IN2014DN03773A - - Google Patents

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Publication number
IN2014DN03773A
IN2014DN03773A IN3773DEN2014A IN2014DN03773A IN 2014DN03773 A IN2014DN03773 A IN 2014DN03773A IN 3773DEN2014 A IN3773DEN2014 A IN 3773DEN2014A IN 2014DN03773 A IN2014DN03773 A IN 2014DN03773A
Authority
IN
India
Prior art keywords
combustion chamber
turbine
contour
conical contour
thermal expansion
Prior art date
Application number
Inventor
Remigi Tschuor
Sinisa Narancic
Guenter Filkorn
Original Assignee
Alstom Technology Ltd
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 Alstom Technology Ltd filed Critical Alstom Technology Ltd
Publication of IN2014DN03773A publication Critical patent/IN2014DN03773A/en

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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
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

A gas turbine (10) comprises a compressor (12), an annular combustion chamber (13), and a turbine (15), a combustion chamber shell (20a) of the combustion chamber (13) adjoining the turbine inlet (26) in a transition region (A) in order to introduce the hot gases generated in the combustion chamber (13) into the downstream turbine (15) such that a thermal expansion-induced relative movement between the combustion chamber (13) and the turbine inlet (26) is possible. Combustion chamber shell (20a) support elements (29) distributed on the periphery come into contact with a conical contour (31a) on the shaft cover (25) due to the thermal expansion (33) that occurs during operation and are supported on said contour. The aim of the invention is an improvement with respect to loading and service life. This is achieved in that the conical contour (31a) and the machine axis form an angle (a2) that allows the combustion chamber shell (20a) support elements (29) to slide onto the conical contour (31a) .
IN3773DEN2014 2011-10-24 2012-10-23 IN2014DN03773A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP11186387 2011-10-24
PCT/EP2012/070930 WO2013060663A2 (en) 2011-10-24 2012-10-23 Gas turbine

Publications (1)

Publication Number Publication Date
IN2014DN03773A true IN2014DN03773A (en) 2015-07-10

Family

ID=47045047

Family Applications (1)

Application Number Title Priority Date Filing Date
IN3773DEN2014 IN2014DN03773A (en) 2011-10-24 2012-10-23

Country Status (7)

Country Link
US (1) US9708920B2 (en)
EP (1) EP2852735B1 (en)
KR (1) KR101613096B1 (en)
CN (1) CN104246373B (en)
IN (1) IN2014DN03773A (en)
RU (1) RU2597350C2 (en)
WO (1) WO2013060663A2 (en)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ES2637944T3 (en) * 2014-06-06 2017-10-18 MTU Aero Engines AG Arrangement of the components of a gas turbine
EP2998517B1 (en) * 2014-09-16 2019-03-27 Ansaldo Energia Switzerland AG Sealing arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement
EP3287610B1 (en) * 2016-08-22 2019-07-10 Ansaldo Energia Switzerland AG Gas turbine transition duct
US10697634B2 (en) 2018-03-07 2020-06-30 General Electric Company Inner cooling shroud for transition zone of annular combustor liner
US20220336123A1 (en) * 2019-09-24 2022-10-20 Ls Electric Co., Ltd. Cooling apparatus for superconductor cooling container
EP3835657A1 (en) * 2019-12-10 2021-06-16 Siemens Aktiengesellschaft Combustion chamber with wall cooling
CN112377946B (en) * 2020-11-16 2022-02-11 四川航天中天动力装备有限责任公司 Large bent pipe structure of axial floating type backflow annular combustion chamber

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Also Published As

Publication number Publication date
US20140223921A1 (en) 2014-08-14
CN104246373B (en) 2016-06-08
EP2852735A2 (en) 2015-04-01
KR20140077978A (en) 2014-06-24
US9708920B2 (en) 2017-07-18
EP2852735B1 (en) 2016-04-27
RU2014120759A (en) 2015-12-10
RU2597350C2 (en) 2016-09-10
WO2013060663A3 (en) 2015-02-26
CN104246373A (en) 2014-12-24
WO2013060663A2 (en) 2013-05-02
KR101613096B1 (en) 2016-04-20

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