DE69828757D1 - Kühlung der Anströmkante einer Gasturbinenschaufel - Google Patents

Kühlung der Anströmkante einer Gasturbinenschaufel

Info

Publication number
DE69828757D1
DE69828757D1 DE69828757T DE69828757T DE69828757D1 DE 69828757 D1 DE69828757 D1 DE 69828757D1 DE 69828757 T DE69828757 T DE 69828757T DE 69828757 T DE69828757 T DE 69828757T DE 69828757 D1 DE69828757 D1 DE 69828757D1
Authority
DE
Germany
Prior art keywords
cooling
gas turbine
leading edge
turbine blade
blade
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.)
Expired - Lifetime
Application number
DE69828757T
Other languages
English (en)
Other versions
DE69828757T2 (de
Inventor
Martin G Tabbita
James P Downs
Friedrich Soechting
Thomas A Auxier
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
Application granted granted Critical
Publication of DE69828757D1 publication Critical patent/DE69828757D1/de
Publication of DE69828757T2 publication Critical patent/DE69828757T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • 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
    • 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
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage

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)
DE69828757T 1997-12-17 1998-12-02 Kühlung der Anströmkante einer Gasturbinenschaufel Expired - Lifetime DE69828757T2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US992322 1997-12-17
US08/992,322 US6050777A (en) 1997-12-17 1997-12-17 Apparatus and method for cooling an airfoil for a gas turbine engine

Publications (2)

Publication Number Publication Date
DE69828757D1 true DE69828757D1 (de) 2005-03-03
DE69828757T2 DE69828757T2 (de) 2005-07-14

Family

ID=25538192

Family Applications (2)

Application Number Title Priority Date Filing Date
DE0924382T Pending DE924382T1 (de) 1997-12-17 1998-12-02 Kühlung der Anströmkante einer Gasturbinenschaufel
DE69828757T Expired - Lifetime DE69828757T2 (de) 1997-12-17 1998-12-02 Kühlung der Anströmkante einer Gasturbinenschaufel

Family Applications Before (1)

Application Number Title Priority Date Filing Date
DE0924382T Pending DE924382T1 (de) 1997-12-17 1998-12-02 Kühlung der Anströmkante einer Gasturbinenschaufel

Country Status (4)

Country Link
US (2) US6050777A (de)
EP (1) EP0924382B1 (de)
KR (1) KR100581301B1 (de)
DE (2) DE924382T1 (de)

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US6547524B2 (en) 2001-05-21 2003-04-15 United Technologies Corporation Film cooled article with improved temperature tolerance
JP4487449B2 (ja) 2001-06-28 2010-06-23 アイシン精機株式会社 弁開閉時期制御装置
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US6955522B2 (en) * 2003-04-07 2005-10-18 United Technologies Corporation Method and apparatus for cooling an airfoil
US8061981B2 (en) * 2004-12-03 2011-11-22 Volvo Aero Corporation Blade for a flow machine
US7371048B2 (en) * 2005-05-27 2008-05-13 United Technologies Corporation Turbine blade trailing edge construction
US7484935B2 (en) * 2005-06-02 2009-02-03 Honeywell International Inc. Turbine rotor hub contour
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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
US7510367B2 (en) * 2006-08-24 2009-03-31 Siemens Energy, Inc. Turbine airfoil with endwall horseshoe cooling slot
US7540712B1 (en) * 2006-09-15 2009-06-02 Florida Turbine Technologies, Inc. Turbine airfoil with showerhead cooling holes
US7806658B2 (en) * 2006-10-25 2010-10-05 Siemens Energy, Inc. Turbine airfoil cooling system with spanwise equalizer rib
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US8157527B2 (en) 2008-07-03 2012-04-17 United Technologies Corporation Airfoil with tapered radial cooling passage
US20100008759A1 (en) * 2008-07-10 2010-01-14 General Electric Company Methods and apparatuses for providing film cooling to turbine components
US8105030B2 (en) * 2008-08-14 2012-01-31 United Technologies Corporation Cooled airfoils and gas turbine engine systems involving such airfoils
US8572844B2 (en) 2008-08-29 2013-11-05 United Technologies Corporation Airfoil with leading edge cooling passage
US8303252B2 (en) 2008-10-16 2012-11-06 United Technologies Corporation Airfoil with cooling passage providing variable heat transfer rate
US8057182B2 (en) * 2008-11-21 2011-11-15 General Electric Company Metered cooling slots for turbine blades
US8109725B2 (en) 2008-12-15 2012-02-07 United Technologies Corporation Airfoil with wrapped leading edge cooling passage
US8152468B2 (en) * 2009-03-13 2012-04-10 United Technologies Corporation Divoted airfoil baffle having aimed cooling holes
US8292583B2 (en) * 2009-08-13 2012-10-23 Siemens Energy, Inc. Turbine blade having a constant thickness airfoil skin
US20110097188A1 (en) * 2009-10-23 2011-04-28 General Electric Company Structure and method for improving film cooling using shallow trench with holes oriented along length of trench
US8742279B2 (en) * 2010-02-01 2014-06-03 United Technologies Corporation Method of creating an airfoil trench and a plurality of cooling holes within the trench
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US10113435B2 (en) * 2011-07-15 2018-10-30 United Technologies Corporation Coated gas turbine components
US9022737B2 (en) 2011-08-08 2015-05-05 United Technologies Corporation Airfoil including trench with contoured surface
US8870536B2 (en) 2012-01-13 2014-10-28 General Electric Company Airfoil
US8870535B2 (en) * 2012-01-13 2014-10-28 General Electric Company Airfoil
US9228442B2 (en) 2012-04-05 2016-01-05 United Technologies Corporation Turbine airfoil tip shelf and squealer pocket cooling
US9429027B2 (en) * 2012-04-05 2016-08-30 United Technologies Corporation Turbine airfoil tip shelf and squealer pocket cooling
US9080451B2 (en) 2012-06-28 2015-07-14 General Electric Company Airfoil
US9273561B2 (en) 2012-08-03 2016-03-01 General Electric Company Cooling structures for turbine rotor blade tips
US10113433B2 (en) 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
US9228440B2 (en) 2012-12-03 2016-01-05 Honeywell International Inc. Turbine blade airfoils including showerhead film cooling systems, and methods for forming an improved showerhead film cooled airfoil of a turbine blade
US9562437B2 (en) * 2013-04-26 2017-02-07 Honeywell International Inc. Turbine blade airfoils including film cooling systems, and methods for forming an improved film cooled airfoil of a turbine blade
EP3017148A1 (de) 2013-07-03 2016-05-11 General Electric Company Grabenkühlung von tragflächenstrukturen
US10775115B2 (en) 2013-08-29 2020-09-15 General Electric Company Thermal spray coating method and thermal spray coated article
WO2015112225A2 (en) 2013-11-25 2015-07-30 United Technologies Corporation Gas turbine engine airfoil with leading edge trench and impingement cooling
CN103806952A (zh) * 2014-01-20 2014-05-21 北京航空航天大学 一种具有前缘凹腔的涡轮叶片
US10329923B2 (en) 2014-03-10 2019-06-25 United Technologies Corporation Gas turbine engine airfoil leading edge cooling
US10443395B2 (en) 2016-03-18 2019-10-15 General Electric Company Component for a turbine engine with a film hole
US20170306764A1 (en) * 2016-04-26 2017-10-26 General Electric Company Airfoil for a turbine engine
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US10508551B2 (en) * 2016-08-16 2019-12-17 General Electric Company Engine component with porous trench
US11286787B2 (en) 2016-09-15 2022-03-29 Raytheon Technologies Corporation Gas turbine engine airfoil with showerhead cooling holes near leading edge
US10584593B2 (en) 2017-10-24 2020-03-10 United Technologies Corporation Airfoil having impingement leading edge
US11401818B2 (en) 2018-08-06 2022-08-02 General Electric Company Turbomachine cooling trench
US11585224B2 (en) 2020-08-07 2023-02-21 General Electric Company Gas turbine engines and methods associated therewith
US11220917B1 (en) * 2020-09-03 2022-01-11 Raytheon Technologies Corporation Diffused cooling arrangement for gas turbine engine components

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US6050777A (en) * 1997-12-17 2000-04-18 United Technologies Corporation Apparatus and method for cooling an airfoil for a gas turbine engine

Also Published As

Publication number Publication date
DE924382T1 (de) 2000-03-02
US6210112B1 (en) 2001-04-03
EP0924382A3 (de) 2000-08-23
US6050777A (en) 2000-04-18
KR100581301B1 (ko) 2006-08-30
DE69828757T2 (de) 2005-07-14
EP0924382A2 (de) 1999-06-23
KR19990063130A (ko) 1999-07-26
EP0924382B1 (de) 2005-01-26

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Legal Events

Date Code Title Description
8364 No opposition during term of opposition