EP2131109A2 - Gegenwirbel-Doppel-Filmkühlbohrungsdesign - Google Patents

Gegenwirbel-Doppel-Filmkühlbohrungsdesign Download PDF

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Publication number
EP2131109A2
EP2131109A2 EP09251512A EP09251512A EP2131109A2 EP 2131109 A2 EP2131109 A2 EP 2131109A2 EP 09251512 A EP09251512 A EP 09251512A EP 09251512 A EP09251512 A EP 09251512A EP 2131109 A2 EP2131109 A2 EP 2131109A2
Authority
EP
European Patent Office
Prior art keywords
film cooling
vortex
film
wall
cooling
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Withdrawn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
EP09251512A
Other languages
English (en)
French (fr)
Other versions
EP2131109A3 (de
Inventor
Christopher W. Strock
Paul M. Lutjen
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 EP2131109A2 publication Critical patent/EP2131109A2/de
Publication of EP2131109A3 publication Critical patent/EP2131109A3/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/11—Two-dimensional triangular
    • 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
    • F05D2250/12—Two-dimensional rectangular
    • 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
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • the present invention relates to film cooling, and more particularly to structures and methods for providing vortex film cooling flows along gas turbine engine components.
  • Gas turbine engines utilize hot fluid flows in order to generate thrust or other usable power.
  • Modem gas turbine engines have increased working fluid temperatures in order to increase engine operating efficiency.
  • high temperature fluids pose a risk of damage to engine components, such as turbine blades and vanes.
  • High melting point superalloys and specialized coatings e.g., thermal barrier coatings
  • thermal barrier coatings have been used to help avoid thermally induced damage to engine components, but operating temperatures in modem gas turbine engines can still exceed superalloy melting points and coatings can become damaged or otherwise fail over time.
  • Cooling fluids have also been used to protect engine components, often in conjunction with the use of high temperature alloys and specialized coatings.
  • One method of using cooling fluids is called impingement cooling, which involves directing a relatively cool fluid (e.g., compressor bleed air) against a surface of a component exposed to high temperatures in order to absorb thermal energy into the cooling fluid that is then carried away from the component to cool it.
  • Impingement cooling is typically implemented with internal cooling passages. However, impingement cooling alone may not be sufficient to maintain suitable component temperatures in operation.
  • An alternative method of using cooling fluids is called film cooling, which involves providing a flow of relatively cool fluid from film cooling holes in order to create a thermally insulative barrier between a surface of a component and a relatively hot fluid flow.
  • Cooling flows of any type can present efficiency loss for an engine. The more fluid that is redirected within an engine for cooling purposes, the less efficient the engine tends to be in producing thrust or another usable power output. Therefore, fewer and smaller cooling holes with less dense cooling hole patterns are desirable.
  • the present invention provides an alternative method and apparatus for film cooling gas turbine engine components.
  • An apparatus for use in a gas turbine engine includes a wall defining an exterior face, a first film cooling passage extending through the wall for providing film cooling to the exterior face of the wall, and a second film cooling passage extending through the wall adjacent to the first film cooling passage for providing film cooling to the exterior face of the wall.
  • the first film passage includes a first vortex-generating structure for inducing a vortex in a first rotational direction in a cooling fluid passing therethrough
  • the second film passage includes a second vortex-generating structure for inducing a vortex in a second rotational direction in a cooling fluid passing therethrough.
  • the first and second rotational directions are substantially opposite one another.
  • FIG. 1 is a perspective view of an exemplary film cooled turbine blade.
  • FIG. 2A is a cross-sectional view of a portion of a film cooled gas turbine engine component.
  • FIGS. 2B-2E are cross-sectional views of portions of the film cooled gas turbine engine component taken along lines B-B, C-C, D-D and E-E, respectively, of FIG. 2A .
  • FIG. 3 is a schematic view of a pair of film cooling passages.
  • FIGS. 4A-4C are cross-sectional views of exemplary embodiments of vortex-generating structures.
  • FIG. 5 is a schematic view of another embodiment of a film cooling passage.
  • FIG. 6A is a cross-sectional view of a portion of another embodiment of a film cooled gas turbine engine component.
  • FIGS. 6B and 6C are cross-sectional views of a portion of the film cooled gas turbine engine component, taken along lines B-B and C-C, respectively, of FIG. 6A .
  • the present invention in general, relates to structures and methods for generating a counter-rotating vortex film cooling flow along a surface of a component for a gas turbine engine exposed to hot gases, such as a turbine blade, vane, shroud, duct wall, etc.
  • a film cooling flow can provide a thermally insulative barrier between the gas turbine engine component and the hot gases.
  • a pair of film cooling passages have closely-spaced outlets at an exterior surface (or face) of the component that is exposed to the hot gases.
  • a vortex-generating structure is positioned within each film cooling passage of the pair to generate a vortex flow.
  • the vortex-generating structures can comprise helical ribs (or rifling), with the helical ribs of the first and second film cooling passages winding in opposite directions. Additional features and benefits of the present invention will be recognized in light of the description that follows.
  • FIG. 1 is a perspective view of an exemplary film cooled turbine blade 20 having an airfoil portion 22. Pairs of film cooling hole outlets 24 are positioned along exterior sidewall surfaces of the airfoil portion 22 (only one side of the airfoil portion 22 is visible in FIG. 1 ). The hole outlets 24 of each pair are located at substantially the same streamwise location along the airfoil portion 22. During operation, the pairs of film cooling hole outlets 24 eject a film cooling fluid (e.g., compressor bleed air) to provide a thermally insulative barrier along portions of the turbine blade 20 exposed to hot gases.
  • a film cooling fluid e.g., compressor bleed air
  • turbine blade 20 is shown merely as one example of a gas turbine engine component that can be film cooled according to the present invention.
  • the present invention is equally applicable to other types of gas turbine engine components, such as vanes, shrouds, duct walls, etc.
  • FIG. 2A is a cross-sectional view of a portion of a wall 30 of a film cooled gas turbine engine component.
  • the wall 30 has an exterior surface 32 that is exposed to a hot gas flow 34.
  • a substantially cylindrically shaped first film cooling passage 36A extends through the wall 30 to a first outlet 38A located at the exterior surface 32 of the wall 30, the first film cooling passage 36A being angled slightly toward a free stream direction of the hot gas flow 34.
  • the first outlet 38A can be shaped similarly to a cross-sectional profile of an interior portion of the first film cooling passage 36A.
  • a substantially helically-shaped vortex generating rib 40A is positioned along an interior surface of the first film cooling passage 36A, and can be formed using electro-discharge machining (EDM), stem drilling, casting, or other suitable processes.
  • EDM electro-discharge machining
  • a film cooling fluid 42 passes through the first film cooling passage 36A and is ejected from the first outlet 38A, and then forms a thermally insulative barrier along the exterior surface 32 of the wall 30 that extends downstream from the first outlet 38A.
  • a second film cooling passage 36B can be positioned adjacent to the first film cooling passage 36A and have a similar configuration.
  • the first and second film cooling passages 36A and 36B respectively can be arranged substantially parallel to one another, angled toward one another (i.e., in a non-parallel arrangement), or have other configurations. Furthermore, the first and second film cooling passages 36A and 36B respectively can be connected to a common fluid supply manifold (not shown), or otherwise branched together opposite the first and second outlets 38A and 38B respectively.
  • FIG. 2B is a cross-sectional view of a portion of the wall 30 of the film cooled gas turbine engine component, taken along line B-B of FIG. 2A .
  • the pair of first and second film cooling passages 36A and 36B respectively have a first and second substantially helically-shaped vortex-generating ribs 40A and 40B, respectively.
  • the first vortex-generating rib 40A generates a vortex flow within the first film cooling passage 36A in generally a first rotational direction 44 (e.g., clockwise).
  • the second vortex-generating rib 40B generates a vortex flow within the second film cooling passage 36B in generally a second rotational direction 46 (e.g., counter-clockwise).
  • first rotational direction 44 e.g., clockwise
  • the second vortex-generating rib 40B generates a vortex flow within the second film cooling passage 36B in generally a second rotational direction 46 (e.g., counter-clockwise).
  • 2B is taken at a location within the wall 30, upstream from the first and second outlets 38A and 38B respectively of the film cooling passages 36A and 36B (see FIG. 2A ), and vortex flows are present within the film cooling passages 36A and 36B upstream from the first and second outlets 38A and 38B respectively.
  • FIG. 2C is a cross-sectional view of a portion of the wall 30 of the film cooled gas turbine engine component, taken along line C-C of FIG. 2A just downstream from the first and second outlets 38A and 38B respectively (not shown in FIG, 2C ) along the exterior surface 32 of the wall 30 (relative to the hot gas flow 34).
  • cooling fluid 42 from both the first and second film cooling passages 36A and 36B respectively have mixed together to form a contiguous jet of the film cooling fluid 42 upon leaving the first and second outlets 38A and 38B, respectively (not shown in FIG, 2C ).
  • a boundary 48 is defined between the jet of the film cooling fluid 42 and the hot gas flow 34.
  • the cooling fluid 42 passes along the exterior surface 32 of the wall 30, attached thereto, that is, the film cooling fluid 42 remains substantially in contact with the exterior surface 32 to form a barrier between the exterior surface 32 and the hot gas flow 34.
  • the film cooling fluid 42 includes counter-rotating vortices defined by fluid rotating in the substantially opposite first and second rotational directions 44 and 46 respectively.
  • the first and second rotational directions 44 and 46 respectively can be arranged to generally oppose a tendency of the hot gas flow 34 to move toward the exterior surface 32 of the wall 30, thereby reducing "liftoff” or "flow separation” that occur when a portion of the hot gas flow 34 extends between the film cooling fluid 42 and the exterior surface 32 of the wall 30.
  • the first and second rotational directions 44 and 46 respectively are arranged to flow generally toward the exterior surface 32 at a location where the vortexes adjoin each other, and generally away from the exterior surface 32 at lateral boundaries of the jet of the film cooling fluid 42.
  • FIG. 2D is a cross-sectional view of a portion of the wall 30 of the film cooled gas turbine engine component, taken along line D-D of FIG. 2A downstream from the cross-sectional view shown in FIG. 2C (relative to the hot gas flow 34).
  • the counter-rotating vortices defined by the film cooling fluid 42 rotating in the substantially opposite first and second rotational directions 44 and 46 respectively causes mixing with the hot gas flow 34 at or near the boundary 48, which can reduce momentum of the counter-rotating vortices of the film cooling fluid 42 and also reduce or disrupt momentum of the hot gas flow 34 in a direction toward the wall 30.
  • This mixing can help reduce "liftoff" of the film cooling fluid 42, such that the film cooling fluid 42 remains substantially attached to the exterior surface 32 of the wall.
  • FIG. 2E is a cross-sectional view of a portion of the wall 30 of the film cooled gas turbine engine component, taken along line E-E of FIG. 2A downstream from the cross-sectional view of FIG. 2D .
  • mixing of the film cooling fluid 42 with the hot gas flow 34 (not labeled in FIG. 2E ) has formed a mixed fluid zone 48 around the original location of the boundary 48, which is no longer a distinct transition.
  • the film cooling fluid 42 has lost essentially all rotational kinetic energy, meaning the counter-rotating vortices have substantially ceased to rotate.
  • the film cooling fluid 42 still moves downstream along wall 30 substantially attached to the exterior surface 32.
  • the film cooling fluid 42 will inevitably degrade as it continues downstream along the exterior surface 32 of the wall 30.
  • the present invention can allow the film cooling fluid 42 to provide a relatively effective thermal barrier that is substantially attached to the exterior surface 32 for a relatively long distance along the wall 32 downstream from the first and second outlets 38A and 38B respectively.
  • FIG. 3 is a schematic view of the pair of first and second film cooling passages 36A and 36B respectively.
  • the first and second film cooling passages 36A and 36B respectively define first and second central axes 50A and 50B, respectively.
  • the first and second central axes 50A and 50B respectively are arranged substantially parallel to one another, and are closely spaced apart by a distance S.
  • the term "closely spaced” means spaced from each other on the order of a few diameters. For example, the spacing could be greater than one and up to ten diameters, or greater than one and up to three diameters.
  • the first film cooling passage 36A has a radius R A
  • the second film cooling passage has a radius R B .
  • the radii R A and R B can be substantially equal.
  • the first vortex-generating structure 40A has a pitch P A
  • the second vortex-generating structure 40B has a pitch P B .
  • the pitches P A and P B can be substantially constant (as shown in FIG. 3 ) or variable along lengths of the first and second film cooling passages 36A and 36B, respectively.
  • FIGS. 4A, 4B, and 4C are cross-sectional views of exemplary embodiments of vortex-generating structures 140A, 140B, and 140C, respectively, each defining a height H t and a width W t .
  • the vortex-generating structure 140A shown in FIG. 4A has a substantially rectangular cross-sectional shape
  • the vortex-generating structure 140B shown in FIG. 4B has a substantially triangular cross-sectional shape
  • the vortex-generating structure 140C shown in FIG. 4C has a substantially arcuate cross-sectional shape. It should be understood that further cross-sectional shapes can be utilized in alternative embodiments.
  • the first and second film cooling passages 36A and 36B and the first and second vortex-generating structures 40A and 40B can be described as having vortex generating structures with a pitch P that is a multiple of a radius R, where P represents either the pitch P A or P B and R represents the corresponding radius R A or R B .
  • the pitch P can be in the range of approximately 1 to 10 times the radius R, or alternatively in the range of approximately 1.5 to 3 times the radius R.
  • a ratio of the height of vortex-generating structure H t over the diameter of the associated film cooling passage (i.e., two time the radius R A or R B ) can be between approximately 0.05 and 0.5, or alternatively between approximately 0.1 and 0.3.
  • a ratio of the width W t over the height H t of the vortex-generating structures 40A and 40B can be between approximately 0.5 and 4, or alternatively between approximately 0.5 and 1.5.
  • the distance S between the axes 50A and 50B can be less than approximately ten times the radius R, or alternatively between approximately two to six times the radius R.
  • a length of the first and second film cooling passages 36A and 36B respectively can be at least approximately three to ten times a hydraulic diameter at the respective first and second outlets 38A and 38B, or alternatively at least approximately 5 to ten times the hydraulic diameter at the respective first and second outlets 38A and 38B (where the hydraulic diameter is four times the area divided by the perimeter).
  • FIG. 5 is a schematic view of an alternative embodiment of a film cooling passage 36 of the present invention (applicable to either one of the pair of film cooling passages 36A or 36B).
  • the film cooling passage 36 includes two sets of helical vortex-generating ribs 46C and 46D that wind in the same direction, adjacent one another (the vortex-generating rib 46C is represented by a weighted line in FIG. 5 , for illustrative purposes).
  • the rib 46C has a pitch P 1 and the rib 46D has a pitch P 2 .
  • the pitches P 1 and P 2 can be substantially equal.
  • the pitches P 1 and P 2 can be substantially constant (as shown in FIG. 3 ) or variable along lengths of the film cooling passage 36. In further embodiments, still more additional ribs can be provided.
  • the present invention provides numerous advantages. For example, while mixing of film cooling fluid jets with hot gas flows represents an efficiency loss, that loss is balanced against improved film cooling effectiveness per film cooling passage. This can permit a given level of film cooling to be provided to a given component with a relatively small number of film cooling passages for a given film cooling fluid flow rate and/or increasing spacing between pairs of cooling hole outlets. Moreover, even with the presence of paired, closely spaced cooling hole outlets, the present invention can provide film cooling to a given surface area with a relatively low density of cooling holes and a relatively low total cooling hole area. Film cooling according to the present invention can help allow gas turbine engine components to operate in higher temperature environments with a relatively low risk of thermal damage.
  • FIGS. 6A , 6B and 6C illustrate an alternative embodiment of the present invention, configured to produce a different effect from the previously described embodiments.
  • FIG. 6A is a cross-sectional view of another embodiment of a portion of a wall 30 of the film cooled gas turbine engine component.
  • FIG. 6B is a cross sectional view of a portion of the film cooled gas turbine engine component 30, taken along line B-B of FIG. 6A .
  • the first film cooling passage 36A has a first helical vortex-generating rib 40C, which winds in an opposite direction with respect to the first vortex-generating rib 40A of previously-described embodiments, and a second helical vortex-generating rib 40D, which winds in an opposite direction with respect to the second vortex-generating rib 40B of previously-described embodiments (vortex-generating ribs 40A and 40B are not shown in FIG. 6B ).
  • the film cooling fluid 42 rotates in the second rotational direction 46 (e.g., counter-clockwise) within the first film cooling passage 36A
  • the film cooling fluid 42 rotates in the first rotational direction 44 (e.g., clockwise) within the second film cooling passage 36B.
  • FIG. 6C is a cross sectional view of a portion of the film cooled gas turbine engine component 30, taken along line C-C of FIG. 6A (i.e., downstream from an outlet of the film cooling passage 36A).
  • the first and second rotational directions 44 and 46 are arranged to flow generally away from the exterior surface 32 at a location where the vortexes adjoin each other, and generally toward the exterior surface 32 at lateral boundaries of the jet of the film cooling fluid 42.
  • This configuration would essentially encourage liftoff of the fluid 42 from the exterior surface 32 (i.e., the entrainment of the hot gas flow 34 between the exterior surface 32 and the cooling fluid 42), which may be desirable for fluidic injection applications, etc.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09251512.1A 2008-06-06 2009-06-08 Gegenwirbel-Doppel-Filmkühlbohrungsdesign Withdrawn EP2131109A3 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/157,115 US20090304494A1 (en) 2008-06-06 2008-06-06 Counter-vortex paired film cooling hole design

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Publication Number Publication Date
EP2131109A2 true EP2131109A2 (de) 2009-12-09
EP2131109A3 EP2131109A3 (de) 2014-01-01

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EP09251512.1A Withdrawn EP2131109A3 (de) 2008-06-06 2009-06-08 Gegenwirbel-Doppel-Filmkühlbohrungsdesign

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EP2918782A1 (de) * 2014-03-11 2015-09-16 United Technologies Corporation Bauteil mit Kühlungsloch mit Wendelnut und zugehöriges Gasturbinenkraftwerk
EP2971671A4 (de) * 2013-03-15 2016-11-02 United Technologies Corp Kühlkanäle für gasturbinenmotorteile
EP3156597B1 (de) * 2015-10-12 2019-11-27 United Technologies Corporation Kühllöcher einer turbine

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US20130195650A1 (en) * 2012-01-27 2013-08-01 Adebukola O. Benson Gas Turbine Pattern Swirl Film Cooling
US9416665B2 (en) * 2012-02-15 2016-08-16 United Technologies Corporation Cooling hole with enhanced flow attachment
US10689986B1 (en) * 2012-06-01 2020-06-23 United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration High blowing ratio high effectiveness film cooling configurations
EP2961964B1 (de) 2013-02-26 2020-10-21 United Technologies Corporation Bauteil eines gasturbinentriebwerks und zugehöriges verfahren zur herstellung einer öffnung
US20150003962A1 (en) * 2013-06-27 2015-01-01 Bruce L. Smith Apparatus for reducing a temperature gradient of mainstream fluid downstream of an airfoil in a gas turbine engine
WO2015094531A1 (en) * 2013-12-20 2015-06-25 United Technologies Corporation Gas turbine engine component cooling cavity with vortex promoting features
EP3502418B1 (de) 2016-08-22 2021-05-05 Doosan Heavy Industries & Construction Co., Ltd. Gasturbinenschaufel
WO2018038507A1 (ko) * 2016-08-22 2018-03-01 두산중공업 주식회사 가스 터빈 블레이드
KR102000830B1 (ko) 2017-09-11 2019-07-16 두산중공업 주식회사 가스 터빈 블레이드
US10539026B2 (en) * 2017-09-21 2020-01-21 United Technologies Corporation Gas turbine engine component with cooling holes having variable roughness
US20190218917A1 (en) * 2018-01-17 2019-07-18 General Electric Company Engine component with set of cooling holes
CN113006879B (zh) * 2021-03-19 2023-06-23 西北工业大学 一种有漩涡发生器的航空发动机涡轮气膜冷却孔
CN114109518A (zh) * 2021-11-29 2022-03-01 西安交通大学 一种涡轮叶片前缘带肋旋流-气膜复合冷却结构

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