DE178242T1 - Kuehlungskonzept fuer den brennkammer-leitschaufel-uebergang. - Google Patents

Kuehlungskonzept fuer den brennkammer-leitschaufel-uebergang.

Info

Publication number
DE178242T1
DE178242T1 DE198585630109T DE85630109T DE178242T1 DE 178242 T1 DE178242 T1 DE 178242T1 DE 198585630109 T DE198585630109 T DE 198585630109T DE 85630109 T DE85630109 T DE 85630109T DE 178242 T1 DE178242 T1 DE 178242T1
Authority
DE
Germany
Prior art keywords
turbine
combustion chamber
vane
platform
guide vanes
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.)
Pending
Application number
DE198585630109T
Other languages
English (en)
Inventor
Theodore George Newington Connecticut 06111 Fox
Jason Seabury Glastonbury Connecticut 06033 Pettengill
Dennis James Vernon Connecticut 06066 Sullivan
John Stanley Tolland Connecticut 06084 Thackrah
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of DE178242T1 publication Critical patent/DE178242T1/de
Pending 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
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

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)

Claims (2)

Übersetzung EP-Anmeldung Nr. 85630109.8 United Technologies Corp. Patentansprüche
1. Für ein Gasturbinentriebwerk mit einer Brennkammer, einer Turbinenleitschaufel und einer Turbine in axialem Abstand von, aber benachbart zu der Turbinenleitschaufel, wobei die Brennkammer Leitblechflammrohre aufweist, die einen ringförmigen Durchlaß zum Einleiten der Verbrennungsprodukte in die Turbinenleitschaufel bilden, wobei die Turbinenlaufschaufel einen Schaufelblattabschnitt und einen Plattformabschnitt am Fuß des Schaufelblattabschnitts aufweist, eine Tragvorrichtung mit einem Umhüllungsteil, das Abstand von dem Leitblechflammrohr hat, mit diesem aber einen Durchlaß zum Einleiten von Kühlluft in die Turbinenleitschaufel bildet, ein sinusförmiges Teil, das in dem Durchlaß angeordnet ist und am Ende offene Kanäle hat, die die Kühlluft an der Verbindungsstelle der Vorderkante der Turbinenleitschaufeln und der Plattform und in der Nähe des Staupunkts der Verbrennungsprodukte, die zwischen die Turbinenleitschaufeln eintreten, leiten, wodurch die
Grenzschicht an den Turbinenleitschaufeln und der Plattform auf einer relativ kühlen Temperatur gehalten wird.
2. Für ein Gasturbinentriebwerk nach Anspruch 1, wobei das sinusförmige, am Ende offene Teil abwechselnd blockierte Kanäle und abwechsend am Ende offene Kanäle aufweist.
DE198585630109T 1984-10-11 1985-07-11 Kuehlungskonzept fuer den brennkammer-leitschaufel-uebergang. Pending DE178242T1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/659,748 US4739621A (en) 1984-10-11 1984-10-11 Cooling scheme for combustor vane interface

Publications (1)

Publication Number Publication Date
DE178242T1 true DE178242T1 (de) 1986-10-16

Family

ID=24646666

Family Applications (2)

Application Number Title Priority Date Filing Date
DE8585630109T Expired DE3566010D1 (en) 1984-10-11 1985-07-11 Cooling scheme for combustor vane interface
DE198585630109T Pending DE178242T1 (de) 1984-10-11 1985-07-11 Kuehlungskonzept fuer den brennkammer-leitschaufel-uebergang.

Family Applications Before (1)

Application Number Title Priority Date Filing Date
DE8585630109T Expired DE3566010D1 (en) 1984-10-11 1985-07-11 Cooling scheme for combustor vane interface

Country Status (7)

Country Link
US (1) US4739621A (de)
EP (1) EP0178242B1 (de)
JP (1) JPS6196140A (de)
CN (1) CN1003879B (de)
CA (1) CA1245869A (de)
DE (2) DE3566010D1 (de)
IL (1) IL75780A (de)

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US5083422A (en) * 1988-03-25 1992-01-28 General Electric Company Method of breach cooling
US4916906A (en) * 1988-03-25 1990-04-17 General Electric Company Breach-cooled structure
US5101620A (en) * 1988-12-28 1992-04-07 Sundstrand Corporation Annular combustor for a turbine engine without film cooling
US5303543A (en) * 1990-02-08 1994-04-19 Sundstrand Corporation Annular combustor for a turbine engine with tangential passages sized to provide only combustion air
DE9203776U1 (de) * 1992-03-20 1992-05-21 Schreckling, Kurt, 5090 Leverkusen, De
GB9304994D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Improvements in or relating to gas turbine engines
GB9305010D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc A cooled turbine nozzle assembly and a method of calculating the diameters of cooling holes for use in such an assembly
GB9305012D0 (en) * 1993-03-11 1993-04-28 Rolls Royce Plc Sealing structures for gas turbine engines
US5394687A (en) * 1993-12-03 1995-03-07 The United States Of America As Represented By The Department Of Energy Gas turbine vane cooling system
DE19813779B4 (de) * 1998-03-27 2005-04-14 Rolls-Royce Deutschland Ltd & Co Kg Anordnung zur Kühlung der Plattformen von Leitschaufeln einer Gasturbine
DE19856199A1 (de) 1998-12-05 2000-06-08 Abb Alstom Power Ch Ag Kühlung in Gasturbinen
US6419446B1 (en) * 1999-08-05 2002-07-16 United Technologies Corporation Apparatus and method for inhibiting radial transfer of core gas flow within a core gas flow path of a gas turbine engine
FR2825787B1 (fr) * 2001-06-06 2004-08-27 Snecma Moteurs Montage de chambre de combustion cmc de turbomachine par viroles de liaison souples
US6884029B2 (en) * 2002-09-26 2005-04-26 Siemens Westinghouse Power Corporation Heat-tolerated vortex-disrupting fluid guide component
US6969232B2 (en) 2002-10-23 2005-11-29 United Technologies Corporation Flow directing device
US7234304B2 (en) 2002-10-23 2007-06-26 Pratt & Whitney Canada Corp Aerodynamic trip to improve acoustic transmission loss and reduce noise level for gas turbine engine
EP1731711A1 (de) * 2005-06-10 2006-12-13 Siemens Aktiengesellschaft Übergang zwischen Brennkammer und Turbineneinheit, Hitzeschild und Turbinenleitschaufel für eine Gasturbine
US7862291B2 (en) * 2007-02-08 2011-01-04 United Technologies Corporation Gas turbine engine component cooling scheme
EP2229507B1 (de) * 2007-12-29 2017-02-08 General Electric Technology GmbH Gasturbine
US20100054922A1 (en) * 2008-09-04 2010-03-04 General Electric Company Turbine airfoil clocking
US8087253B2 (en) * 2008-11-20 2012-01-03 General Electric Company Methods, apparatus and systems concerning the circumferential clocking of turbine airfoils in relation to combustor cans and the flow of cooling air through the turbine hot gas flowpath
JP5180807B2 (ja) 2008-12-24 2013-04-10 三菱重工業株式会社 １段静翼の冷却構造、及びガスタービン
US8439626B2 (en) * 2008-12-29 2013-05-14 General Electric Company Turbine airfoil clocking
JP5479058B2 (ja) 2009-12-07 2014-04-23 三菱重工業株式会社 燃焼器とタービン部との連通構造、および、ガスタービン
CN102146844A (zh) * 2010-02-10 2011-08-10 中国科学院工程热物理研究所 航空发动机涡轮叶片的零冷气消耗超强度冷却装置
JP5031110B2 (ja) * 2011-01-21 2012-09-19 三菱重工業株式会社 ガスタービン
US9157331B2 (en) * 2011-12-08 2015-10-13 Siemens Aktiengesellschaft Radial active clearance control for a gas turbine engine
US8905714B2 (en) * 2011-12-30 2014-12-09 General Electric Company Turbine rotor blade platform cooling
JP5506834B2 (ja) * 2012-01-27 2014-05-28 三菱重工業株式会社 ガスタービン
JP2012107628A (ja) * 2012-01-27 2012-06-07 Mitsubishi Heavy Ind Ltd ガスタービン
US9752447B2 (en) * 2014-04-04 2017-09-05 United Technologies Corporation Angled rail holes
CN108442985B (zh) * 2018-04-11 2020-10-27 西安交通大学 一种具有提高静叶通道端壁冷却效率的槽缝冷却结构

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3126705A (en) * 1956-03-26 1964-03-31 Combustion system
FR1248821A (fr) * 1960-02-17 1960-12-23 Entwicklungsbau Pirna Veb Chambre de combustion annulaire pour turbines à gaz, notamment pour avions et turbine équipée de ladite chambre ou d'une chambre similaire
GB980363A (en) * 1961-12-04 1965-01-13 Jan Jerie 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
US3307354A (en) * 1965-10-01 1967-03-07 Gen Electric Cooling structure for overlapped panels
US3608310A (en) * 1966-06-27 1971-09-28 Gen Motors Corp Turbine stator-combustor structure
US3527053A (en) * 1968-12-11 1970-09-08 Gen Electric Gas turbine engine with improved gas seal
US3565545A (en) * 1969-01-29 1971-02-23 Melvin Bobo Cooling of turbine rotors in gas turbine engines
US3670497A (en) * 1970-09-02 1972-06-20 United Aircraft Corp Combustion chamber support
US3965066A (en) * 1974-03-15 1976-06-22 General Electric Company Combustor-turbine nozzle interconnection
US4025226A (en) * 1975-10-03 1977-05-24 United Technologies Corporation Air cooled turbine vane
USH903H (en) * 1982-05-03 1991-04-02 General Electric Company Cool tip combustor

Also Published As

Publication number Publication date
IL75780A (en) 1991-04-15
CA1245869A (en) 1988-12-06
EP0178242A1 (de) 1986-04-16
CN85105913A (zh) 1986-08-06
IL75780A0 (en) 1985-11-29
DE3566010D1 (en) 1988-12-08
US4739621A (en) 1988-04-26
CN1003879B (zh) 1989-04-12
JPS6196140A (ja) 1986-05-14
EP0178242B1 (de) 1988-11-02

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