JP7216716B2 - 高温ガス構成要素の壁、および壁を備える高温ガス構成要素 - Google Patents

高温ガス構成要素の壁、および壁を備える高温ガス構成要素 Download PDF

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JP7216716B2
JP7216716B2 JP2020512472A JP2020512472A JP7216716B2 JP 7216716 B2 JP7216716 B2 JP 7216716B2 JP 2020512472 A JP2020512472 A JP 2020512472A JP 2020512472 A JP2020512472 A JP 2020512472A JP 7216716 B2 JP7216716 B2 JP 7216716B2
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diffuser
section
wall
hot gas
metering
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JP2020531746A5 (enExample
JP2020531746A (ja
Inventor
セバスティアン・ホーエンシュタイン
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シーメンス・エナジー・グローバル・ゲーエムベーハー・ウント・コ・カーゲー
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    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • 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
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • 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
    • 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
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
JP2020512472A 2017-08-30 2018-08-28 高温ガス構成要素の壁、および壁を備える高温ガス構成要素 Active JP7216716B2 (ja)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP17188510.6 2017-08-30
EP17188510.6A EP3450682A1 (en) 2017-08-30 2017-08-30 Wall of a hot gas component and corresponding hot gas component
PCT/EP2018/073090 WO2019042970A1 (en) 2017-08-30 2018-08-28 WALL OF A COMPONENT IMPLANTED IN A HOT GAS PATH AND COMPONENT IMPLANTED IN A HOT GAS PATH COMPRISING A WALL

Publications (3)

Publication Number Publication Date
JP2020531746A JP2020531746A (ja) 2020-11-05
JP2020531746A5 JP2020531746A5 (enExample) 2021-08-19
JP7216716B2 true JP7216716B2 (ja) 2023-02-01

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JP2020512472A Active JP7216716B2 (ja) 2017-08-30 2018-08-28 高温ガス構成要素の壁、および壁を備える高温ガス構成要素

Country Status (4)

Country Link
US (1) US11525361B2 (enExample)
EP (2) EP3450682A1 (enExample)
JP (1) JP7216716B2 (enExample)
WO (1) WO2019042970A1 (enExample)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110185500A (zh) * 2019-04-26 2019-08-30 中国航发湖南动力机械研究所 涡轮叶片的v型气膜孔和涡轮叶片
FR3119639B1 (fr) * 2021-02-10 2025-04-25 Safran Aircraft Engines Paroi pourvue d’un orifice de refroidissement ayant une portion de diffusion à section triangulaire
CN112983561B (zh) * 2021-05-11 2021-08-03 中国航发四川燃气涡轮研究院 梅花型气膜孔和形成方法、涡轮叶片和形成方法、燃气机
US11913119B2 (en) 2021-08-13 2024-02-27 Rtx Corporation Forming cooling aperture(s) in a turbine engine component
US11732590B2 (en) 2021-08-13 2023-08-22 Raytheon Technologies Corporation Transition section for accommodating mismatch between other sections of a cooling aperture in a turbine engine component
US12123839B2 (en) 2021-08-13 2024-10-22 Rtx Corporation Forming and/or inspecting cooling aperture(s) in a turbine engine component
US11673200B2 (en) 2021-08-13 2023-06-13 Raytheon Technologies Corporation Forming cooling aperture(s) using electrical discharge machining
US11898465B2 (en) 2021-08-13 2024-02-13 Rtx Corporation Forming lined cooling aperture(s) in a turbine engine component
US11813706B2 (en) 2021-08-13 2023-11-14 Rtx Corporation Methods for forming cooling apertures in a turbine engine component
US11542831B1 (en) 2021-08-13 2023-01-03 Raytheon Technologies Corporation Energy beam positioning during formation of a cooling aperture
US11603769B2 (en) 2021-08-13 2023-03-14 Raytheon Technologies Corporation Forming lined cooling aperture(s) in a turbine engine component
CN114046535B (zh) * 2021-11-09 2022-08-05 南京航空航天大学 一种可调吹附式扩压器
CN114893255B (zh) * 2022-05-12 2023-05-05 中国航发四川燃气涡轮研究院 月牙型气膜孔结构和形成方法、涡轮叶片及其加工方法
US11898460B2 (en) 2022-06-09 2024-02-13 General Electric Company Turbine engine with a blade
US11927111B2 (en) 2022-06-09 2024-03-12 General Electric Company Turbine engine with a blade
CN115234314A (zh) * 2022-07-12 2022-10-25 西北工业大学 一种猫爪形气膜冷却孔结构、设计方法及涡轮叶片
CN116085118A (zh) * 2023-04-10 2023-05-09 清华大学 导向结构
GB2629431A (en) * 2023-04-28 2024-10-30 Siemens Energy Global Gmbh & Co Kg Burner for gas turbine engine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2015520322A (ja) 2012-06-13 2015-07-16 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジンの壁

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4650949A (en) 1985-12-23 1987-03-17 United Technologies Corporation Electrode for electrical discharge machining film cooling passages in an airfoil
JP2810023B2 (ja) * 1996-09-18 1998-10-15 株式会社東芝 高温部材冷却装置
DE59808269D1 (de) * 1998-03-23 2003-06-12 Alstom Switzerland Ltd Filmkühlungsbohrung
US7328580B2 (en) 2004-06-23 2008-02-12 General Electric Company Chevron film cooled wall
JP4147239B2 (ja) 2005-11-17 2008-09-10 川崎重工業株式会社 ダブルジェット式フィルム冷却構造
US20080003096A1 (en) * 2006-06-29 2008-01-03 United Technologies Corporation High coverage cooling hole shape
US7997867B1 (en) * 2006-10-17 2011-08-16 Iowa State University Research Foundation, Inc. Momentum preserving film-cooling shaped holes
US8057181B1 (en) * 2008-11-07 2011-11-15 Florida Turbine Technologies, Inc. Multiple expansion film cooling hole for turbine airfoil
US20110097191A1 (en) * 2009-10-28 2011-04-28 General Electric Company Method and structure for cooling airfoil surfaces using asymmetric chevron film holes
CN102140964B (zh) 2010-02-03 2013-07-03 中国科学院工程热物理研究所 一种提高离散孔气膜冷却效率的结构
JP4954309B2 (ja) * 2010-03-24 2012-06-13 川崎重工業株式会社 ダブルジェット式フィルム冷却構造
US8905713B2 (en) 2010-05-28 2014-12-09 General Electric Company Articles which include chevron film cooling holes, and related processes
US9181819B2 (en) 2010-06-11 2015-11-10 Siemens Energy, Inc. Component wall having diffusion sections for cooling in a turbine engine
US8584470B2 (en) * 2012-02-15 2013-11-19 United Technologies Corporation Tri-lobed cooling hole and method of manufacture
US9482100B2 (en) * 2012-02-15 2016-11-01 United Technologies Corporation Multi-lobed cooling hole
US9598979B2 (en) * 2012-02-15 2017-03-21 United Technologies Corporation Manufacturing methods for multi-lobed cooling holes
JP5530001B1 (ja) 2013-05-22 2014-06-25 川崎重工業株式会社 ダブルジェット式フイルム冷却構造とその製造方法
EP2990606A1 (de) 2014-08-26 2016-03-02 Siemens Aktiengesellschaft Turbinenschaufel
US10400607B2 (en) * 2014-12-30 2019-09-03 United Technologies Corporation Large-footprint turbine cooling hole
US20180135520A1 (en) * 2016-11-16 2018-05-17 United Technologies Corporation Large area ratio cooling holes

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2015520322A (ja) 2012-06-13 2015-07-16 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジンの壁

Also Published As

Publication number Publication date
US20200190990A1 (en) 2020-06-18
EP3652418A1 (en) 2020-05-20
US11525361B2 (en) 2022-12-13
EP3450682A1 (en) 2019-03-06
JP2020531746A (ja) 2020-11-05
EP3652418B1 (en) 2021-07-14
WO2019042970A1 (en) 2019-03-07

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