IL74050A0 - Vortex generating flow passage design for increased film cooling effectiveness - Google Patents

Vortex generating flow passage design for increased film cooling effectiveness

Info

Publication number
IL74050A0
IL74050A0 IL74050A IL7405085A IL74050A0 IL 74050 A0 IL74050 A0 IL 74050A0 IL 74050 A IL74050 A IL 74050A IL 7405085 A IL7405085 A IL 7405085A IL 74050 A0 IL74050 A0 IL 74050A0
Authority
IL
Israel
Prior art keywords
flow passage
film cooling
cooling effectiveness
vortex generating
generating flow
Prior art date
Application number
IL74050A
Other languages
English (en)
Original Assignee
Nasa
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 Nasa filed Critical Nasa
Publication of IL74050A0 publication Critical patent/IL74050A0/xx

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • 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
    • 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)
  • Chemical Vapour Deposition (AREA)
IL74050A 1984-02-15 1985-01-14 Vortex generating flow passage design for increased film cooling effectiveness IL74050A0 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US06/580,419 US4529358A (en) 1984-02-15 1984-02-15 Vortex generating flow passage design for increased film cooling effectiveness

Publications (1)

Publication Number Publication Date
IL74050A0 true IL74050A0 (en) 1985-04-30

Family

ID=24321032

Family Applications (1)

Application Number Title Priority Date Filing Date
IL74050A IL74050A0 (en) 1984-02-15 1985-01-14 Vortex generating flow passage design for increased film cooling effectiveness

Country Status (5)

Country Link
US (1) US4529358A (xx)
EP (1) EP0151918A3 (xx)
JP (1) JPS60216022A (xx)
CA (1) CA1225530A (xx)
IL (1) IL74050A0 (xx)

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US10422230B2 (en) 2012-02-15 2019-09-24 United Technologies Corporation Cooling hole with curved metering section
US8850828B2 (en) 2012-02-15 2014-10-07 United Technologies Corporation Cooling hole with curved metering section
US9422815B2 (en) 2012-02-15 2016-08-23 United Technologies Corporation Gas turbine engine component with compound cusp cooling configuration
US8683814B2 (en) 2012-02-15 2014-04-01 United Technologies Corporation Gas turbine engine component with impingement and lobed cooling hole
US9482100B2 (en) 2012-02-15 2016-11-01 United Technologies Corporation Multi-lobed cooling hole
US9416971B2 (en) 2012-02-15 2016-08-16 United Technologies Corporation Multiple diffusing cooling hole
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US8763402B2 (en) 2012-02-15 2014-07-01 United Technologies Corporation Multi-lobed cooling hole and method of manufacture
US8522558B1 (en) 2012-02-15 2013-09-03 United Technologies Corporation Multi-lobed cooling hole array
US9279330B2 (en) 2012-02-15 2016-03-08 United Technologies Corporation Gas turbine engine component with converging/diverging cooling passage
US9416665B2 (en) 2012-02-15 2016-08-16 United Technologies Corporation Cooling hole with enhanced flow attachment
US9273560B2 (en) 2012-02-15 2016-03-01 United Technologies Corporation Gas turbine engine component with multi-lobed cooling hole
US9598979B2 (en) 2012-02-15 2017-03-21 United Technologies Corporation Manufacturing methods for multi-lobed cooling holes
US8733111B2 (en) 2012-02-15 2014-05-27 United Technologies Corporation Cooling hole with asymmetric diffuser
US9284844B2 (en) 2012-02-15 2016-03-15 United Technologies Corporation Gas turbine engine component with cusped cooling hole
US9410435B2 (en) 2012-02-15 2016-08-09 United Technologies Corporation Gas turbine engine component with diffusive cooling hole
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US10113433B2 (en) 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
EP2961964B1 (en) * 2013-02-26 2020-10-21 United Technologies Corporation Gas turbine engine component and corresponding method of manufacturing an aperture
US10378362B2 (en) 2013-03-15 2019-08-13 United Technologies Corporation Gas turbine engine component cooling channels
US20150003962A1 (en) * 2013-06-27 2015-01-01 Bruce L. Smith Apparatus for reducing a temperature gradient of mainstream fluid downstream of an airfoil in a gas turbine engine
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US10598379B2 (en) * 2013-11-25 2020-03-24 United Technologies Corporation Film cooled multi-walled structure with one or more indentations
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CN104033251A (zh) * 2014-06-12 2014-09-10 中国科学院工程热物理研究所 一种提高燃机高温部件冷却效率的气膜孔结构
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Also Published As

Publication number Publication date
US4529358A (en) 1985-07-16
CA1225530A (en) 1987-08-18
JPS60216022A (ja) 1985-10-29
EP0151918A3 (en) 1987-03-11
EP0151918A2 (en) 1985-08-21
JPH025883B2 (xx) 1990-02-06

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