IN2014DN03773A - - Google Patents

Download PDF

Info

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

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
    • 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)

Families Citing this family (7)

* 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
WO2021060831A1 (en) * 2019-09-24 2021-04-01 엘에스일렉트릭(주) 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

Family Cites Families (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2592060A (en) * 1946-03-25 1952-04-08 Rolls Royce Mounting of combustion chambers in jet-propulsion and gas-turbine power-units
GB638807A (en) * 1948-07-12 1950-06-14 Havilland Engine Co Ltd Improvements in or relating to gas turbines
GB1010338A (en) * 1962-09-11 1965-11-17 Lucas Industries Ltd Means for supporting the downstream end of a combustion chamber in a gas turbine engine
DE1186275B (en) * 1963-07-04 1965-01-28 Daimler Benz Ag Arrangement of the flame chamber of annular combustion chambers for gas turbine engines
US3481146A (en) * 1967-12-28 1969-12-02 Lucas Industries Ltd Combustion apparatus for gas turbine engines
US3670467A (en) 1970-04-27 1972-06-20 Robert H Walker Method and apparatus for manufacturing tumbling media
US3670497A (en) * 1970-09-02 1972-06-20 United Aircraft Corp Combustion chamber support
US3928963A (en) * 1974-11-04 1975-12-30 Gen Motors Corp Cast in place gas turbine containment ring and method of manufacture
GB2102897B (en) * 1981-07-27 1985-06-19 Gen Electric Annular seals
US4821522A (en) * 1987-07-02 1989-04-18 United Technologies Corporation Sealing and cooling arrangement for combustor vane interface
FR2624953B1 (en) * 1987-12-16 1990-04-20 Snecma COMBUSTION CHAMBER FOR TURBOMACHINES HAVING A DOUBLE WALL CONVERGENT
US5271714A (en) * 1992-07-09 1993-12-21 General Electric Company Turbine nozzle support arrangement
US5265412A (en) * 1992-07-28 1993-11-30 General Electric Company Self-accommodating brush seal for gas turbine combustor
GB2328011A (en) * 1997-08-05 1999-02-10 Europ Gas Turbines Ltd Combustor for gas or liquid fuelled turbine
US6098397A (en) * 1998-06-08 2000-08-08 Caterpillar Inc. Combustor for a low-emissions gas turbine engine
ES2295164T3 (en) * 2000-03-22 2008-04-16 Siemens Aktiengesellschaft PROCEDURE TO REMOVE A MEANS OF OBTURATION.
US6334310B1 (en) * 2000-06-02 2002-01-01 General Electric Company Fracture resistant support structure for a hula seal in a turbine combustor and related method
IT1317978B1 (en) 2000-06-16 2003-07-21 Nuovo Pignone Spa TRANSITION PIECE FOR COMBUSTION CHAMBERS OF NONANULAR GAS TURBINES.
SE520594C2 (en) * 2000-09-29 2003-07-29 Turbec Ab Burner chamber for a heat engine unit
US6442946B1 (en) * 2000-11-14 2002-09-03 Power Systems Mfg., Llc Three degrees of freedom aft mounting system for gas turbine transition duct
US6450762B1 (en) * 2001-01-31 2002-09-17 General Electric Company Integral aft seal for turbine applications
US6860108B2 (en) * 2003-01-22 2005-03-01 Mitsubishi Heavy Industries, Ltd. Gas turbine tail tube seal and gas turbine using the same
US7152411B2 (en) * 2003-06-27 2006-12-26 General Electric Company Rabbet mounted combuster
US7178340B2 (en) * 2003-09-24 2007-02-20 Power Systems Mfg., Llc Transition duct honeycomb seal
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly
FR2871847B1 (en) * 2004-06-17 2006-09-29 Snecma Moteurs Sa MOUNTING A TURBINE DISPENSER ON A COMBUSTION CHAMBER WITH CMC WALLS IN A GAS TURBINE
WO2006059979A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral case, vane, mount, and mixer
US7082766B1 (en) * 2005-03-02 2006-08-01 General Electric Company One-piece can combustor
US7726114B2 (en) * 2005-12-07 2010-06-01 General Electric Company Integrated combustor-heat exchanger and systems for power generation using the same
US7604456B2 (en) * 2006-04-11 2009-10-20 Siemens Energy, Inc. Vane shroud through-flow platform cover
US7762766B2 (en) * 2006-07-06 2010-07-27 Siemens Energy, Inc. Cantilevered framework support for turbine vane
WO2009103658A1 (en) * 2008-02-20 2009-08-27 Alstom Technology Ltd Gas turbine having an annular combustion chamber
EP2242916B1 (en) * 2008-02-20 2015-06-24 Alstom Technology Ltd Gas turbine
EP2249003B1 (en) * 2008-02-27 2016-11-02 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine
US8534076B2 (en) * 2009-06-09 2013-09-17 Honeywell Internationl Inc. Combustor-turbine seal interface for gas turbine engine
US8347636B2 (en) * 2010-09-24 2013-01-08 General Electric Company Turbomachine including a ceramic matrix composite (CMC) bridge
US20150167979A1 (en) * 2013-12-17 2015-06-18 General Electric Company First stage nozzle or transition nozzle configured to promote mixing of respective combustion streams downstream thereof before entry into a first stage bucket of a turbine
US10309652B2 (en) * 2014-04-14 2019-06-04 Siemens Energy, Inc. Gas turbine engine combustor basket with inverted platefins

Also Published As

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

Similar Documents

Publication Publication Date Title
IN2014DN03773A (en)
US9109510B2 (en) Gas turbine engine bearing support strut
RU2435039C2 (en) Case for turbine, turbine and turbo-machine containing such turbine
US8944756B2 (en) Blade outer air seal assembly
US10533444B2 (en) Turbine shroud sealing architecture
US10724404B2 (en) Vane, gas turbine, ring segment, remodeling method for vane, and remodeling method for ring segment
RU2548535C2 (en) Insulation of circular protruding edge of external turbomachine casing in respect to relevant annular sector, turbomachine stage and turbomachine
SG130185A1 (en) Sacrificial inner shroud liners for gas turbine engines
CA2624425A1 (en) Ring seal system with reduced cooling requirements
RU2014113393A (en) ASSEMBLY FORMED BY THE TURBINE GUIDING NOZZLE DEVICE OR THE KKM COMPRESSOR REDUCING DEVICE FOR THE TURBO MACHINE AND THE RING - SUBSTRATE FOR THE WIPEABLE MATERIAL, AND THE TURBISHER IS COMPLETE
RU2012130351A (en) TURBINE STEP IN A TURBO MACHINE
RU2014145223A (en) TURBO MACHINE SUCH AS AN AIRCRAFT TURBOREACTIVE ENGINE OR TURBIN SCREW ENGINE
JP6557478B2 (en) Turbine bucket and method for balancing turbine bucket tip shroud
EP2565400A3 (en) Exhaust gas duct for a gas turbine with heat resistant liner and gas turbine having such a gas duct
US8888445B2 (en) Turbomachine seal assembly
WO2013135859A3 (en) Annular-combustion-chamber bypass
IN2014DN06186A (en)
IN2014DN06185A (en)
US9957829B2 (en) Rotor tip clearance
IN2014DN06183A (en)
WO2012071254A3 (en) Exhaust-gas turbocharger
US20110179804A1 (en) Radial turbine engine floating ring seal
US20180187550A1 (en) Last turbine rotor disk for a gas turbine, rotor for a gas turbine comprising such last turbine rotor disk and gas turbine comprising such rotor
US20130108434A1 (en) Method for mounting a stator blading of a turbomachine, an engine casing and a turbomachine comprising at least one stator blading mounted on this engine casing
JP2011089508A (en) Turbine exhaust structure