the thermal expansion behavior of the shaft cover 4 approximately corresponds to the housing 2.
  • the radial gap 10 which is formed by the distance between the peripheral edge of the heat insulating ring 11, which faces the diffuser 5, and the blade tips 14, is formed to be approximately constant over time.
  • the mass flow of the leakage flow through the radial gap 10 can be reduced, so that both the efficiency of the axial compressor 1 and the pressure gain in the diffuser 5 are further improved.
  • the heat insulating ring 11 has the circumferential segments 12, so that a thermal radial expansion of the heat insulating ring 11 is prevented.
  • the vote regarding the choice of material and the geometric dimensioning of the heat insulating ring 11 with respect to the shaft cover 4 is simple.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP20080020995 2008-12-03 2008-12-03 Anneau d'isolation thermique pour contrôle passif de jeu dans une turbine à gaz Withdrawn EP2194234A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP20080020995 EP2194234A1 (fr) 2008-12-03 2008-12-03 Anneau d'isolation thermique pour contrôle passif de jeu dans une turbine à gaz
EP09759708.2A EP2358979B1 (fr) 2008-12-03 2009-11-18 Compresseur axial pour turbine a gaz, avec controle passif du jeu radial
US13/132,126 US20110236184A1 (en) 2008-12-03 2009-11-18 Axial Compressor for a Gas Turbine Having Passive Radial Gap Control
PCT/EP2009/065359 WO2010063575A1 (fr) 2008-12-03 2009-11-18 Compresseur axial pour turbine à gaz, avec contrôle passif de la fente radiale

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20080020995 EP2194234A1 (fr) 2008-12-03 2008-12-03 Anneau d'isolation thermique pour contrôle passif de jeu dans une turbine à gaz

Publications (1)

Publication Number Publication Date
EP2194234A1 true EP2194234A1 (fr) 2010-06-09

Family

ID=40802146

Family Applications (2)

Application Number Title Priority Date Filing Date
EP20080020995 Withdrawn EP2194234A1 (fr) 2008-12-03 2008-12-03 Anneau d'isolation thermique pour contrôle passif de jeu dans une turbine à gaz
EP09759708.2A Not-in-force EP2358979B1 (fr) 2008-12-03 2009-11-18 Compresseur axial pour turbine a gaz, avec controle passif du jeu radial

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP09759708.2A Not-in-force EP2358979B1 (fr) 2008-12-03 2009-11-18 Compresseur axial pour turbine a gaz, avec controle passif du jeu radial

Country Status (3)

Country Link
US (1) US20110236184A1 (fr)
EP (2) EP2194234A1 (fr)
WO (1) WO2010063575A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2474744A1 (fr) 2011-01-11 2012-07-11 Siemens Aktiengesellschaft Canal d'écoulement annulaire pour un compresseur axial
EP2703604A1 (fr) * 2012-08-30 2014-03-05 Rolls-Royce Deutschland Ltd & Co KG Module d'une turbomachine axiale et procédé de fabrication d'un tel module
DE102012215413A1 (de) * 2012-08-30 2014-03-27 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704212A1 (de) * 2010-12-15 2012-06-15 Alstom Technology Ltd Axialkompressor.
US11225907B2 (en) 2016-02-11 2022-01-18 General Electric Company Gas turbine engine pipe cover

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3056579A (en) * 1959-04-13 1962-10-02 Gen Electric Rotor construction
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
US20060292001A1 (en) * 2005-06-23 2006-12-28 Siemens Westinghouse Power Corporation Ring seal attachment system

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB902645A (en) * 1957-11-26 1962-08-09 Bristol Siddeley Engines Ltd Improvements in turbines, rotary compressors and the like
NO123552B (fr) * 1968-12-17 1971-12-06 Kongsberg Vapenfab As
US4920742A (en) * 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
US5180281A (en) * 1990-09-12 1993-01-19 United Technologies Corporation Case tying means for gas turbine engine
DE19938443A1 (de) * 1999-08-13 2001-02-15 Abb Alstom Power Ch Ag Befestigungs- und Fixierungsvorrichtung
DE19945581B4 (de) * 1999-09-23 2014-04-03 Alstom Technology Ltd. Turbomaschine
US6514041B1 (en) * 2001-09-12 2003-02-04 Alstom (Switzerland) Ltd Carrier for guide vane and heat shield segment
JP2004036443A (ja) * 2002-07-02 2004-02-05 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンシュラウド構造
DE102005015146A1 (de) * 2005-03-31 2006-10-05 Alstom Technology Ltd. Schleifbeschichtung an einem Rotor
US7445426B1 (en) * 2005-06-15 2008-11-04 Florida Turbine Technologies, Inc. Guide vane outer shroud bias arrangement

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3056579A (en) * 1959-04-13 1962-10-02 Gen Electric Rotor construction
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
US20060292001A1 (en) * 2005-06-23 2006-12-28 Siemens Westinghouse Power Corporation Ring seal attachment system

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2474744A1 (fr) 2011-01-11 2012-07-11 Siemens Aktiengesellschaft Canal d'écoulement annulaire pour un compresseur axial
WO2012095220A1 (fr) 2011-01-11 2012-07-19 Siemens Aktiengesellschaft Canal d'écoulement annulaire pour un compresseur axial
EP2703604A1 (fr) * 2012-08-30 2014-03-05 Rolls-Royce Deutschland Ltd & Co KG Module d'une turbomachine axiale et procédé de fabrication d'un tel module
DE102012215412A1 (de) * 2012-08-30 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine und Verfahren zur Herstellung einer solchen Baugruppe
DE102012215413A1 (de) * 2012-08-30 2014-03-27 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine
US9366148B2 (en) 2012-08-30 2016-06-14 Rolls-Royce Deutschland Ltd & Co Kg Assembly of an axial turbomachine and method for manufacturing an assembly of this type
DE102012215413B4 (de) * 2012-08-30 2020-04-02 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine

Also Published As

Publication number Publication date
US20110236184A1 (en) 2011-09-29
EP2358979A1 (fr) 2011-08-24
WO2010063575A1 (fr) 2010-06-10
EP2358979B1 (fr) 2015-10-28

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