US20090246011A1 - Film cooling of turbine components - Google Patents

Film cooling of turbine components Download PDF

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Publication number
US20090246011A1
US20090246011A1 US12/054,535 US5453508A US2009246011A1 US 20090246011 A1 US20090246011 A1 US 20090246011A1 US 5453508 A US5453508 A US 5453508A US 2009246011 A1 US2009246011 A1 US 2009246011A1
Authority
US
United States
Prior art keywords
cooling
flow
turbine component
hole
diverter
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.)
Abandoned
Application number
US12/054,535
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English (en)
Inventor
Gary Michael Itzel
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to US12/054,535 priority Critical patent/US20090246011A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ITZEL, GARY MICHAEL
Priority to JP2009057231A priority patent/JP2009236112A/ja
Priority to DE102009003634A priority patent/DE102009003634A1/de
Priority to FR0951711A priority patent/FR2929323A1/fr
Priority to CN200910132498A priority patent/CN101545381A/zh
Publication of US20090246011A1 publication Critical patent/US20090246011A1/en
Abandoned legal-status Critical Current

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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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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

Definitions

  • the subject invention relates to turbines. More particularly, the subject invention relates to film cooling of turbine components.
  • Components in the hot gas path of turbines are subjected to high temperatures which leads to low cycle fatigue cracking, creep rupture, and/or oxidation and the like which causes premature failure of the components.
  • One or more methods are often employed to cool the hot gas path components to extend their useful lives.
  • One such method is film cooling. Film cooling is accomplished by injecting air through holes in the surface of the component, from a source such as compressor bleed flow which bypasses a combustor. The relatively cooler air enters the hot gas path and forms an insulating layer between the hot gas and the component and reduces heat flux into the component.
  • a turbine component includes a flow path surface and a trench disposed in the flow path surface. At least one cooling through hole is located in the trench and is capable of injecting a cooling flow onto the flow path surface of the turbine component. The cooling flow forms a cooling film on the flow path surface.
  • a method of cooling a turbine component includes injecting a cooling flow onto a flow path surface of the turbine component through at least one cooling through hole disposed in a trench in the turbine component.
  • a cooling film is formed by the cooling flow between the flow path surface and a hot gas flow.
  • FIG. 1 is a partial perspective view of an embodiment of a turbine component having flow diverters for film cooling
  • FIG. 2 is a cross-sectional view of the turbine component of FIG. 1 ;
  • FIG. 3 is an axial cross-sectional view of the turbine component of FIG. 1 ;
  • FIG. 4 is a partial perspective view of another embodiment of a turbine component having flow diverters for film cooling
  • FIG. 5 is a partial perspective view of an alternative embodiment of the turbine component of FIG. 4 ;
  • FIG. 6 is a partial perspective view of yet another embodiment of a turbine component having flow diverters for film cooling.
  • FIG. 1 A partial view of a turbine component, for example, a turbine airfoil 10 is shown in FIG. 1 .
  • Hot gas flow 12 proceeds across an outer surface 14 of the turbine airfoil 10 in a flow direction 16 .
  • At least one trench 18 is disposed in the turbine airfoil 10 and is defined by an upstream trench wall 20 which, in some embodiments extends substantially radially outward from the turbine airfoil 10 , and at least one downstream trench surface 22 .
  • At least one cooling through hole 24 is disposed in the trench 18 .
  • a plurality of cooling through holes 24 are arranged substantially in a line extending radially along the trench 18 , but other arrangements of cooling through holes 24 in the trench 18 are contemplated within the scope of the present disclosure.
  • the cooling through holes 24 may have an elliptical opening as shown in FIG. 1 , or may have circular or other-shaped openings depending on desired flow from the cooling through holes 24 . Further, as shown in FIG. 2 , the cooling through holes 24 may have an axis 26 which is not perpendicular to the outer surface 14 , to facilitate smoother flow through the cooling through holes 24 .
  • the downstream trench surface 22 slopes radially outwardly from a trench floor 28 . This prevents a cooling flow 30 exiting the cooling through holes 24 from blowing off of the outer surface 14 and into the hot gas flow 12 .
  • At least one flow diverter 32 is disposed at the downstream trench surface 22 .
  • Each flow diverter 32 includes a downstream wall 34 which, in the embodiment of FIG. 1 , is disposed axially downstream from and substantially perpendicular to the flow direction 16 such that cooling flow 30 exiting the cooling through hole 24 is diverted or split as shown in FIG. 1 .
  • the downstream wall 34 is disposed at a substantially same lateral position as a corresponding cooling through hole 24 .
  • the cooling flow 30 divides and flows laterally around the downstream wall 34 and along the downstream trench surface 22 . A portion of the cooling flow 30 may flow radially outboard of the downstream wall 34 and proceed along the outer surface 14 .
  • Each flow diverter 32 includes two diverter sidewalls 36 . Each diverter sidewall 36 extends from the downstream wall 34 at a sidewall angle 38 which in some embodiments may be toward a diverter sidewall 36 of an adjacent flow diverter 32 . In the embodiment shown in FIG. 1 , the sidewall angles 38 are equal, but it is to be appreciated that embodiments where sidewall angles 38 differ for one or more sidewalls 36 are contemplated within the present scope.
  • Utilizing flow diverters 32 causes the cooling flow 30 to spread over a greater portion of the turbine airfoil 10 thus providing more effective cooling of the turbine airfoil 10 .
  • a width 40 of the downstream wall 32 and/or the sidewall angle 38 can be varied to provide a desired amount of spread of the cooling flow 28 .
  • the diverter sidewalls 36 of adjacent flow diverters form a flow channel 42 preventing hot gas flow 12 from flowing between the cooling flow 30 and the downstream trench surface 22 thus preventing mixing of the hot gas flow 12 and the cooling flow 30 .
  • each flow diverter 32 comprises two diverter sidewalls 36 converging at a vertex 44 located axially downstream from, and at a substantially same lateral position as a corresponding cooling through hole 24 such that cooling flow 30 exiting the cooling through hole 24 is split or diverted as shown in FIG. 4 .
  • Each diverter sidewall 36 is disposed at a sidewall angle 38 and extends toward a diverter sidewall 36 of an adjacent flow diverter 32 .
  • the flow diverter 32 including a vertex 44 prevents a vortex from forming in the cooling flow 30 at an exit of the cooling through hole 24 , as well as causes the cooling flow 30 to spread over a greater portion of the turbine airfoil 10 .
  • each vertex 44 may be disposed at least partially within a corresponding cooling through hole 24 .
  • a flow diverter 32 of this configuration is capable of splitting or diverting the cooling flow 30 as the cooling flow 30 exits the cooling through hole 24 .
  • each flow diverter 32 is disposed laterally substantially between two cooling through holes 24 .
  • each flow diverter 32 includes a downstream wall 34 and two diverter sidewalls 36 disposed at a sidewall angle 38 .
  • the sidewall angles 38 are such that each diverter sidewall 36 extends toward convergence with the other diverter sidewall 36 of the same flow diverter 32 .
  • the cooling flow 30 does not split upon exit from the cooling through hole 24 , but spreads across the flow channel 42 between adjacent flow diverters 32 .
  • the cooling through holes 24 may have a number of shapes.
  • the cooling through holes 24 shown in FIG. 6 include a diffusion surface 46 located at a downstream exit portion of the cooling through hole 24 and which slopes radially inward below the trench floor 28 .
  • Cooling through holes 24 including the diffusion surface 46 provide additionally smooth transition of cooling flow 30 from the cooling through holes 24 to the outer surface 14 preventing blowing off of the cooling flow 30 into the hot gas flow 12 .
  • an edge 48 of the diffusion surface is coplanar with the diverter sidewall 36 , but other configurations and alignments of the edge 48 relative to the diverter sidewall 36 are contemplated within the present scope.
  • the turbine airfoil 10 comprises a substrate layer 50 and a coating layer 52 , which may include a thermal barrier coating (TBC) to provide additional thermal protection of the substrate layer 50 .
  • TBC thermal barrier coating
  • the cooling through holes 24 are disposed in the substrate layer 50 while the flow diverters 32 , upstream trench wall 20 and downstream trench surface 22 are disposed in the coating layer 52 and may be formed from TBC.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/054,535 2008-03-25 2008-03-25 Film cooling of turbine components Abandoned US20090246011A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US12/054,535 US20090246011A1 (en) 2008-03-25 2008-03-25 Film cooling of turbine components
JP2009057231A JP2009236112A (ja) 2008-03-25 2009-03-11 タービン部品のフィルム冷却
DE102009003634A DE102009003634A1 (de) 2008-03-25 2009-03-17 Filmkühlung von Turbinenkomponenten
FR0951711A FR2929323A1 (fr) 2008-03-25 2009-03-18 Procede de refroidissement d'une piece de turbine et piece de turbine correspondante
CN200910132498A CN101545381A (zh) 2008-03-25 2009-03-25 涡轮机构件的薄膜冷却

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/054,535 US20090246011A1 (en) 2008-03-25 2008-03-25 Film cooling of turbine components

Publications (1)

Publication Number Publication Date
US20090246011A1 true US20090246011A1 (en) 2009-10-01

Family

ID=41011319

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/054,535 Abandoned US20090246011A1 (en) 2008-03-25 2008-03-25 Film cooling of turbine components

Country Status (5)

Country Link
US (1) US20090246011A1 (de)
JP (1) JP2009236112A (de)
CN (1) CN101545381A (de)
DE (1) DE102009003634A1 (de)
FR (1) FR2929323A1 (de)

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100329846A1 (en) * 2009-06-24 2010-12-30 Honeywell International Inc. Turbine engine components
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
US20110123312A1 (en) * 2009-11-25 2011-05-26 Honeywell International Inc. Gas turbine engine components with improved film cooling
EP2557269A1 (de) * 2011-08-08 2013-02-13 Siemens Aktiengesellschaft Filmkühlung von Turbinenbauteilen
US20130045106A1 (en) * 2011-08-15 2013-02-21 General Electric Company Angled trench diffuser
US8608443B2 (en) 2010-06-11 2013-12-17 Siemens Energy, Inc. Film cooled component wall in a turbine engine
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US8938879B2 (en) 2011-02-14 2015-01-27 General Electric Company Components with cooling channels and methods of manufacture
US9028207B2 (en) 2010-09-23 2015-05-12 Siemens Energy, Inc. Cooled component wall in a turbine engine
US9181819B2 (en) 2010-06-11 2015-11-10 Siemens Energy, Inc. Component wall having diffusion sections for cooling in a turbine engine
US9441488B1 (en) * 2013-11-07 2016-09-13 United States Of America As Represented By The Secretary Of The Air Force Film cooling holes for gas turbine airfoils
US20160281511A1 (en) * 2012-11-16 2016-09-29 Siemens Aktiengesellschaft Modified surface around a hole
US9631505B2 (en) 2013-10-18 2017-04-25 Rolls-Royce Deutschland Ltd & Co Kg Device for cooling a wall of a component
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
US9957809B2 (en) 2011-11-24 2018-05-01 Siemens Aktiengesellschaft Modified interface around a hole
US10113433B2 (en) 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
CN108729953A (zh) * 2018-04-24 2018-11-02 哈尔滨工程大学 一种在端壁气膜孔上游布置新月形沙丘凸台结构的涡轮
US10378444B2 (en) 2015-08-19 2019-08-13 General Electric Company Engine component for a gas turbine engine
US10570747B2 (en) * 2017-10-02 2020-02-25 DOOSAN Heavy Industries Construction Co., LTD Enhanced film cooling system
CN112443361A (zh) * 2020-11-04 2021-03-05 西北工业大学 一种用于涡轮叶片的凹坑逆向气膜孔结构
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US11118461B2 (en) * 2018-03-29 2021-09-14 Mitsubishi Power, Ltd. Turbine rotor blade and gas turbine
US11168570B1 (en) 2020-08-27 2021-11-09 Raytheon Technologies Corporation Cooling arrangement for gas turbine engine components
US11352902B2 (en) 2020-08-27 2022-06-07 Aytheon Technologies Corporation Cooling arrangement including alternating pedestals for gas turbine engine components

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US8727727B2 (en) * 2010-12-10 2014-05-20 General Electric Company Components with cooling channels and methods of manufacture
EP2489836A1 (de) 2011-02-21 2012-08-22 Karlsruher Institut für Technologie Kühlbares Bauteil
US8601691B2 (en) * 2011-04-27 2013-12-10 General Electric Company Component and methods of fabricating a coated component using multiple types of fillers
JP2013100771A (ja) * 2011-11-08 2013-05-23 Central Research Institute Of Electric Power Industry 高温部品のフィルム冷却構造
US8858175B2 (en) * 2011-11-09 2014-10-14 General Electric Company Film hole trench
JP5696080B2 (ja) * 2012-03-22 2015-04-08 三菱重工業株式会社 被冷却構造部材、タービン翼、及びタービン
US9080451B2 (en) * 2012-06-28 2015-07-14 General Electric Company Airfoil
US20170089579A1 (en) * 2015-09-30 2017-03-30 General Electric Company Cmc articles having small complex features for advanced film cooling
WO2017171764A1 (en) * 2016-03-31 2017-10-05 Siemens Aktiengesellschaft Turbine airfoil with internal cooling channels having flow splitter feature
CN112145235B (zh) * 2020-09-24 2021-08-20 大连理工大学 一种ω型回转腔层板冷却结构
CN112145234B (zh) * 2020-09-24 2021-08-20 大连理工大学 一种ω型回转腔层板冷却结构

Citations (8)

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US5419681A (en) * 1993-01-25 1995-05-30 General Electric Company Film cooled wall
US5651662A (en) * 1992-10-29 1997-07-29 General Electric Company Film cooled wall
US5660525A (en) * 1992-10-29 1997-08-26 General Electric Company Film cooled slotted wall
US6234754B1 (en) * 1999-08-09 2001-05-22 United Technologies Corporation Coolable airfoil structure
US6234755B1 (en) * 1999-10-04 2001-05-22 General Electric Company Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture
US6984100B2 (en) * 2003-06-30 2006-01-10 General Electric Company Component and turbine assembly with film cooling
US7553534B2 (en) * 2006-08-29 2009-06-30 General Electric Company Film cooled slotted wall and method of making the same
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

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5651662A (en) * 1992-10-29 1997-07-29 General Electric Company Film cooled wall
US5660525A (en) * 1992-10-29 1997-08-26 General Electric Company Film cooled slotted wall
US5419681A (en) * 1993-01-25 1995-05-30 General Electric Company Film cooled wall
US6234754B1 (en) * 1999-08-09 2001-05-22 United Technologies Corporation Coolable airfoil structure
US6234755B1 (en) * 1999-10-04 2001-05-22 General Electric Company Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture
US6984100B2 (en) * 2003-06-30 2006-01-10 General Electric Company Component and turbine assembly with film cooling
US7553534B2 (en) * 2006-08-29 2009-06-30 General Electric Company Film cooled slotted wall and method of making the same
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

Cited By (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8371814B2 (en) 2009-06-24 2013-02-12 Honeywell International Inc. Turbine engine components
US20100329846A1 (en) * 2009-06-24 2010-12-30 Honeywell International Inc. Turbine engine components
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
US20110123312A1 (en) * 2009-11-25 2011-05-26 Honeywell International Inc. Gas turbine engine components with improved film cooling
US8529193B2 (en) 2009-11-25 2013-09-10 Honeywell International Inc. Gas turbine engine components with improved film cooling
US8608443B2 (en) 2010-06-11 2013-12-17 Siemens Energy, Inc. Film cooled component wall in a turbine engine
US9181819B2 (en) 2010-06-11 2015-11-10 Siemens Energy, Inc. Component wall having diffusion sections for cooling in a turbine engine
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US9028207B2 (en) 2010-09-23 2015-05-12 Siemens Energy, Inc. Cooled component wall in a turbine engine
US8938879B2 (en) 2011-02-14 2015-01-27 General Electric Company Components with cooling channels and methods of manufacture
US9771804B2 (en) 2011-08-08 2017-09-26 Siemens Aktiengesellschaft Film cooling of turbine blades or vanes
EP2557269A1 (de) * 2011-08-08 2013-02-13 Siemens Aktiengesellschaft Filmkühlung von Turbinenbauteilen
EP2559855A3 (de) * 2011-08-15 2014-08-27 General Electric Company Turbinenschaufel mit Filmkühllöcher sowie Verfahren zu deren Herstellung
US20130045106A1 (en) * 2011-08-15 2013-02-21 General Electric Company Angled trench diffuser
US9957809B2 (en) 2011-11-24 2018-05-01 Siemens Aktiengesellschaft Modified interface around a hole
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
US20160281511A1 (en) * 2012-11-16 2016-09-29 Siemens Aktiengesellschaft Modified surface around a hole
US9631505B2 (en) 2013-10-18 2017-04-25 Rolls-Royce Deutschland Ltd & Co Kg Device for cooling a wall of a component
US9441488B1 (en) * 2013-11-07 2016-09-13 United States Of America As Represented By The Secretary Of The Air Force Film cooling holes for gas turbine airfoils
US10378444B2 (en) 2015-08-19 2019-08-13 General Electric Company Engine component for a gas turbine engine
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US11286791B2 (en) 2016-05-19 2022-03-29 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US10570747B2 (en) * 2017-10-02 2020-02-25 DOOSAN Heavy Industries Construction Co., LTD Enhanced film cooling system
US11002137B2 (en) * 2017-10-02 2021-05-11 DOOSAN Heavy Industries Construction Co., LTD Enhanced film cooling system
US11118461B2 (en) * 2018-03-29 2021-09-14 Mitsubishi Power, Ltd. Turbine rotor blade and gas turbine
CN108729953A (zh) * 2018-04-24 2018-11-02 哈尔滨工程大学 一种在端壁气膜孔上游布置新月形沙丘凸台结构的涡轮
US11168570B1 (en) 2020-08-27 2021-11-09 Raytheon Technologies Corporation Cooling arrangement for gas turbine engine components
US11352902B2 (en) 2020-08-27 2022-06-07 Aytheon Technologies Corporation Cooling arrangement including alternating pedestals for gas turbine engine components
CN112443361A (zh) * 2020-11-04 2021-03-05 西北工业大学 一种用于涡轮叶片的凹坑逆向气膜孔结构

Also Published As

Publication number Publication date
FR2929323A1 (fr) 2009-10-02
CN101545381A (zh) 2009-09-30
DE102009003634A1 (de) 2009-10-01
JP2009236112A (ja) 2009-10-15

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AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:ITZEL, GARY MICHAEL;REEL/FRAME:020695/0195

Effective date: 20080317

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION