US20070297916A1 - Leading edge cooling using wrapped staggered-chevron trip strips - Google Patents

Leading edge cooling using wrapped staggered-chevron trip strips Download PDF

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Publication number
US20070297916A1
US20070297916A1 US11/473,893 US47389306A US2007297916A1 US 20070297916 A1 US20070297916 A1 US 20070297916A1 US 47389306 A US47389306 A US 47389306A US 2007297916 A1 US2007297916 A1 US 2007297916A1
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US
United States
Prior art keywords
trip strips
leading edge
turbine engine
engine component
component according
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
US11/473,893
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English (en)
Inventor
Jeffrey R. Levine
William Abdel-Messeh
Eleanor Kaufman
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
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First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=38349575&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=US20070297916(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to US11/473,893 priority Critical patent/US20070297916A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ABDEL-MESSEH, WILLIAM, KAUFMAN, ELEANOR, LEVINE, JEFFREY R.
Priority to JP2007160904A priority patent/JP2008002464A/ja
Priority to EP07252545.4A priority patent/EP1870561B1/fr
Publication of US20070297916A1 publication Critical patent/US20070297916A1/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
    • F01D5/187—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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the present invention relates to enhanced cooling of the leading edge of airfoil portions of turbine engine components using trip strips that are staggered and wrapped around the nose of the leading edge cavity.
  • FIG. 1 where there is shown an airfoil portion 10 of a turbine engine component 12 .
  • a radial flow leading edge cavity 14 is used to effect cooling of the leading edge region.
  • a turbine engine component broadly comprises an airfoil portion having a leading edge, a suction side, and a pressure side, a radial flow leading edge cavity through which a cooling fluid flows for cooling the leading edge, and means for generating a vortex in the leading edge cavity which impinges on a nose portion of the leading edge cavity.
  • the vortex generating means comprises a first set of trip strips which wrap around the nose portion of the leading edge cavity and a second set of trip strips. The first set of trip strips is staggered relative to the second set of trip strips.
  • FIG. 1 illustrates a prior art turbine engine component having a radial flow leading edge cavity
  • FIG. 2 illustrates a cross-section of a leading edge portion of an airfoil used in a turbine engine component having staggered and wrapped trip strips;
  • FIG. 3 illustrates the trip strips on the suction side of the leading edge portion
  • FIG. 4 illustrates the trip strips on the pressure side of the leading edge portion
  • FIG. 5 illustrates the placement of the leading edge of the staggered trip strips
  • FIG. 6 is a three dimensional view of the leading edge trip strips.
  • FIG. 7 illustrates the vortex generated in the leading edge cavity.
  • FIG. 2 illustrates the leading edge 30 of an airfoil portion 32 of a turbine engine component.
  • the leading edge 30 has a leading edge cavity 34 in which a cooling fluid, such as engine bleed air, flows in a radial direction.
  • the leading edge 30 also has a nose portion 36 and an external stagnation region 38 .
  • trip strips are desirable to provide adequate cooling of the leading edge, especially at the nose portion 36 of the airfoil portion 32 adjacent to the external stagnation region 38 .
  • the trip strip arrangement which will be discussed hereinafter provides high heat transfer to the leading edge 30 of the airfoil portion 32 .
  • a plurality of trip strips 40 are positioned on the pressure side 42 of the airfoil portion 32 , while, as shown in FIGS. 2 , 3 , and 6 , a plurality of trip strips 44 are placed on the suction side 46 of the airfoil portion 32 .
  • the trip strips 40 on the pressure side 42 are wrapped around the leading edge nose portion 36 .
  • the curvature of the leading edge nose portion 36 causes the trip strips 40 to be oriented more or less normal to the direction of flow 48 (see FIG. 6 ).
  • the flow is tripped and generates a large vortex 49 at the leading edge (see FIG. 7 ). This large vortex generates very high heat transfer coefficients at the leading edge nose 36 .
  • the trip strips 40 and the trip strips 44 are preferably staggered approximately one half pitch apart between the suction side 46 and the pressure side 42 of the airfoil portion 32 . As shown in FIGS. 2 and 7 , there is also a gap 47 between adjacent ones of the trip strips 40 and the trip strips 44 . Each gap 47 is preferably located along a parting line 70 of the airfoil portion 32 .
  • the orientation of the trip strips 40 and 44 in the cavity 34 also increases heat transfer at the leading edge 30 of the airfoil portion 32 .
  • the trip strips 40 and 44 may be oriented at an angle ⁇ of approximately 45 degrees relative to the flow direction 48 .
  • the leading edges 54 and 56 of the trip strips 40 and 44 are positioned in the region of highest heat load, in this case the leading edge nose 36 .
  • This trip strip orientation permits the creation of a turbulent vortex 49 in the cavity 34 .
  • the cooling fluid initially hits the leading edges 54 and 56 of the trip strip and separates from the airfoil surface. The flow then re-attaches downstream of the trip strip leading edges 54 and 56 and moves toward the divider rib 60 between the leading edge cavity 34 and the adjacent cavity 62 .
  • the particular orientation of the trip strip configuration allows for cooling flow to impinge on the leading edge nose 36 , further enhancing heat transfer.
  • the leading edge of the trip strips 40 and 44 is located near the nose 36 of the leading edge cavity 34 .
  • the trip strips 40 although skewed at an angle a with respect to the direction of flow 48 along the pressure-side wall 42 , become normal to the direction of flow 48 as they wrap around the nose 36 of the leading edge cavity 34 , increasing the turbulent vortex 49 generated by the trip strips 40 and 44 , and subsequently increasing the heat transfer coefficient.
  • the trip strips 40 and 44 may overlap with the trip strip 40 extending underneath the trip strip 44 , and vice-versa.
  • trip strips 40 have been described as being on the pressure side wall 42 of the airfoil portion, they could instead be mounted to the suction side wall 46 if desired. In such a situation, the trip strips 44 would be mounted to the pressure side wall 42 .
  • the staggered and 45 degree angled trip strips generate a vortex that impinges flow onto the nose 36 of the leading edge cavity.
  • the trip strip configuration of the present invention maintains a P/E ratio between 3 and 25 where P is the radial pitch in between trip strips and E is trip strip height. Further, the trip strip configuration described herein maintains an E/H ratio of between 0.15 and 1.50 where E is trip strip height and H is the height of the cavity 34 .
  • Airflow testing has shown that the heat transfer coefficients at the leading edge of the airfoil adjacent to the external stagnation region when using the staggered trip strips of the present invention are enhanced by approximately two times, greatly increasing airfoil oxidation and thermo-mechanical fatigue cracking life.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US11/473,893 2006-06-22 2006-06-22 Leading edge cooling using wrapped staggered-chevron trip strips Abandoned US20070297916A1 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
US11/473,893 US20070297916A1 (en) 2006-06-22 2006-06-22 Leading edge cooling using wrapped staggered-chevron trip strips
JP2007160904A JP2008002464A (ja) 2006-06-22 2007-06-19 タービンエンジン構成部品
EP07252545.4A EP1870561B1 (fr) 2006-06-22 2007-06-22 Refroidissement du bord d'attaque d'un composant de turbine à gaz par générateurs de turbulence

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/473,893 US20070297916A1 (en) 2006-06-22 2006-06-22 Leading edge cooling using wrapped staggered-chevron trip strips

Publications (1)

Publication Number Publication Date
US20070297916A1 true US20070297916A1 (en) 2007-12-27

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ID=38349575

Family Applications (1)

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US11/473,893 Abandoned US20070297916A1 (en) 2006-06-22 2006-06-22 Leading edge cooling using wrapped staggered-chevron trip strips

Country Status (3)

Country Link
US (1) US20070297916A1 (fr)
EP (1) EP1870561B1 (fr)
JP (1) JP2008002464A (fr)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090087312A1 (en) * 2007-09-28 2009-04-02 Ronald Scott Bunker Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method
US20100054952A1 (en) * 2006-11-09 2010-03-04 Siemens Aktiengesellschaft Turbine Blade
US20120148383A1 (en) * 2010-12-14 2012-06-14 Gear Paul J Gas turbine vane with cooling channel end turn structure
US8757961B1 (en) * 2011-05-21 2014-06-24 Florida Turbine Technologies, Inc. Industrial turbine stator vane
WO2014159589A1 (fr) * 2013-03-14 2014-10-02 United Technologies Corporation Refroidissement d'un composant d'un moteur à turbine à gaz avec des bandes de déclenchement en regard imbriquées
WO2014159800A1 (fr) * 2013-03-14 2014-10-02 United Technologies Corporation Barrette perturbatrice en forme de chevron à angle obtus
US20160230664A1 (en) * 2013-10-29 2016-08-11 United Technologies Corporation Pedestals with heat transfer augmenter
US9850762B2 (en) 2013-03-13 2017-12-26 General Electric Company Dust mitigation for turbine blade tip turns
US9957816B2 (en) 2014-05-29 2018-05-01 General Electric Company Angled impingement insert
US9995173B2 (en) 2013-08-20 2018-06-12 United Technologies Corporation Ducting platform cover plate
US9995148B2 (en) 2012-10-04 2018-06-12 General Electric Company Method and apparatus for cooling gas turbine and rotor blades
US10233775B2 (en) 2014-10-31 2019-03-19 General Electric Company Engine component for a gas turbine engine
US10280785B2 (en) 2014-10-31 2019-05-07 General Electric Company Shroud assembly for a turbine engine
US10352177B2 (en) 2016-02-16 2019-07-16 General Electric Company Airfoil having impingement openings
US10364684B2 (en) 2014-05-29 2019-07-30 General Electric Company Fastback vorticor pin
US10406596B2 (en) 2015-05-01 2019-09-10 United Technologies Corporation Core arrangement for turbine engine component
US10422235B2 (en) 2014-05-29 2019-09-24 General Electric Company Angled impingement inserts with cooling features
US10465530B2 (en) 2013-12-20 2019-11-05 United Technologies Corporation Gas turbine engine component cooling cavity with vortex promoting features
US10563514B2 (en) 2014-05-29 2020-02-18 General Electric Company Fastback turbulator
US10577944B2 (en) 2017-08-03 2020-03-03 General Electric Company Engine component with hollow turbulators
US10590778B2 (en) 2017-08-03 2020-03-17 General Electric Company Engine component with non-uniform chevron pins
US10690055B2 (en) 2014-05-29 2020-06-23 General Electric Company Engine components with impingement cooling features
US10934856B2 (en) * 2014-10-15 2021-03-02 Honeywell International Inc. Gas turbine engines with improved leading edge airfoil cooling
US11788416B2 (en) 2019-01-30 2023-10-17 Rtx Corporation Gas turbine engine components having interlaced trip strip arrays
US11952913B2 (en) * 2022-04-27 2024-04-09 Shanghai Jiaotong University Turbine blade with improved swirl cooling performance at leading edge and engine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8690538B2 (en) * 2006-06-22 2014-04-08 United Technologies Corporation Leading edge cooling using chevron trip strips
US8348613B2 (en) 2009-03-30 2013-01-08 United Technologies Corporation Airflow influencing airfoil feature array
US10422233B2 (en) * 2015-12-07 2019-09-24 United Technologies Corporation Baffle insert for a gas turbine engine component and component with baffle insert
US10280841B2 (en) 2015-12-07 2019-05-07 United Technologies Corporation Baffle insert for a gas turbine engine component and method of cooling
US10337334B2 (en) 2015-12-07 2019-07-02 United Technologies Corporation Gas turbine engine component with a baffle insert
US10577947B2 (en) 2015-12-07 2020-03-03 United Technologies Corporation Baffle insert for a gas turbine engine component

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US4514144A (en) * 1983-06-20 1985-04-30 General Electric Company Angled turbulence promoter
US5232343A (en) * 1984-05-24 1993-08-03 General Electric Company Turbine blade
US4786233A (en) * 1986-01-20 1988-11-22 Hitachi, Ltd. Gas turbine cooled blade
US5052889A (en) * 1990-05-17 1991-10-01 Pratt & Whintey Canada Offset ribs for heat transfer surface
US5246340A (en) * 1991-11-19 1993-09-21 Allied-Signal Inc. Internally cooled airfoil
US5700132A (en) * 1991-12-17 1997-12-23 General Electric Company Turbine blade having opposing wall turbulators
US5681144A (en) * 1991-12-17 1997-10-28 General Electric Company Turbine blade having offset turbulators
US5695321A (en) * 1991-12-17 1997-12-09 General Electric Company Turbine blade having variable configuration turbulators
US5431537A (en) * 1994-04-19 1995-07-11 United Technologies Corporation Cooled gas turbine blade
US5472316A (en) * 1994-09-19 1995-12-05 General Electric Company Enhanced cooling apparatus for gas turbine engine airfoils
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US20050025623A1 (en) * 2003-08-01 2005-02-03 Snecma Moteurs Cooling circuits for a gas turbine blade

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Publication number Priority date Publication date Assignee Title
US20100054952A1 (en) * 2006-11-09 2010-03-04 Siemens Aktiengesellschaft Turbine Blade
US8215909B2 (en) * 2006-11-09 2012-07-10 Siemens Aktiengesellschaft Turbine blade
US8376706B2 (en) * 2007-09-28 2013-02-19 General Electric Company Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method
US20090087312A1 (en) * 2007-09-28 2009-04-02 Ronald Scott Bunker Turbine Airfoil Concave Cooling Passage Using Dual-Swirl Flow Mechanism and Method
US8821111B2 (en) * 2010-12-14 2014-09-02 Siemens Energy, Inc. Gas turbine vane with cooling channel end turn structure
US20120148383A1 (en) * 2010-12-14 2012-06-14 Gear Paul J Gas turbine vane with cooling channel end turn structure
US8757961B1 (en) * 2011-05-21 2014-06-24 Florida Turbine Technologies, Inc. Industrial turbine stator vane
US9995148B2 (en) 2012-10-04 2018-06-12 General Electric Company Method and apparatus for cooling gas turbine and rotor blades
US9850762B2 (en) 2013-03-13 2017-12-26 General Electric Company Dust mitigation for turbine blade tip turns
US10215031B2 (en) 2013-03-14 2019-02-26 United Technologies Corporation Gas turbine engine component cooling with interleaved facing trip strips
WO2014159589A1 (fr) * 2013-03-14 2014-10-02 United Technologies Corporation Refroidissement d'un composant d'un moteur à turbine à gaz avec des bandes de déclenchement en regard imbriquées
WO2014159800A1 (fr) * 2013-03-14 2014-10-02 United Technologies Corporation Barrette perturbatrice en forme de chevron à angle obtus
US10626729B2 (en) 2013-03-14 2020-04-21 United Technologies Corporation Obtuse angle chevron trip strip
US9995173B2 (en) 2013-08-20 2018-06-12 United Technologies Corporation Ducting platform cover plate
US10247099B2 (en) * 2013-10-29 2019-04-02 United Technologies Corporation Pedestals with heat transfer augmenter
US20160230664A1 (en) * 2013-10-29 2016-08-11 United Technologies Corporation Pedestals with heat transfer augmenter
US10465530B2 (en) 2013-12-20 2019-11-05 United Technologies Corporation Gas turbine engine component cooling cavity with vortex promoting features
US10563514B2 (en) 2014-05-29 2020-02-18 General Electric Company Fastback turbulator
US10690055B2 (en) 2014-05-29 2020-06-23 General Electric Company Engine components with impingement cooling features
US10364684B2 (en) 2014-05-29 2019-07-30 General Electric Company Fastback vorticor pin
US9957816B2 (en) 2014-05-29 2018-05-01 General Electric Company Angled impingement insert
US10422235B2 (en) 2014-05-29 2019-09-24 General Electric Company Angled impingement inserts with cooling features
US10934856B2 (en) * 2014-10-15 2021-03-02 Honeywell International Inc. Gas turbine engines with improved leading edge airfoil cooling
US10280785B2 (en) 2014-10-31 2019-05-07 General Electric Company Shroud assembly for a turbine engine
US10233775B2 (en) 2014-10-31 2019-03-19 General Electric Company Engine component for a gas turbine engine
US10406596B2 (en) 2015-05-01 2019-09-10 United Technologies Corporation Core arrangement for turbine engine component
US11148191B2 (en) 2015-05-01 2021-10-19 Raytheon Technologies Corporation Core arrangement for turbine engine component
US10352177B2 (en) 2016-02-16 2019-07-16 General Electric Company Airfoil having impingement openings
US10577944B2 (en) 2017-08-03 2020-03-03 General Electric Company Engine component with hollow turbulators
US10590778B2 (en) 2017-08-03 2020-03-17 General Electric Company Engine component with non-uniform chevron pins
US11788416B2 (en) 2019-01-30 2023-10-17 Rtx Corporation Gas turbine engine components having interlaced trip strip arrays
US11952913B2 (en) * 2022-04-27 2024-04-09 Shanghai Jiaotong University Turbine blade with improved swirl cooling performance at leading edge and engine

Also Published As

Publication number Publication date
EP1870561B1 (fr) 2017-04-05
EP1870561A2 (fr) 2007-12-26
JP2008002464A (ja) 2008-01-10
EP1870561A3 (fr) 2010-12-22

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