EP0924384A3 - Airfoil with leading edge cooling - Google Patents

Airfoil with leading edge cooling Download PDF

Info

Publication number
EP0924384A3
EP0924384A3 EP98310191A EP98310191A EP0924384A3 EP 0924384 A3 EP0924384 A3 EP 0924384A3 EP 98310191 A EP98310191 A EP 98310191A EP 98310191 A EP98310191 A EP 98310191A EP 0924384 A3 EP0924384 A3 EP 0924384A3
Authority
EP
European Patent Office
Prior art keywords
leading edge
airfoil
trench
edge cooling
disposed
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Withdrawn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
EP98310191A
Other languages
German (de)
French (fr)
Other versions
EP0924384A2 (en
Inventor
George P. Liang
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
Publication of EP0924384A2 publication Critical patent/EP0924384A2/en
Publication of EP0924384A3 publication Critical patent/EP0924384A3/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Withdrawn legal-status Critical Current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
    • 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
    • F01D5/187—Convection cooling
    • 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
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
    • 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

Abstract

A hollow airfoil (16) is provided which includes a body, a trench (30), and a plurality of cooling apertures (36) disposed within the trench (30). The body extends chordwise between a leading edge (26) and a trailing edge (29), and spanwise between an outer radial surface and an inner radial surface, and includes an exterior wall surrounding a cavity (20). The trench (30) is disposed in the exterior wall along the leading edge (26), extending in a spanwise direction.
EP98310191A 1997-12-17 1998-12-11 Airfoil with leading edge cooling Withdrawn EP0924384A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US99232397A 1997-12-17 1997-12-17
US992323 1997-12-17

Publications (2)

Publication Number Publication Date
EP0924384A2 EP0924384A2 (en) 1999-06-23
EP0924384A3 true EP0924384A3 (en) 2000-08-23

Family

ID=25538194

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98310191A Withdrawn EP0924384A3 (en) 1997-12-17 1998-12-11 Airfoil with leading edge cooling

Country Status (3)

Country Link
EP (1) EP0924384A3 (en)
JP (1) JPH11247611A (en)
KR (1) KR19990063131A (en)

Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6547524B2 (en) * 2001-05-21 2003-04-15 United Technologies Corporation Film cooled article with improved temperature tolerance
US7300252B2 (en) 2004-10-04 2007-11-27 Alstom Technology Ltd Gas turbine airfoil leading edge cooling construction
EP1898051B8 (en) 2006-08-25 2017-08-02 Ansaldo Energia IP UK Limited Gas turbine airfoil with leading edge cooling
US7980819B2 (en) 2007-03-14 2011-07-19 United Technologies Corporation Cast features for a turbine engine airfoil
US8439644B2 (en) * 2007-12-10 2013-05-14 United Technologies Corporation Airfoil leading edge shape tailoring to reduce heat load
US8105030B2 (en) * 2008-08-14 2012-01-31 United Technologies Corporation Cooled airfoils and gas turbine engine systems involving such airfoils
US8371814B2 (en) 2009-06-24 2013-02-12 Honeywell International Inc. Turbine engine components
EP2299056A1 (en) 2009-09-02 2011-03-23 Siemens Aktiengesellschaft Cooling of a gas turbine component shaped as a rotor disc or as a blade
US8529193B2 (en) 2009-11-25 2013-09-10 Honeywell International Inc. Gas turbine engine components with improved film cooling
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US9022737B2 (en) 2011-08-08 2015-05-05 United Technologies Corporation Airfoil including trench with contoured surface
US9650900B2 (en) 2012-05-07 2017-05-16 Honeywell International Inc. Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
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
CA2898822A1 (en) 2013-03-13 2014-10-09 Rolls-Royce Corporation Trenched cooling hole arrangement for a ceramic matrix composite vane
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
CN103806952A (en) * 2014-01-20 2014-05-21 北京航空航天大学 Turbine blade with leading-edge concaved cavity
GB201521862D0 (en) * 2015-12-11 2016-01-27 Rolls Royce Plc Cooling arrangement
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
GB201721533D0 (en) * 2017-12-21 2018-02-07 Rolls Royce Plc Aerofoil cooling arrangement
GB201819064D0 (en) * 2018-11-23 2019-01-09 Rolls Royce Aerofoil stagnation zone cooling
JP7232035B2 (en) * 2018-12-18 2023-03-02 三菱重工業株式会社 Gas turbine stator blades and gas turbines

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB435906A (en) * 1934-01-29 1935-10-01 Bbc Brown Boveri & Cie Improvements in and relating to the protection of machine parts, more particularly of turbine blades, against high temperatures
GB2127105A (en) * 1982-09-16 1984-04-04 Rolls Royce Improvements in cooled gas turbine engine aerofoils
US5152667A (en) * 1991-07-16 1992-10-06 General Motors Corporation Cooled wall structure especially for gas turbine engines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB435906A (en) * 1934-01-29 1935-10-01 Bbc Brown Boveri & Cie Improvements in and relating to the protection of machine parts, more particularly of turbine blades, against high temperatures
GB2127105A (en) * 1982-09-16 1984-04-04 Rolls Royce Improvements in cooled gas turbine engine aerofoils
US5152667A (en) * 1991-07-16 1992-10-06 General Motors Corporation Cooled wall structure especially for gas turbine engines

Also Published As

Publication number Publication date
KR19990063131A (en) 1999-07-26
EP0924384A2 (en) 1999-06-23
JPH11247611A (en) 1999-09-14

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