EP3421727B1 - Gas turbine comprising a turbine vane carrier - Google Patents

Gas turbine comprising a turbine vane carrier Download PDF

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Publication number
EP3421727B1
EP3421727B1 EP17179138.7A EP17179138A EP3421727B1 EP 3421727 B1 EP3421727 B1 EP 3421727B1 EP 17179138 A EP17179138 A EP 17179138A EP 3421727 B1 EP3421727 B1 EP 3421727B1
Authority
EP
European Patent Office
Prior art keywords
casing
front ring
gas turbine
turbine
vane carrier
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.)
Active
Application number
EP17179138.7A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3421727A1 (en
Inventor
Meisam Sistaninia
Tobias Herzog
Philippe LOTT
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland 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 Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP17179138.7A priority Critical patent/EP3421727B1/en
Priority to CN201810705835.5A priority patent/CN109209516B/zh
Publication of EP3421727A1 publication Critical patent/EP3421727A1/en
Application granted granted Critical
Publication of EP3421727B1 publication Critical patent/EP3421727B1/en
Active 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F01D25/265—Vertically split casings; Clamping arrangements therefor
    • 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
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2260/30—Retaining components in desired mutual position

Definitions

  • the present invention relates to a gas turbine for power plants.
  • the present invention relates to the turbine vane carrier configured for supporting a plurality of vanes interposed between a plurality of blades supported by the rotor.
  • a gas turbine for power plant (in the following only gas turbine) comprises a rotor having an axis and is provided with an upstream compressor sector, a combustor sector and a downstream turbine sector.
  • the terms downstream and upstream refer to the direction of the main gas flow passing through the gas turbine whereas the terms radial, axial, circumferential, inner/inward and outer/outward refer to the gas turbine axis.
  • the compressor sector comprises an inlet supplied with air and a plurality of blades connected to the rotor and configured for compressing the incoming air. The compressed air leaving the compressor flows into a plenum delimited by an outer casing and from there enters into the combustor.
  • the compressed air is mixed with at least one fuel and such resulting mixture of fuel and compressed air flows into a combustion chamber where this mixture is combusted.
  • the resulting hot gas leaves the combustion chamber and expands in the turbine performing work on the rotor.
  • the turbine comprises a plurality of blades supported by the rotor and an outer vane carrier surrounding the rotor and supporting a plurality of vanes axially interposed between the blades.
  • the vane carrier comprises a casing having an upstream end facing the combustor plenum and a downstream end at the last blade.
  • EP2196628 discloses in fig. 3 a vane carrier for gas or steam turbines, the carrier comprising a casing formed by an upstream inner section and a downstream outer section consisting of different materials and interconnected by dovetail couplings.
  • EP3023600 discloses a vane carrier provided with a cooling bore.
  • EP2423454 refers to a double steam turbine having an inner casing formed by three axially spaced sections consisting of different materials and interconnected by shrinking via hook-type connections.
  • WO2007068538 refers to a gas turbine having a carrier element and a lining element that is connected to the carrier element and configured for acting as a heat shield.
  • EP2634373 refers to a turbomachine having a stator ring for securing the vane carrier.
  • US2013149123 refers to a gas turbine comprising a vane carrier supporting a plurality of vanes.
  • a primary object of the present invention is to provide a gas turbine for power plants able to overcome the above described problems of the current state of the art.
  • primary object of the present invention is to provide a turbine vane carrier suitable for reducing the distortion of the part due to the temperature gradient between the upstream portion in contact with the combustor plenum and the downstream portion.
  • the present invention provides a gas turbine as defined in claim 1, having an axis and comprising (following the main gas flow direction) a compressor, a combustor and at least a turbine.
  • the gas turbine moreover comprises an outer casing defining a plenum fed by the compressed air leaving the compressor.
  • the combustor is at least in part housed in the plenum.
  • the outer casing is provided with a plurality of portal holes for supporting a plurality of can-combustors concentrically arranged around the axis of the gas turbine.
  • the turbine Downstream the combustor, the turbine comprises an inner rotor provided with a plurality of blades and an outer vane carrier provided with a plurality of vanes axially interposed between the blades.
  • the vane carrier comprises a casing having an upstream end supporting the first vane and located near the combustor plenum and an opposite downstream end at the last blade.
  • the vane carrier moreover comprises a circumferential front ring centered at the gas turbine axis and coupled to the upstream end of the casing.
  • the front portion of the turbine vane carrier is mechanically separated from the remaining part of the casing.
  • the hotter portion of the vane carrier is separated from the cooler portion and therefore each portion is free to deform independent from the other according to the local temperature. This configuration allows reducing the distortion of the vane carrier.
  • the front part of the vane carrier is made as a separated piece with respect to the remaining part of the casing, such front ring can be made by a particular material that is too expensive for realizing the entire vane carrier.
  • the front ring could be made by a so called “low thermal expansion material” or low “CTE” (coefficient of Thermal expansion) that allows to better control the clearances between the front ring and the casing.
  • CTE coefficient of Thermal expansion
  • the front ring is coupled to the upstream end of the casing by a circumferential rail coupling.
  • a circumferential rail coupling Preferably, at such circumferential rail coupling gaps are present between the casing and the front ring.
  • the front ring can freely deform within the rail gaps before coming into contact with the casing.
  • the circumferential rail coupling is realized in form of a single rail and configured to limit only the radial inward displacement of the front ring with respect to the casing.
  • the front ring can freely deform along radial outward direction.
  • the circumferential front ring comprises two halves bolted at the relative split line and no gap is provided at the split line.
  • the vane carrier moreover comprises a plurality of axial supports protruding from the upstream end of the casing and housed in relative seats in the front ring.
  • the axial supports avoid the decoupling of front ring from the casing during the assembly of the vane carrier.
  • the gas turbine comprises a device for cooling the casing downstream the front ring.
  • the casing comprises an inner and an outer surface; downstream the upstream end the outer surface of the casing is provided with at least a bore fed by cooling air.
  • This embodiment can be considered as an alternative of the embodiment where the front ring is realized in low CTE alloy.
  • the rail coupling is configured to allow a free radial inner displacement of the front ring with respect to the casing.
  • the present invention allow to better control the thermal expansion/contraction of the casing that indeed is no more integral with the hot part facing the combustor plenum.
  • the invention has been above foregoing defined as a gas turbine comprising the inventive turbine vane carrier with a separated front ring.
  • the present invention relates moreover to the single turbine vane carrier. Indeed, this element can be integrated with current gas turbines in order to reach to the claimed solution.
  • Fig. 1 is a schematic view of a gas turbine for a power plant.
  • the gas turbine 1 has an axis 7 and comprises a compressor 2, a combustor 3 and a turbine 5.
  • the incoming air is compressed by the compressor 2 and then enters into a plenum (not shown in figure 1 ) defined by an outer casing of the gas turbine. From the plenum the compressed air enters the combustor 3.
  • the air is mixed with at least a fuel and this mixture is combusted.
  • the hot gas leaving the combustor stage 3 is expanded in the turbine 5 performing work on the rotor 4 along the axis 7.
  • Fig. 2 is a schematic prospective view of the turbine of figure 1 .
  • the turbine comprises a rotor 4 along the axis 7 provided with a plurality of blades 6.
  • a turbine vane carrier 9 is provided around the rotor 4 .
  • This vane carrier 9 supports a plurality of vanes 8 and comprises a casing 10 and a front ring 13 coupled to the upstream portion 11 of the casing 10. Both the front ring 13 and the casing 10 are realized in two halves bolted each other at a split line 18.
  • Fig. 3 is a schematic sectional view of the turbine section of figure 2 .
  • the casing 10 comprises an inner 15 and outer surface 16 connecting the upstream portion 11 with the downstream portion 12.
  • the inner surface 15 supports a plurality of vanes 8 interposed by the rotor blades 6.
  • the front ring 13 is not integral with the casing 9 and is coupled to the upstream portion 11 by a circumferential rail coupling 14 centered at the axis 7.
  • Figure 3 discloses moreover a bore 17 realized in the outer surface of the casing 10 and configured for receiving cooling air.
  • the reference M in figure 3 represent the main flow direction of the hot gas.
  • the front ring 13 may be realized by conventional alloy and it ends substantially at the first vane.
  • FIG. 4 is a schematic enlarged view of a particular of figure 3 .
  • figure 4 discloses the circumferential rail coupling 14 between the front ring 13 and the upstream portion 10 of the casing 9.
  • the front ring 13 comprises a hook portion 19 oriented toward the axis 7 and housed in a corresponding seat 20 obtained in the outer surface 16 of the casing 10.
  • Fig. 5 is a schematic sectional view of an alternative example of the turbine section of figure 2 and does not form part of the invention.
  • the casing 9 is not provided with the cooling bore but the front ring 13 is realized by a low CTE (coefficient of Thermal expansion) alloys.
  • the front ring 13 ends substantially at the middle of the vane carrier 9.
  • the rail coupling is configured to limit the radial outward displacement and to allow the radial inward displacement of the front ring 13 with respect to the casing 10.
  • the front ring made of low CTE material expands less than the remaining part of the casing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17179138.7A 2017-06-30 2017-06-30 Gas turbine comprising a turbine vane carrier Active EP3421727B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17179138.7A EP3421727B1 (en) 2017-06-30 2017-06-30 Gas turbine comprising a turbine vane carrier
CN201810705835.5A CN109209516B (zh) 2017-06-30 2018-06-29 燃气涡轮的涡轮导叶载体和包括涡轮导叶载体的燃气涡轮

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17179138.7A EP3421727B1 (en) 2017-06-30 2017-06-30 Gas turbine comprising a turbine vane carrier

Publications (2)

Publication Number Publication Date
EP3421727A1 EP3421727A1 (en) 2019-01-02
EP3421727B1 true EP3421727B1 (en) 2020-01-29

Family

ID=59269943

Family Applications (1)

Application Number Title Priority Date Filing Date
EP17179138.7A Active EP3421727B1 (en) 2017-06-30 2017-06-30 Gas turbine comprising a turbine vane carrier

Country Status (2)

Country Link
EP (1) EP3421727B1 (zh)
CN (1) CN109209516B (zh)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7341969B2 (ja) * 2020-09-30 2023-09-11 三菱重工業株式会社 タービンの設計及び製造方法

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1960636B1 (de) * 2005-12-14 2016-01-27 Alstom Technology Ltd Strömungsmaschine
EP2196628A1 (de) * 2008-12-10 2010-06-16 Siemens Aktiengesellschaft Leitschaufelträger
DE102009009129B4 (de) * 2009-02-17 2022-11-03 BMTS Technology GmbH & Co. KG Turbolader mit variabler Turbinengeometrie
EP2423454A1 (de) * 2010-08-25 2012-02-29 Siemens Aktiengesellschaft Gehäuse für Strömungsmaschine sowie Verfahren zur Herstellung
US9157331B2 (en) * 2011-12-08 2015-10-13 Siemens Aktiengesellschaft Radial active clearance control for a gas turbine engine
EP2634373A1 (en) * 2012-02-28 2013-09-04 Siemens Aktiengesellschaft Arrangement for a turbomachine
EP2949873A1 (en) * 2014-05-27 2015-12-02 Siemens Aktiengesellschaft Turbomachine with an ingestion shield and use of the turbomachine
EP3023600B1 (en) * 2014-11-24 2018-01-03 Ansaldo Energia IP UK Limited Engine casing element
US10233844B2 (en) * 2015-05-11 2019-03-19 General Electric Company System for thermally shielding a portion of a gas turbine shroud assembly
CN204851337U (zh) * 2015-05-19 2015-12-09 北京华清燃气轮机与煤气化联合循环工程技术有限公司 一种燃气轮机透平

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
CN109209516B (zh) 2022-11-04
CN109209516A (zh) 2019-01-15
EP3421727A1 (en) 2019-01-02

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