EP3279432A1 - Schaufel mit einem oder mehreren sockeln mit genoppter oberfläche zur kühlung - Google Patents

Schaufel mit einem oder mehreren sockeln mit genoppter oberfläche zur kühlung Download PDF

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Publication number
EP3279432A1
EP3279432A1 EP16182733.2A EP16182733A EP3279432A1 EP 3279432 A1 EP3279432 A1 EP 3279432A1 EP 16182733 A EP16182733 A EP 16182733A EP 3279432 A1 EP3279432 A1 EP 3279432A1
Authority
EP
European Patent Office
Prior art keywords
side inner
aerofoil
pedestal
pressure side
suction side
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Withdrawn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
EP16182733.2A
Other languages
English (en)
French (fr)
Inventor
Dawid Frach
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.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to EP16182733.2A priority Critical patent/EP3279432A1/de
Publication of EP3279432A1 publication Critical patent/EP3279432A1/de
Withdrawn legal-status Critical Current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
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • 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

Definitions

  • the present invention relates to turbomachine components having an aerofoil, such as a vane or a blade, and more particularly to turbomachine components having aerofoils that include pedestals for cooling of the aerofoil of the turbomachine component in gas turbine engines.
  • present pedestals designs may be improved to enhance further cooling of the pedestals resulting from flow of the cooling fluid over and in contact with surfaces of the pedestals.
  • the object of the present disclosure is to provide a pedestal design wherein cooling of the pedestal arranged within the aerofoil is improved.
  • an aerofoil for a gas turbine engine has a pressure side wall and a suction side wall.
  • the pressure side and the suction side walls extend in a radial direction.
  • the pressure side wall and the suction side wall join each other at a leading edge and a trailing edge.
  • the pressure side wall has a pressure side outer surface and a pressure side inner surface.
  • the suction side wall has a suction side outer surface and a suction side inner surface.
  • the pressure side inner surface and the suction side inner surface are opposing surfaces.
  • a cooling passage is arranged between the pressure side inner surface and the suction side inner surface.
  • a plurality of pedestals extending longitudinally between the pressure side inner surface and the suction side inner surface are arranged within the cooling passage.
  • the plurality of pedestals includes one or more pedestal having dimpled surface.
  • the dimpled surface of the pedestals provides a different aerodynamic characteristic to the pedestals as compared to a pedestal without a dimpled surface, i.e. the point at which the cooling air flow contacting the pedestal surface breaks away from the pedestal surface, i.e. the separation point, is further downstream at the pedestal surface for the dimpled pedestal surface as compared to a pedestal surface without dimples for example a pedestal having a smooth surface.
  • the cooling air flowing around the pedestals remains in contact with the pedestal surface for a longer time and over a greater area of the pedestal surface as compared to a pedestal surface without dimples, and thus the cooling efficiency due to cooling air flowing over and in contact with the pedestal with dimpled surface is greater as compared to cooling efficiency due to cooling air flowing in contact with a pedestal without dimpled surface.
  • the one or more pedestal having dimpled surface includes at least one pedestal joining the pressure side inner surface and the suction side inner surface i.e. the pedestal is connected on one of its end with the pressure side inner surface and on its other end with the suction side inner surface and longitudinally extends all the way from the pressure side inner surface to the suction side inner surface.
  • the pedestal acts as a thermal bridge between the pressure side inner surface and the suction side inner surface and thereby between the pressure side wall and the suction side wall.
  • the pedestal with dimpled surface has a larger surface area compared to a similarly placed pedestal that does not extend the entire way between the pressure side inner surface and the suction side inner surface, and larger surface area results in more number of dimples and more contact with the cooling air and thus better cooling.
  • the one or more pedestal having dimpled surface includes at least one pedestal extending from the pressure side inner surface towards the suction side inner surface.
  • the pedestal extending from the pressure side inner surface towards the suction side inner surface is non-contiguous with the suction side inner surface i.e. the pedestal does not extend the entire way between the pressure side inner surface and the suction side inner surface.
  • the pedestal aids in cooling of the pressure side inner surface and thereby in cooling of the pressure side wall.
  • the at least one pedestal extending from the pressure side inner surface towards the suction side inner surface and non-contiguous with the suction side inner surface includes a top surface with dimples, for example the top surface with dimples is spherical cap shaped.
  • the dimpled top surface ensures that cooling air contacts the top surface for a longer time and over a greater area of the pedestal top surface and thus facilitating the cooling of the top surface and thereby of the pedestal extending from the pressure side inner surface towards the suction side inner surface and non-contiguous with the suction side inner surface.
  • the one or more pedestal having dimpled surface includes at least one pedestal extending from the suction side inner surface towards the pressure side inner surface.
  • the pedestal extending from the suction side inner surface towards the pressure side inner surface is non-contiguous with the pressure side inner surface i.e. the pedestal does not extend the entire way between the suction side inner surface and the pressure side inner surface.
  • the pedestal aids in cooling of the suction side inner surface and thereby in cooling of the suction side wall.
  • the at least one pedestal extending from the suction side inner surface towards the pressure side inner surface and non-contiguous with the pressure side inner surface includes a top surface with dimples, for example the top surface with dimples is spherical cap shaped.
  • the dimpled top surface ensures that cooling air contacts the top surface for a longer time and over a greater area of the pedestal top surface and thus facilitating the cooling of the top surface and thereby of the pedestal extending from the suction side inner surface towards the pressure side inner surface and non-contiguous with the pressure side inner surface.
  • the one or more pedestal having dimpled surface is positioned in a trailing edge section of the aerofoil.
  • the cooling passage arranged within the aerofoil generally exits towards the trailing edge through holes or slits at the trailing edge and thus pedestals positioned in the trailing edge section of the aerofoil ensure that pressure drop in the cooling air flowing across the pedestals is reduced, due to the dimpled surface, hence the pressure in the cooling air exiting the trailing edge holes or slots is high. Reducing pressure drop is beneficial for working of the turbine engines in various ways for example if the pressure drop is smaller additional cooling features can be used so more effective cooling schemes can be implemented.
  • the one or more pedestal having dimpled surface have elliptical cross-sections, for example a circular cross-section. This provides an implementation for a shape of the pedestal with the dimpled surface.
  • a turbine blade for a gas turbine engine is presented.
  • the turbine blade includes an aerofoil according to the first aspect of the present technique as described hereinabove.
  • the turbine blade has the aerofoil with the pedestal having dimpled surface and thus cooling of the turbine blade is aided by the pedestal having dimpled surface.
  • a turbine vane for a gas turbine engine is presented.
  • the turbine vane includes an aerofoil according to the first aspect of the present technique as described hereinabove.
  • the turbine vane has the aerofoil with the pedestal having dimpled surface and thus cooling of the turbine vane is aided by the pedestal having dimpled surface.
  • FIG. 1 shows an example of a gas turbine engine 10 in a sectional view.
  • the gas turbine engine 10 comprises, in flow series, an inlet 12, a compressor or compressor section 14, a combustor section 16 and a turbine section 18 which are generally arranged in flow series and generally about and in the direction of a rotational axis 20.
  • the gas turbine engine 10 further comprises a shaft 22 which is rotatable about the rotational axis 20 and which extends longitudinally through the gas turbine engine 10.
  • the shaft 22 drivingly connects the turbine section 18 to the compressor section 14.
  • air 24 which is taken in through the air inlet 12 is compressed by the compressor section 14 and delivered to the combustion section or burner section 16.
  • the burner section 16 comprises a burner plenum 26, one or more combustion chambers 28 extending along a longitudinal axis 35 and at least one burner 30 fixed to each combustion chamber 28.
  • the combustion chambers 28 and the burners 30 are located inside the burner plenum 26.
  • the compressed air passing through the compressor 14 enters a diffuser 32 and is discharged from the diffuser 32 into the burner plenum 26 from where a portion of the air enters the burner 30 and is mixed with a gaseous or liquid fuel.
  • the air/fuel mixture is then burned and the combustion gas 34 or working gas from the combustion is channelled through the combustion chamber 28 to the turbine section 18 via a transition duct 17.
  • This exemplary gas turbine engine 10 has a cannular combustor section arrangement 16, which is constituted by an annular array of combustor cans 19 each having the burner 30 and the combustion chamber 28, the transition duct 17 has a generally circular inlet that interfaces with the combustor chamber 28 and an outlet in the form of an annular segment.
  • An annular array of transition duct outlets form an annulus for channelling the combustion gases to the turbine 18.
  • the turbine section 18 comprises a number of blade carrying discs 36 attached to the shaft 22.
  • two discs 36 each carry an annular array of turbine blades 38.
  • the number of blade carrying discs could be different, i.e. only one disc or more than two discs.
  • guiding vanes 40 which are fixed to a stator 42 of the gas turbine engine 10, are disposed between the stages of annular arrays of turbine blades 38. Between the exit of the combustion chamber 28 and the leading turbine blades 38 inlet guiding vanes 44 are provided and turn the flow of working gas onto the turbine blades 38.
  • the combustion gas 34 from the combustion chamber 28 enters the turbine section 18 and drives the turbine blades 38 which in turn rotate the shaft 22.
  • the guiding vanes 40, 44 serve to optimise the angle of the combustion or working gas 34 on the turbine blades 38.
  • the turbine section 18 drives the compressor section 14.
  • the compressor section 14 comprises an axial series of vane stages 46 and rotor blade stages 48.
  • the rotor blade stages 48 comprise a rotor disc supporting an annular array of blades.
  • the compressor section 14 also comprises a casing 50 that surrounds the rotor stages and supports the vane stages 48.
  • the guide vane stages include an annular array of radially extending vanes that are mounted to the casing 50. The vanes are provided to present gas flow at an optimal angle for the blades at a given engine operational point.
  • Some of the guide vane stages have variable vanes, where the angle of the vanes, about their own longitudinal axis, can be adjusted for angle according to air flow characteristics that can occur at different engine operations conditions.
  • the casing 50 defines a radially outer surface 52 of the passage 56 of the compressor 14.
  • a radially inner surface 54 of the passage 56 is at least partly defined by a rotor drum 53 of the rotor which is partly defined by the annular array of blades 48.
  • the present technique is described with reference to the above exemplary turbine engine having a single shaft or spool connecting a single, multi-stage compressor and a single, one or more stage turbine.
  • the present technique is equally applicable to two or three shaft engines and which can be used for industrial, aero or marine applications.
  • the cannular combustor section arrangement 16 is also used for exemplary purposes and it should be appreciated that the present technique is equally applicable to annular type and can type combustion chambers.
  • upstream and downstream refer to the flow direction of the airflow and/or working gas flow 34 through the engine unless otherwise stated.
  • forward and rearward refer to the general flow of gas through the engine.
  • axial, radial and circumferential are made with reference to the rotational axis 20 of the engine, unless otherwise stated.
  • FIG 2 schematically illustrates a turbomachine component 1 having an aerofoil 5 depicting a portion of an inside of the turbomachine component 1.
  • Examples of the turbomachine component 1 are the turbine blade 38 or the vane 40 of FIG 1 .
  • FIG 3 schematically illustrates a top perspective view of the aerofoil 5 of the turbomachine component 1, hereinafter also referred to as the blade 1.
  • FIG 4 represents detailed view of a region A of FIG 3 .
  • the aerofoil 5 extends from a platform 6 in a radial direction.
  • the platform 6 extends circumferentially.
  • a root 8 or a fixing part 8 may be used to attach the blade 1 to the turbine disc 36 (shown in FIG 1 ).
  • the root 8 and the platform 6 together form a base in the blade 1. It may be noted that in some other embodiments of the turbomachine component 1, the root 8 may not be present and the base is then formed only of the platform 6 which may be an integrally fabricated part of a larger structure (not shown) such as a stator disc in the turbine section 16 of the engine 10, as shown in FIG 1 .
  • the aerofoil 5 includes a suction side wall 60, also called suction side 60, and a pressure side wall 70, also called pressure side 70.
  • the side walls 60 and 70 meet at a trailing edge 92 on one end and a leading edge 91 on another end.
  • the aerofoil 5 has a tip end 93 and a platform end 94.
  • the aerofoil 5 may be connected to a shroud (not shown) or an outer platform (not shown) at the tip end 93 of the aerofoil 5.
  • the suction side wall 60 has a suction side outer surface 61 i.e.
  • the suction side wall 60 has a suction side inner surface 62, opposite face of the suction side wall 60 as compared to the suction side outer surface 61.
  • the suction side inner surface 62 is the surface of the suction side wall 60 that is at the inside of the aerofoil 5 and that is not positioned in the hot gas path when the aerofoil 5 is arranged in the gas turbine engine 10.
  • the pressure side wall 70 has a pressure side outer surface 71 i.e.
  • the pressure side wall 70 has a pressure side inner surface 72, opposite face of the pressure side wall 70 as compared to the pressure side outer surface 71.
  • the pressure side inner surface 72 is the surface of the pressure side wall 70 that is at the inside of the aerofoil 5 and that is not positioned in the hot gas path when the aerofoil 5 is arranged in the gas turbine engine 10.
  • the suction side inner surface 62 and the pressure side inner surface 72 are opposing surfaces.
  • the side walls 60 and 70 of the aerofoil 5 act as boundary for an aerofoil cavity or volume enclosed by the side walls 60 and 70.
  • a cooling passage 9 is arranged, more particularly between the suction side inner surface 62 and the pressure side inner surface 72.
  • the cooling passage 9 defines a flow path for a cooling fluid such as cooling air for purpose of cooling the aerofoil 5.
  • An exemplary embodiment of the cooling passage 9 and a direction of flow of cooling air represented by arrows marked with reference numeral 7 have been schematically depicted in FIG 2 . It may be noted that dimensions, arrangement, design etc of the cooling passage 9 and pattern of flow 7 of the cooling air or fluid within the cooling passage 9 may be different depending on different blade/vane designs.
  • cooling passage 9 may be formed of one or more parts, for example smaller cooling passages or channels that define different flow paths for the cooling fluid and that are not fluidly connected.
  • the cooling passage 9 or its constituting passages or channels may exit the aerofoil 5 through one or more exits that are usually arranged at the leading edge 91 and/or the trailing edge 92, for example trailing edge slits 95 in FIG 2 .
  • cooling fluid enters the cooling passage 9 through the base of the blade 1.
  • FIG 5 presents an exemplary embodiment of one such pedestal 80 according to the present technique and that has been removed from the aerofoil 5.
  • the pedestal 80 generally has an extended body, i.e. extending along an axis 85, and two ends 86, 87.
  • Both the ends 86 and 87 may be attached to the inner surfaces 62, 67 for example one end 86 may be attached to the suction side inner surface 62 whereas the other side 87 may be attached to the pressure side inner surface 72; or one of the two ends 86 and 87 may be attached to the inner surface 62 or 67 for example one end 86 may be attached to the suction side inner surface 62 whereas the other side 87 may be free standing i.e. not attached to the pressure side inner surface 72 or the other end 87 may be attached to the pressure side inner surface 72 whereas the one side 86 may be free standing i.e. not attached to the suction side inner surface 62. It may be noted that attached includes formed as integral part, for example by casting, wherein the pedestal 80 and the inner surfaces 62,72 are formed together as one part and then the phrase 'attached to' as used hereinabove means joint with or formed with.
  • the aerofoil 5 may include a plurality of the pedestals 80.
  • the plurality of pedestals 80 includes one or more pedestal 80 that have dimpled surface 84 as shown in FIG 5 .
  • the pedestal 80 having the dimpled surface 84 may have an elliptical cross-section, for example a circular cross section.
  • An example of a shape of the pedestal 80 may be a rod shape.
  • FIG 9 and 10 depict an advantage in cooling provided due to the pedestal 80 having dimpled surface 84 in comparison to a conventionally known pedestal 78 having a surface that is not dimpled surface 84 for example a pedestal 78 having a smooth surface. As shown in FIG 9 , when the flow 7 of cooling fluid for example cooling air encounters the pedestal 78, the cooling air is forced to flow over the smooth surface of the pedestal 78.
  • the cooling air starts to flow in contact with the surface of the pedestal 78 from point or region wherefrom the cooling air comes in contact with the surface of the pedestal 78, however as is known conventionally, due to curvature of the surface of the pedestal 78, the flow 7 of the cooling air separates from the surface of the pedestal 78 at a point 79, also referred generally to as separation point or flow separation point, after flowing for some duration in contact with the surface of the pedestal 78.
  • the cooling air is forced to flow over the dimpled surface 84 of the pedestal 80 from point or region wherefrom the cooling air comes in contact with the dimpled surface 84 of the pedestal 80, and although due to curvature of the dimpled surface 84 of the pedestal 80, the flow 7 of the cooling air eventually separates from the dimpled surface 84 of the pedestal 80, due to the dimpled surface 84 the separation point 79 on the dimpled surface 84 is further downstream, with respect to flow direction 7 of the cooling air wherefrom the cooling air comes in contact with the dimpled surface 84 of the pedestal 80.
  • This shift of the position of the separation point 79 on the dimpled surface 84 of the pedestal 80 results in greater contact time between the cooling air and the dimpled surface 84 and greater contact area of the dimpled surface 84 with the cooling air before the occurrence of the flow separation at the separation point 79.
  • FIG 6 presents various exemplary embodiments of the aerofoil 5 differing in the arrangement of the pedestals 80.
  • the one or more pedestal 80 having dimpled surface 84 includes at least one pedestal 81 that joins or is attached with or is formed with the pressure side inner surface 72 and the suction side inner surface 62 i.e. the pedestal 81 is physically in contact with the pressure side inner surface 72 as well as the suction side inner surface 62 and extends the entire way between the pressure side inner surface 72 as well as the suction side inner surface 62.
  • the one or more pedestal 80 having dimpled surface 84 includes at least one pedestal 82 extending from the suction side inner surface 62 towards the pressure side inner surface 72.
  • the pedestal 82 extends towards the pressure side inner surface 72 but is non-contiguous with the pressure side inner surface 72 i.e. the pedestal 82 does not extend the entire way between the suction side inner surface 62 and the pressure side inner surface 72.
  • the one or more pedestal 80 having dimpled surface 84 includes at least one pedestal 83 extending from the pressure side inner surface 72 towards the suction side inner surface 62.
  • the pedestal 83 extends towards the suction side inner surface 62 but is non-contiguous with the suction side inner surface 62 i.e. the pedestal 83 does not extend the entire way between the pressure side inner surface 72 and the suction side inner surface 62.
  • FIG 7 presents further exemplary embodiments of the aerofoil 5 and the pedestals 80 that are related to embodiments of the pedestals 82 and 83 of the plurality of pedestals 80.
  • the pedestal 82 includes a top surface 88 with dimples, for example the top surface 88 with dimples is spherical cap shaped as shown in FIG 7 .
  • the pedestal 83 includes a top surface 89 with dimples, for example the top surface 89 with dimples is spherical cap shaped as shown in FIG 7 .
  • FIG 8 schematically depicts another exemplary embodiment of the aerofoil 5 wherein the one or more pedestal 80 having dimpled surface 84, for example including the pedestals 81, 82 and 83, is positioned in a trailing edge section 99 of the aerofoil 5.
  • the trailing edge section 99 may be understood as an a region of the aerofoil 5 starting at the trailing edge 92 and extending up to a length 98 along a chord 96 of the aerofoil 5.
  • the length 98 is less than 50 percent of a chord length 97 of the chord 96 of the aerofoil 5, and more particularly, the length 98 is less than 25 percent of the chord length 97 of the chord 96 of the aerofoil 5, or the length 98 is less than 10 percent of the chord length 97 of the chord 96 of the aerofoil 5.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16182733.2A 2016-08-04 2016-08-04 Schaufel mit einem oder mehreren sockeln mit genoppter oberfläche zur kühlung Withdrawn EP3279432A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP16182733.2A EP3279432A1 (de) 2016-08-04 2016-08-04 Schaufel mit einem oder mehreren sockeln mit genoppter oberfläche zur kühlung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16182733.2A EP3279432A1 (de) 2016-08-04 2016-08-04 Schaufel mit einem oder mehreren sockeln mit genoppter oberfläche zur kühlung

Publications (1)

Publication Number Publication Date
EP3279432A1 true EP3279432A1 (de) 2018-02-07

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EP16182733.2A Withdrawn EP3279432A1 (de) 2016-08-04 2016-08-04 Schaufel mit einem oder mehreren sockeln mit genoppter oberfläche zur kühlung

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110033311A1 (en) * 2009-08-06 2011-02-10 Martin Nicholas F Turbine Airfoil Cooling System with Pin Fin Cooling Chambers
WO2012036965A1 (en) * 2010-09-17 2012-03-22 Siemens Energy, Inc. Turbine component with multi - scale turbulation features
US20150037165A1 (en) * 2013-07-31 2015-02-05 General Electric Company Turbine blade with sectioned pins

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110033311A1 (en) * 2009-08-06 2011-02-10 Martin Nicholas F Turbine Airfoil Cooling System with Pin Fin Cooling Chambers
WO2012036965A1 (en) * 2010-09-17 2012-03-22 Siemens Energy, Inc. Turbine component with multi - scale turbulation features
US20150037165A1 (en) * 2013-07-31 2015-02-05 General Electric Company Turbine blade with sectioned pins

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