WO2015116325A3 - Turbine airfoil cooling system with nonlinear trailing edge exit slots - Google Patents

Turbine airfoil cooling system with nonlinear trailing edge exit slots Download PDF

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Publication number
WO2015116325A3
WO2015116325A3 PCT/US2014/070714 US2014070714W WO2015116325A3 WO 2015116325 A3 WO2015116325 A3 WO 2015116325A3 US 2014070714 W US2014070714 W US 2014070714W WO 2015116325 A3 WO2015116325 A3 WO 2015116325A3
Authority
WO
WIPO (PCT)
Prior art keywords
trailing edge
nonlinear
exit slot
edge exit
cooling system
Prior art date
Application number
PCT/US2014/070714
Other languages
French (fr)
Other versions
WO2015116325A2 (en
Inventor
Ching-Pang Lee
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
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 Siemens Aktiengesellschaft, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Publication of WO2015116325A2 publication Critical patent/WO2015116325A2/en
Publication of WO2015116325A3 publication Critical patent/WO2015116325A3/en

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/02—Lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B22C9/043—Removing the consumable pattern
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing 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
    • F05D2240/304—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 trailing 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/183—Two-dimensional patterned zigzag
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A cooling system for a turbine airfoil of a turbine engine having a trailing edge cooling channel formed from a central trailing edge cooling channel and at least one trailing edge exit slot with a nonlinear longitudinal axis is disclosed. The trailing edge exit slot may be defined by ribs (24) having wavy side edges that form a jagged edge. As such, the nonlinear longitudinal axis (22) of the trailing edge exit slot reduces the effective flow area, generates impingement and turbulence to increase heat transfer and provides sufficient mechanical strength for better casting yield without overflowing for better performance. The nonlinear trailing edge exit slot may be formed using a ceramic core (106) and investment casting.
PCT/US2014/070714 2013-12-26 2014-12-17 Turbine airfoil cooling system with nonlinear trailing edge exit slots WO2015116325A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US14/140,593 US20150184518A1 (en) 2013-12-26 2013-12-26 Turbine airfoil cooling system with nonlinear trailing edge exit slots
US14/140,593 2013-12-26

Publications (2)

Publication Number Publication Date
WO2015116325A2 WO2015116325A2 (en) 2015-08-06
WO2015116325A3 true WO2015116325A3 (en) 2015-10-29

Family

ID=53481157

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2014/070714 WO2015116325A2 (en) 2013-12-26 2014-12-17 Turbine airfoil cooling system with nonlinear trailing edge exit slots

Country Status (2)

Country Link
US (1) US20150184518A1 (en)
WO (1) WO2015116325A2 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL3086893T3 (en) 2013-12-23 2020-01-31 United Technologies Corporation Lost core structural frame
KR102209771B1 (en) * 2016-05-20 2021-01-29 한화에어로스페이스 주식회사 Core for casting turbine blade, manufacturing method thereof, and turbine blade using the same
CN106014487A (en) * 2016-06-12 2016-10-12 上海交通大学 Jet flow impact control structure with confined space internally provided with cross flow
FR3062675B1 (en) * 2017-02-07 2021-01-15 Safran Helicopter Engines HELICOPTER TURBINE HIGH PRESSURE VENTILATED VANE INCLUDING UPSTREAM DUCT AND CENTRAL COOLING CAVITY

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5752801A (en) * 1997-02-20 1998-05-19 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil and method of making same
EP1524045A2 (en) * 2003-10-15 2005-04-20 United Technologies Corporation Refractory metal core
EP1607577A2 (en) * 2004-06-17 2005-12-21 United Technologies Corporation Turbine engine blades with drillable film cooling holes
EP2230384A2 (en) * 2009-03-18 2010-09-22 General Electric Company Film-cooling augmentation device and turbine airfoil incorporating the same
US20120269649A1 (en) * 2011-04-22 2012-10-25 Christopher Rawlings Turbine blade with improved trailing edge cooling
US20130064681A1 (en) * 2011-09-09 2013-03-14 Ching-Pang Lee Trailing edge cooling system in a turbine airfoil assembly

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3921271A (en) * 1973-01-02 1975-11-25 Gen Electric Air-cooled turbine blade and method of making same
US4203706A (en) * 1977-12-28 1980-05-20 United Technologies Corporation Radial wafer airfoil construction
DE19963349A1 (en) * 1999-12-27 2001-06-28 Abb Alstom Power Ch Ag Blade for gas turbines with throttle cross section at the rear edge
US6325593B1 (en) * 2000-02-18 2001-12-04 General Electric Company Ceramic turbine airfoils with cooled trailing edge blocks
FR2896710B1 (en) * 2006-01-27 2009-10-30 Snecma Sa PROCESS FOR MANUFACTURING TURBOMACHINE COMPONENT WITH COOLING AIR EXHAUST ORIFICES
US8109726B2 (en) * 2009-01-19 2012-02-07 Siemens Energy, Inc. Turbine blade with micro channel cooling system
US8961133B2 (en) * 2010-12-28 2015-02-24 Rolls-Royce North American Technologies, Inc. Gas turbine engine and cooled airfoil
US20140064983A1 (en) * 2012-08-31 2014-03-06 General Electric Company Airfoil and method for manufacturing an airfoil

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5752801A (en) * 1997-02-20 1998-05-19 Westinghouse Electric Corporation Apparatus for cooling a gas turbine airfoil and method of making same
EP1524045A2 (en) * 2003-10-15 2005-04-20 United Technologies Corporation Refractory metal core
EP1607577A2 (en) * 2004-06-17 2005-12-21 United Technologies Corporation Turbine engine blades with drillable film cooling holes
EP2230384A2 (en) * 2009-03-18 2010-09-22 General Electric Company Film-cooling augmentation device and turbine airfoil incorporating the same
US20120269649A1 (en) * 2011-04-22 2012-10-25 Christopher Rawlings Turbine blade with improved trailing edge cooling
US20130064681A1 (en) * 2011-09-09 2013-03-14 Ching-Pang Lee Trailing edge cooling system in a turbine airfoil assembly

Also Published As

Publication number Publication date
US20150184518A1 (en) 2015-07-02
WO2015116325A2 (en) 2015-08-06

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