EP2650480A3 - Transition piece for a gas turbine engine, corresponding system and method - Google Patents

Transition piece for a gas turbine engine, corresponding system and method Download PDF

Info

Publication number
EP2650480A3
EP2650480A3 EP13163218.4A EP13163218A EP2650480A3 EP 2650480 A3 EP2650480 A3 EP 2650480A3 EP 13163218 A EP13163218 A EP 13163218A EP 2650480 A3 EP2650480 A3 EP 2650480A3
Authority
EP
European Patent Office
Prior art keywords
transition piece
gas turbine
turbine engine
sectional area
cross sectional
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.)
Withdrawn
Application number
EP13163218.4A
Other languages
German (de)
French (fr)
Other versions
EP2650480A2 (en
Inventor
Richard Martin Dicintio
Patrick Benedict Melton
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2650480A2 publication Critical patent/EP2650480A2/en
Publication of EP2650480A3 publication Critical patent/EP2650480A3/en
Withdrawn legal-status Critical Current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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Management, Administration, Business Operations System, And Electronic Commerce (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Portable Nailing Machines And Staplers (AREA)
  • Spark Plugs (AREA)

Abstract

Disclosed herein are apparatus, method, and system for cross sectional area convergence reduction and selection of a transition piece (200) of a gas turbine engine. In an embodiment, an aft end cross sectional area (210) is determined for a transition piece and a forward end cross sectional area (205) is determined for the transition piece. The transition piece may be fabricated based on a constant slope of cross sectional area change between the aft end and the forward end.
EP13163218.4A 2012-04-13 2013-04-10 Transition piece for a gas turbine engine, corresponding system and method Withdrawn EP2650480A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/446,718 US20130272863A1 (en) 2012-04-13 2012-04-13 Transition Piece Cross Sectional Area Convergence Reduction And Selection

Publications (2)

Publication Number Publication Date
EP2650480A2 EP2650480A2 (en) 2013-10-16
EP2650480A3 true EP2650480A3 (en) 2015-10-21

Family

ID=48139718

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13163218.4A Withdrawn EP2650480A3 (en) 2012-04-13 2013-04-10 Transition piece for a gas turbine engine, corresponding system and method

Country Status (5)

Country Link
US (1) US20130272863A1 (en)
EP (1) EP2650480A3 (en)
JP (1) JP2013221736A (en)
CN (1) CN103375264A (en)
RU (1) RU2013116554A (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9321115B2 (en) * 2014-02-05 2016-04-26 Alstom Technologies Ltd Method of repairing a transition duct side seal
US10066837B2 (en) 2015-02-20 2018-09-04 General Electric Company Combustor aft mount assembly

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080087020A1 (en) * 2006-10-13 2008-04-17 Siemens Power Generation, Inc. Transition duct for gas turbine engine.
US20080155959A1 (en) * 2006-12-22 2008-07-03 General Electric Company Detonation combustor to turbine transition piece for hybrid engine
US20110061393A1 (en) * 2009-09-11 2011-03-17 Alstom Technologies Ltd. Gas Turbine Transition Duct Profile
US20110265491A1 (en) * 2008-10-01 2011-11-03 Mitsubishi Heavy Industries, Ltd. Combustor connection structure, combustor transition piece, designing method of combustor transition piece, and gas turbine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2326680C3 (en) * 1973-05-25 1980-09-25 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Flame tube with premixing chamber for combustion chambers of gas turbine engines
JP3846169B2 (en) * 2000-09-14 2006-11-15 株式会社日立製作所 Gas turbine repair method
US6644032B1 (en) * 2002-10-22 2003-11-11 Power Systems Mfg, Llc Transition duct with enhanced profile optimization
US7527469B2 (en) * 2004-12-10 2009-05-05 Siemens Energy, Inc. Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080087020A1 (en) * 2006-10-13 2008-04-17 Siemens Power Generation, Inc. Transition duct for gas turbine engine.
US20080155959A1 (en) * 2006-12-22 2008-07-03 General Electric Company Detonation combustor to turbine transition piece for hybrid engine
US20110265491A1 (en) * 2008-10-01 2011-11-03 Mitsubishi Heavy Industries, Ltd. Combustor connection structure, combustor transition piece, designing method of combustor transition piece, and gas turbine
US20110061393A1 (en) * 2009-09-11 2011-03-17 Alstom Technologies Ltd. Gas Turbine Transition Duct Profile

Also Published As

Publication number Publication date
US20130272863A1 (en) 2013-10-17
RU2013116554A (en) 2014-10-20
EP2650480A2 (en) 2013-10-16
JP2013221736A (en) 2013-10-28
CN103375264A (en) 2013-10-30

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