EP2358979A1 - Axial compressor for a gas turbine having passive radial gap control - Google Patents
Axial compressor for a gas turbine having passive radial gap controlInfo
- Publication number
- EP2358979A1 EP2358979A1 EP09759708A EP09759708A EP2358979A1 EP 2358979 A1 EP2358979 A1 EP 2358979A1 EP 09759708 A EP09759708 A EP 09759708A EP 09759708 A EP09759708 A EP 09759708A EP 2358979 A1 EP2358979 A1 EP 2358979A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- heat insulation
- wall portion
- axial compressor
- vane
- guide
- 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
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
- F01D11/001—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 an axial compressor for a gas turbine with passive radial gap control, with at least one fixed to a vane carrier vane ring, each having a plurality of vanes, the blade tips each under
- 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 formed facing the shaft cover and opposite.
- 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 in the operation of the gas turbine to the
- the casing of the turbo-compressor is massively designed to withstand the pressure and temperature stresses in the operation of the gas turbine. Furthermore, 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. In contrast, the
- 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.
- 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 is temporarily smaller when starting and larger when starting.
- the radial gap is provided with a minimum height dimensioned such that in each operating state of the gas turbine - stationary and unsteady - the blade tips almost never touch the shaft cover. 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 to provide an axial compressor for a gas turbine with a passive radial gap control, which has a high efficiency is achieved with such having the features of claim 1.
- the axial compressor according to the invention with at least one vane ring fastened to a vane carrier, which has a plurality of vanes whose vane tips face each other on the hub side with respect to the vane carrier thermally faster responding wall portion forming a radial gap has a heat insulation at the blade tip immediately opposite wall portion, the tuned in its batheintragverzögerungs Koch on the wall portion and the vane support such that the thermal expansion behavior of Leitschaufelani and wall portion during transient operation of the axial compressor over time at least equal, preferably almost identical.
- the heat insulation when mounted on the wall portion, causes the wall portion to be thermally insulated from the hot gas flow. Since no cooling of the wall portion provided, the wall portion with heat insulation portion in the later-adjusting stationary state will assume the same temperature as a wall portion without heat insulation portion. As a result, with the heat insulation, the heat input from the hot gas flow into the wall section is only delayed.
- 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 over time and not a time-varying manner as in the prior art.
- the radial gap in its height over time is approximately constant, which moves approximately synchronously when approaching a still cold gas turbine, the wall portion at a constant distance from the blade tip.
- the radial gap can be designed with a lower height without the blade tip abutting the heat insulation 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 can be performed by the provision of circumferential segments segmented annular.
- the heat insulation may comprise sealing elements which are provided between the peripheral segments.
- the gaps between the peripheral segments are advantageously sealed, so that the leakage rate through the radial gap is low.
- the heat insulation can be fastened to the wall section. It is further preferred that the heat insulation can be fastened as a ring on the wall section by means of a hooking means and / or a screwing means.
- the heat insulation can be fixed stably to the wall section, so that the heat insulation during operation of the gas turbine can not change its position relative to the wall section.
- the heat insulation can also be formed from a heat protection layer applied to the wall section, which is preferably ceramic. A simple production and simple attachment is thus given, even for already operationally used axial compressor.
- 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 influenced by the heat insulation.
- vanes do not have to be on a separate
- the guide vanes can be fastened directly to a housing of the axial compressor, which as a rule is also thicker than the relevant wall section.
- Fig. 2 shows the section A of Fig. 1 and
- FIG. 3 is a longitudinal section of FIG. 1 with an alternative embodiment of an axial compressor according to the invention.
- 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 is 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.
- At the radial inside a respective blade tip 14 is formed, which faces 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 insulation 11 is attached as a heat insulating ring 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.
- 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 formed from the distance between the peripheral edge of the heat insulating ring heat insulation 11 facing the diffuser 5 and the blade tips 14 becomes approximately constant over time.
- the radial gap 10 can be made smaller than would be necessary if the heat insulating ring 11 would not have been provided on the shaft cover 4 and abutment of the blade tips 14 are prevented on the shaft cover 4 should.
- 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.
- FIG. 3 shows how Fig. 1 shows a longitudinal section through a portion of the gas turbine, wherein in Fig. 3 to Fig. 1 identical components are provided with the same reference numerals.
- the heat insulation ring 11 formed from peripheral segments 12 shown in FIG. 1, however, is replaced by an equivalent solution to FIG. 1 by a heat protection layer 15 applied directly to the wall section 4.
- the thermal insulation layer is, for example, a conventional one ceramic thermal barrier coating.
- the invention relates to an axial compressor 1 for a gas turbine with passive radial gap control comprising a guide vane on which in a ring 8, 9 arranged vanes are fixed, the blade tips 14 a wall portion 4 opposite.
- a thermal insulation ring 11 is mounted in the section opposite the blade tips 14 for equalizing the expansion behavior of the guide blade carrier and the wall section 4, which thermally react differently per se, which in its heat input delay effect on the wall section 4 and on the guide vane carrier tuned such that the thermal expansion behavior of vane support and wall section 4 during transient operation of the axial compressor 1 over time is at least equalized.
- the alignment prevents contact between the blade tips 14 and the wall section 4, which could hitherto occur during transient operation or, in particular, after the cold start. By aligning can be achieved at best that the radial position of the blade tip 14 relative to the heat insulating ring 11 during operation of the axial compressor 1 over time is substantially constant.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP09759708.2A EP2358979B1 (en) | 2008-12-03 | 2009-11-18 | Axial compressor for a gas turbine having passive radial gap control |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP20080020995 EP2194234A1 (en) | 2008-12-03 | 2008-12-03 | Thermal insulation ring for passive clearance control in a gas turbine |
PCT/EP2009/065359 WO2010063575A1 (en) | 2008-12-03 | 2009-11-18 | Axial compressor for a gas turbine having passive radial gap control |
EP09759708.2A EP2358979B1 (en) | 2008-12-03 | 2009-11-18 | Axial compressor for a gas turbine having passive radial gap control |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2358979A1 true EP2358979A1 (en) | 2011-08-24 |
EP2358979B1 EP2358979B1 (en) | 2015-10-28 |
Family
ID=40802146
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20080020995 Withdrawn EP2194234A1 (en) | 2008-12-03 | 2008-12-03 | Thermal insulation ring for passive clearance control in a gas turbine |
EP09759708.2A Not-in-force EP2358979B1 (en) | 2008-12-03 | 2009-11-18 | Axial compressor for a gas turbine having passive radial gap control |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20080020995 Withdrawn EP2194234A1 (en) | 2008-12-03 | 2008-12-03 | Thermal insulation ring for passive clearance control in a gas turbine |
Country Status (3)
Country | Link |
---|---|
US (1) | US20110236184A1 (en) |
EP (2) | EP2194234A1 (en) |
WO (1) | WO2010063575A1 (en) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH704212A1 (en) * | 2010-12-15 | 2012-06-15 | Alstom Technology Ltd | Axial Compressor. |
EP2474744A1 (en) | 2011-01-11 | 2012-07-11 | Siemens Aktiengesellschaft | Annular flow channel for an axial compressor |
DE102012215413B4 (en) * | 2012-08-30 | 2020-04-02 | Rolls-Royce Deutschland Ltd & Co Kg | Assembly of an axial turbo machine |
DE102012215412A1 (en) * | 2012-08-30 | 2014-03-06 | Rolls-Royce Deutschland Ltd & Co Kg | Assembly of an axial turbomachine and method for producing such an assembly |
US11225907B2 (en) | 2016-02-11 | 2022-01-18 | General Electric Company | Gas turbine engine pipe cover |
Family Cites Families (14)
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 |
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 |
NO123552B (en) * | 1968-12-17 | 1971-12-06 | Kongsberg Vapenfab As | |
US4411594A (en) * | 1979-06-30 | 1983-10-25 | Rolls-Royce Limited | Support member and a component supported thereby |
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 (en) * | 1999-08-13 | 2001-02-15 | Abb Alstom Power Ch Ag | Fastening and fixing device |
DE19945581B4 (en) * | 1999-09-23 | 2014-04-03 | Alstom Technology Ltd. | turbomachinery |
US6514041B1 (en) * | 2001-09-12 | 2003-02-04 | Alstom (Switzerland) Ltd | Carrier for guide vane and heat shield segment |
JP2004036443A (en) * | 2002-07-02 | 2004-02-05 | Ishikawajima Harima Heavy Ind Co Ltd | Gas turbine shroud structure |
DE102005015146A1 (en) * | 2005-03-31 | 2006-10-05 | Alstom Technology Ltd. | Frictional coating for use in e.g. turbine, has coating material and several frictional lines made of coating material, where lines are arranged distributed in circumferential direction |
US7445426B1 (en) * | 2005-06-15 | 2008-11-04 | Florida Turbine Technologies, Inc. | Guide vane outer shroud bias arrangement |
US7494317B2 (en) * | 2005-06-23 | 2009-02-24 | Siemens Energy, Inc. | Ring seal attachment system |
-
2008
- 2008-12-03 EP EP20080020995 patent/EP2194234A1/en not_active Withdrawn
-
2009
- 2009-11-18 EP EP09759708.2A patent/EP2358979B1/en not_active Not-in-force
- 2009-11-18 US US13/132,126 patent/US20110236184A1/en not_active Abandoned
- 2009-11-18 WO PCT/EP2009/065359 patent/WO2010063575A1/en active Application Filing
Non-Patent Citations (1)
Title |
---|
See references of WO2010063575A1 * |
Also Published As
Publication number | Publication date |
---|---|
WO2010063575A1 (en) | 2010-06-10 |
EP2358979B1 (en) | 2015-10-28 |
EP2194234A1 (en) | 2010-06-09 |
US20110236184A1 (en) | 2011-09-29 |
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