FR2422037A1 - Gas turbine inlet transition piece - has flange for clip on connection to fixing skirt on turbine entry header - Google Patents

Gas turbine inlet transition piece - has flange for clip on connection to fixing skirt on turbine entry header

Info

Publication number
FR2422037A1
FR2422037A1 FR7737466A FR7737466A FR2422037A1 FR 2422037 A1 FR2422037 A1 FR 2422037A1 FR 7737466 A FR7737466 A FR 7737466A FR 7737466 A FR7737466 A FR 7737466A FR 2422037 A1 FR2422037 A1 FR 2422037A1
Authority
FR
France
Prior art keywords
turbine
transition piece
flange
entry header
clip
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
Application number
FR7737466A
Other languages
French (fr)
Other versions
FR2422037B1 (en
Inventor
Jacques Desoroux
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.)
Alsthom Atlantique SA
Original Assignee
Alsthom Atlantique SA
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 Alsthom Atlantique SA filed Critical Alsthom Atlantique SA
Priority to FR7737466A priority Critical patent/FR2422037A1/en
Publication of FR2422037A1 publication Critical patent/FR2422037A1/en
Application granted granted Critical
Publication of FR2422037B1 publication Critical patent/FR2422037B1/fr
Granted legal-status Critical Current

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)

Abstract

The gas turbine has a ring of combustion chambers arranged in an annulus between the compressor and the turbine. A transition piece (7) runs from each combustion chamber to the inlet of the turbine entry header. At the entry end a flange (9) is welded round each transition piece. An outer skirt (12) running round the whole periphery of the turbine clips over the outer sides of all the flanges. Its projecting edge fits into a slot in the outer wall of the entry header. An inner skirt (13) clips over the inner sides of the flanges and fits into a slot in the inner wall of the entry header.
FR7737466A 1977-12-13 1977-12-13 Gas turbine inlet transition piece - has flange for clip on connection to fixing skirt on turbine entry header Granted FR2422037A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR7737466A FR2422037A1 (en) 1977-12-13 1977-12-13 Gas turbine inlet transition piece - has flange for clip on connection to fixing skirt on turbine entry header

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7737466A FR2422037A1 (en) 1977-12-13 1977-12-13 Gas turbine inlet transition piece - has flange for clip on connection to fixing skirt on turbine entry header

Publications (2)

Publication Number Publication Date
FR2422037A1 true FR2422037A1 (en) 1979-11-02
FR2422037B1 FR2422037B1 (en) 1980-09-05

Family

ID=9198770

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7737466A Granted FR2422037A1 (en) 1977-12-13 1977-12-13 Gas turbine inlet transition piece - has flange for clip on connection to fixing skirt on turbine entry header

Country Status (1)

Country Link
FR (1) FR2422037A1 (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2510220A1 (en) * 1981-07-27 1983-01-28 Gen Electric SEAL
US4785623A (en) * 1987-12-09 1988-11-22 United Technologies Corporation Combustor seal and support
EP0469826A2 (en) * 1990-07-30 1992-02-05 General Electric Company Seal assembly for segmented turbine engine structures
EP0616112A1 (en) * 1993-03-11 1994-09-21 ROLLS-ROYCE plc Sealing structures for gas turbine engines
US5761898A (en) * 1994-12-20 1998-06-09 General Electric Co. Transition piece external frame support
WO2002027148A1 (en) * 2000-09-28 2002-04-04 Siemens Westinghouse Power Corporation Flexible interlocking combustor transition seal
EP1245790A1 (en) * 2001-03-26 2002-10-02 Siemens Aktiengesellschaft Gas turbine
EP1767835A1 (en) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Sealing arrangement resistant to high temperatures, in particular for gas turbines
JP2014009938A (en) * 2012-06-27 2014-01-20 General Electric Co <Ge> Transition duct for gas turbine
EP3299582A1 (en) * 2016-09-26 2018-03-28 General Electric Company Sealing arrangement and gas turbine comprising a sealing arrangement
EP3533972A1 (en) * 2018-02-28 2019-09-04 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor and transition piece assembly
DE102019108267A1 (en) * 2019-03-29 2020-10-01 Rolls-Royce Deutschland Ltd & Co Kg Device for fastening sealing plates between components of a gas turbine engine

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2510220A1 (en) * 1981-07-27 1983-01-28 Gen Electric SEAL
US4785623A (en) * 1987-12-09 1988-11-22 United Technologies Corporation Combustor seal and support
EP0469826A2 (en) * 1990-07-30 1992-02-05 General Electric Company Seal assembly for segmented turbine engine structures
EP0469826A3 (en) * 1990-07-30 1993-06-09 General Electric Company Seal assembly for segmented turbine engine structures
EP0616112A1 (en) * 1993-03-11 1994-09-21 ROLLS-ROYCE plc Sealing structures for gas turbine engines
US5761898A (en) * 1994-12-20 1998-06-09 General Electric Co. Transition piece external frame support
WO2002027148A1 (en) * 2000-09-28 2002-04-04 Siemens Westinghouse Power Corporation Flexible interlocking combustor transition seal
EP1245790A1 (en) * 2001-03-26 2002-10-02 Siemens Aktiengesellschaft Gas turbine
EP1767835A1 (en) * 2005-09-22 2007-03-28 Siemens Aktiengesellschaft Sealing arrangement resistant to high temperatures, in particular for gas turbines
WO2007033974A1 (en) * 2005-09-22 2007-03-29 Siemens Aktiengesellschaft High temperature-resistant sealing assembly, especially for gas turbines
US8365538B2 (en) 2005-09-22 2013-02-05 Siemens Aktiengesellschaft High temperature-resistant sealing assembly, especially for gas turbines
JP2014009938A (en) * 2012-06-27 2014-01-20 General Electric Co <Ge> Transition duct for gas turbine
EP3299582A1 (en) * 2016-09-26 2018-03-28 General Electric Company Sealing arrangement and gas turbine comprising a sealing arrangement
US10690059B2 (en) 2016-09-26 2020-06-23 General Electric Company Advanced seals with reduced corner leakage
EP3533972A1 (en) * 2018-02-28 2019-09-04 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor and transition piece assembly
US11391168B2 (en) 2018-02-28 2022-07-19 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor and transition piece assembly
DE102019108267A1 (en) * 2019-03-29 2020-10-01 Rolls-Royce Deutschland Ltd & Co Kg Device for fastening sealing plates between components of a gas turbine engine

Also Published As

Publication number Publication date
FR2422037B1 (en) 1980-09-05

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