WO2016122483A1 - Profil de turbine avec système de refroidissement par impact de bord de fuite - Google Patents

Profil de turbine avec système de refroidissement par impact de bord de fuite Download PDF

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Publication number
WO2016122483A1
WO2016122483A1 PCT/US2015/013254 US2015013254W WO2016122483A1 WO 2016122483 A1 WO2016122483 A1 WO 2016122483A1 US 2015013254 W US2015013254 W US 2015013254W WO 2016122483 A1 WO2016122483 A1 WO 2016122483A1
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WO
WIPO (PCT)
Prior art keywords
trailing edge
impingement
airfoil
pressure side
cavity
Prior art date
Application number
PCT/US2015/013254
Other languages
English (en)
Inventor
George Liang
Original Assignee
Siemens Aktiengesellschaft
Siemens Energy, Inc.
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens Aktiengesellschaft, Siemens Energy, Inc. filed Critical Siemens Aktiengesellschaft
Priority to PCT/US2015/013254 priority Critical patent/WO2016122483A1/fr
Publication of WO2016122483A1 publication Critical patent/WO2016122483A1/fr

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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
    • 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
    • F01D5/181—Blades having a closed internal cavity containing a cooling medium, e.g. sodium
    • 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
    • F01D5/185—Liquid 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • This invention is directed generally to turbine airfoils, and more particularly to cooling systems in hollow turbine airfoils.
  • gas turbine engines typically include a compressor for compressing air, a combustor for mixing the compressed air with fuel and igniting the mixture, and a turbine blade assembly for producing power.
  • Combustors often operate at high temperatures that may exceed 2,500 degrees Fahrenheit.
  • Typical turbine combustor configurations expose turbine blade assemblies to these high temperatures.
  • turbine blades must be made of materials capable of withstanding such high temperatures.
  • turbine blades often contain cooling systems for prolonging the life of the blades and reducing the likelihood of failure as a result of excessive temperatures.
  • the trailing edge region of turbine blades are relatively thin and experience relatively high temperatures relative to other portions of the airfoil. As such, properly cooling the trailing edge region of turbine blades has proven challenging.
  • Conventional cooling systems as shown in Figures 1 -4, have employed use of impingement cooling holes 1 within spanwise extending ribs 2 in a trailing edge region of airfoils.
  • the impingement cooling holes 1 have been positioned at the parting line 3 and face downstream, where cooling fluids are exhausted downstream towards a downstream rib 4.
  • the impingement cooling fluids exhausted from the impingement cooling holes 1 strike the downstream rib 4 near the parting line 3 and form a pair of vortices 5 that partially contact the outer walls 6 forming the pressure and suction sides.
  • a turbine airfoil with a trailing edge impingement cooling system configured to provide a balanced thermal profile.
  • the trailing edge impingement cooling system may include a single trailing edge impingement cooling flow scheme positioned between a trailing edge of an airfoil and a double trailing edge
  • the double trailing edge impingement cooling flow scheme may include first and second somewhat serpentine shaped flow paths passing cooling fluids in an alternating manner between outwardly positioned trailing edge pressure side impingement cavities and more centrally positioned trailing edge collection chambers positioned radially inward of pressure and suction sides via one or more impingement orifices.
  • the single trailing edge impingement cooling flow scheme is configured similarly with a single flow path.
  • the double trailing edge impingement cooling flow scheme reduces the impingement cooling air mass flux in half, thereby yielding less internal convective cooling effectiveness and lower heat up of the cooling fluids, which provides higher cooling potential for cooling fluids flowing into the single trailing edge impingement cooling flow scheme.
  • the dual cooling fluid flows in the double trailing edge impingement cooling flow scheme are combined in the single trailing edge impingement cooling flow scheme yielding twice the impingement mass flux and a higher concentrated impingement jet with a much higher heat transfer coefficient at the high heat load region at the trailing edge.
  • the trailing edge impingement cooling system balances cooling, a relatively large amount of internal convection cooling surface and a capability of tailoring the cooling system configuration to accommodate different external heat loads and sectional mass average metal temperature levels.
  • the turbine airfoil may be formed from a generally elongated, hollow airfoil having a leading edge, a trailing edge, a pressure side, a suction side on an opposite side of the airfoil from the pressure side, a tip section at a first end, a root coupled to the airfoil at an end generally opposite the first end for supporting the airfoil and for coupling the airfoil to a disc, a platform at an
  • the cooling system may be formed form one or more double trailing edge
  • the double trailing edge impingement cooling flow scheme may be formed from one or more trailing edge cooling fluid feed supply channels and one or more first trailing edge pressure side impingement cavities with at least a portion at an outer wall forming the pressure side.
  • the double trailing edge impingement cooling flow scheme may include one or more first pressure side impingement orifices extending between the first trailing edge cooling fluid feed supply channel and the trailing edge pressure side impingement cavity.
  • the double trailing edge impingement cooling flow scheme may include one or more first trailing edge suction side impingement cavities with at least a portion at an outer wall forming the suction side and one or more first suction side impingement orifices extending between the trailing edge cooling fluid feed supply channel and the first trailing edge suction side impingement cavity.
  • the double trailing edge impingement cooling flow scheme may also include one or more first trailing edge collection chambers in fluid communication with the first trailing edge pressure side
  • the first trailing edge collection chamber may be positioned inward of the pressure and suction sides further than the first trailing edge pressure side impingement cavity and the first trailing edge suction side
  • the double trailing edge impingement cooling flow scheme may include one or more second trailing edge pressure side impingement cavities with at least a portion at an outer wall forming the pressure side.
  • the second trailing edge pressure side impingement cavity may include one or more second pressure side impingement orifices extending between the first trailing edge collection chamber and the second trailing edge pressure side impingement cavity.
  • the second trailing edge pressure side impingement cavity may include one or more second trailing edge suction side impingement cavities with at least a portion at an outer wall forming the suction side and one or more second suction side impingement orifices extending between the first trailing edge collection chamber and the second trailing edge suction side impingement cavity.
  • the first suction side impingement orifice may be generally aligned with the second pressure side impingement orifice, and the first pressure side impingement orifice may be generally aligned with the second suction side impingement orifice.
  • the trailing edge impingement cooling system may also include a single trailing edge impingement cooling flow scheme positioned between the double trailing edge impingement cooling flow scheme and the trailing edge.
  • the single trailing edge impingement cooling flow scheme may include one or more first pressure side single impingement cavities with at least a portion at an outer wall forming the pressure side and one or more first suction side single impingement cavities with at least a portion at an outer wall forming the suction side.
  • the impingement cavity may be offset from each other in a chordwise direction and may be in fluid communication with each other via a first single trailing edge impingement cooling flow scheme impingement orifice.
  • the single trailing edge impingement cooling flow scheme may be a repetitive, alternating pattern of the first pressure side single impingement cavity and the first suction side single impingement cavity in fluid communication with each other via the first single trailing edge impingement cooling flow scheme impingement orifice.
  • the first pressure side single impingement cavity of the single trailing edge impingement cooling flow scheme may have a cross- section with a side generally aligned with the pressure side of the airfoil and a side generally aligned with a side of a trailing edge suction side impingement cavity.
  • the first suction side single impingement cavity of the single trailing edge impingement cooling flow scheme may have a triangular cross-section with a side generally aligned with the suction side of the airfoil and a side aligned with a side of the first pressure side single impingement cavity.
  • the trailing edge impingement cooling system may also include one or more cooling fluid exhaust slots with one or more exhaust openings proximate to the trailing edge.
  • the cooling fluid exhaust slots may extend from the single trailing edge impingement cooling flow scheme and may be configured to exhaust spent cooling fluids from the trailing edge impingement cooling system through the trailing edge.
  • the cooling fluid exhaust slot extends between a single trailing edge impingement cooling flow scheme and an outer surface of the airfoil proximate to the trailing edge.
  • the first trailing edge pressure side impingement cavity may have a generally triangular cross-section with a side generally aligned with the pressure side of the airfoil.
  • the first trailing edge suction side impingement cavity may have a generally triangular cross-section with a side generally aligned with the suction side of the airfoil.
  • the first trailing edge collection chamber may have a generally diamond shaped cross-section with a side generally aligned with a side of the first trailing edge pressure side impingement cavity and a side generally aligned with a side of the first trailing edge suction side impingement cavity.
  • At least one second trailing edge pressure side impingement cavity may have a generally triangular cross-section with a side generally aligned with the pressure side of the airfoil. At least one second trailing edge suction side impingement cavity may have a generally triangular cross-section with a side generally aligned with the suction side of the airfoil.
  • the first trailing edge collection chamber may have a side generally aligned with a side of the second trailing edge pressure side impingement cavity and a side generally aligned with a side of the second trailing edge suction side impingement cavity.
  • the first trailing edge pressure side impingement cavity may include one or more micro pin fins extending from a radially outer surface of the first trailing edge pressure side impingement cavity.
  • the first trailing edge suction side impingement cavity may include one or more micro pin fins extending from a radially outer surface of the first trailing edge suction side impingement cavity.
  • cooling fluid such as, but not limited to, air
  • the double trailing edge impingement cooling flow scheme may form multiple rows of impingement baffles with crisscross forming form impingement of cooling fluid onto the trailing edge of the airfoil in between the outer walls forming the pressure and suction sides.
  • the cooling fluid may flow from the trailing edge cooling fluid feed supply channel into the double trailing edge impingement cooling flow scheme through the first pressure side impingement orifices and the first suction side impingement orifices.
  • the double trailing edge impingement cooling flow scheme reduces the impingement cooling air mass flux by about 50 percent, thereby yielding less internal convective cooling effectiveness in the double trailing edge impingement cooling flow scheme at the upstream portion of the trailing edge impingement cooling system. Subsequently, the cooling fluid undergoes lower heat up within the upstream portion of the trailing edge impingement cooling system. The cooling fluid with lower heat up will provide high cooling potential for the cooling fluid to cool the airfoil within a downstream portion of the trailing edge impingement cooling system at the trailing edge.
  • the single trailing edge impingement cooling flow scheme positioned between the double trailing edge impingement cooling flow scheme and the trailing edge and within the downstream portion of the trailing edge impingement cooling system, the internal flow channels are narrower while the heat load is higher than the upstream section.
  • the single trailing edge impingement cooling flow scheme combines both flow paths into a single flow path of cooling fluids which yields twice the impingement mass flux when the cooling fluids impinge onto the inner surfaces of the outer walls forming the pressure and suction sides.
  • a higher concentrated impingement jet may be achieved, thus creating a much higher impingement heat transfer coefficient at the high heat load region of the airfoil, which is the downstream portion of the trailing edge impingement cooling system.
  • the spent cooling fluid may be discharged through the exhaust openings of the cooling fluid exhaust slots to cooling the portions of the airfoil at the trailing edge.
  • An advantage of this invention is that the cooling capacity of the trailing edge impingement cooling system is reduced within the double trailing edge impingement cooling flow scheme that is positioned in an upstream region that has reduced cooling requirements compared with the downstream region of the airfoil positioned between the upstream region and the trailing edge of the airfoil.
  • the downstream region includes a single trailing edge impingement cooling flow scheme with an increased cooling capacity to accommodate the increased cooling requirements.
  • Figure 1 is a perspective view of a conventional turbine airfoil.
  • Figure 2 is a filleted cross-sectional view of the conventional turbine airfoil shown in Figure 1 taken along line 2-2.
  • Figure 3 is a cross-sectional view of the conventional turbine airfoil shown in Figure 2 taken along line 3-3.
  • Figure 4 is a detail, cross-sectional view of the conventional turbine airfoil shown in Figure 3 taken at detail line 4-4 in Figure 3.
  • Figure 5 is a perspective view of a turbine airfoil with the trailing edge impingement cooling system.
  • Figure 6 is a filleted cross-sectional view of the turbine airfoil shown in Figure 5 taken along line 6-6.
  • Figure 7 is a detail, cross-sectional view of the conventional turbine airfoil shown in Figure 5 taken at detail line 7-7 in Figure 5.
  • the trailing edge impingement cooling system 12 may include a single trailing edge impingement cooling flow scheme 14 positioned between a trailing edge 16 of an airfoil 10 and a double trailing edge impingement cooling flow scheme 20.
  • the double trailing edge impingement cooling flow scheme 20 may include first and second somewhat serpentine shaped flow paths 22, 24 passing cooling fluids in an alternating manner between outwardly positioned trailing edge pressure side impingement cavities 26 and more centrally positioned trailing edge collection chambers 28 positioned radially inward of pressure and suction sides 30, 32 via one or more impingement orifices 34.
  • the single trailing edge impingement cooling flow scheme 14 may be configured similarly with a single flow path.
  • the double trailing edge impingement cooling flow scheme 20 may reduce the impingement cooling air mass flux in half, thereby yielding less internal convective cooling effectiveness and lower heat up of the cooling fluids, which provides higher cooling potential for cooling fluids flowing into the single trailing edge impingement cooling flow scheme 14.
  • the dual cooling fluid flows in the double trailing edge impingement cooling flow scheme 20 are combined in the single trailing edge impingement cooling flow scheme 14 yielding twice the impingement mass flux and a higher concentrated impingement jet with a much higher heat transfer coefficient at the high heat load region at the trailing edge 16.
  • the trailing edge impingement cooling system 12 balances cooling, a relatively large amount of internal convection cooling surface and a capability of tailoring the cooling system configuration to accommodate different external heat loads and sectional mass average metal temperature levels.
  • the turbine airfoil 10 may be formed from a generally elongated, hollow airfoil 40 having a leading edge 42, a trailing edge 16, a pressure side 30, a suction side 32 on an opposite side of the airfoil 40 from the pressure side 30, a tip section 44 at a first end 46, a root 48 coupled to the airfoil 40 at a second end 48 generally opposite the first end 46 for supporting the airfoil 40 and for coupling the airfoil 40 to a disc, a platform 50 at an intersection 52 between the root 48 and the generally elongated, hollow airfoil 40 and extending nonparallel to a longitudinal axis 54 of the generally elongated, hollow airfoil 40, and a cooling system 12 formed from at least one cavity 56 in the elongated, hollow airfoil 40.
  • the cooling system 12 may include one or more double trailing edge impingement cooling flow schemes 20.
  • the double trailing edge impingement cooling flow scheme 20 may include one or more trailing edge cooling fluid feed supply channels 58 extending generally spanwise within the airfoil 40.
  • the trailing edge cooling fluid feed supply channels 58 may be the last leg of a serpentine cooling channel.
  • the trailing edge cooling fluid feed supply channels 58 may be the last leg of a three, four or five pass serpentine cooling channel, or other number of channels serpentine cooling channel.
  • the trailing edge cooling fluid feed supply channel 58 may be formed from one or more first trailing edge pressure side impingement cavities 60 with at least a portion at an outer wall 62 forming the pressure side 30.
  • One or more first pressure side impingement orifices 64 may extend between the trailing edge cooling fluid feed supply channel 58 and the trailing edge pressure side impingement cavity 60.
  • the double trailing edge impingement cooling flow scheme 20 may include one or more first trailing edge suction side impingement cavities 68 with at least a portion at an outer wall 70 forming the suction side 32.
  • One or more first suction side impingement orifices 72 may extend between the trailing edge cooling fluid feed supply channel 58 and the first trailing edge suction side impingement cavity 68.
  • the first pressure side impingement orifices 64 and the first suction side impingement orifices 72 may have any appropriate configuration.
  • impingement orifices 72 may have tapered inlets 80 or outlets 82.
  • the inlets 80 and outlets 82 may be tapered linearly or nonlinearly.
  • One or more first trailing edge collection chambers 74 may be in fluid communication with the first trailing edge pressure side impingement cavity 60 via one or more second pressure side impingement orifices 76 and with the first trailing edge suction side impingement cavity 68 via one or more second suction side impingement orifices 78.
  • the first trailing edge pressure side impingement cavity 60 may have a generally triangular cross-section with a side 84 generally aligned with the pressure side 30 of the airfoil 10.
  • impingement cavity 68 may have a generally triangular cross-section with a side 86 generally aligned with the suction side 32 of the airfoil 10.
  • the first trailing edge collection chamber 74 may have a generally diamond shaped cross-section with a side 88 generally aligned with a side 90 of the first trailing edge pressure side impingement cavity 60 and a side 92 generally aligned with a side 94 of the first trailing edge suction side impingement cavity 68.
  • the first trailing edge collection chamber 74 may be positioned inward of the pressure and suction sides 30, 32 further than the first trailing edge pressure side impingement cavity 60 and the first trailing edge suction side impingement cavity 68.
  • the double trailing edge impingement cooling flow scheme 20 may include one or more second trailing edge pressure side impingement cavities 96 with at least a portion at an outer wall 62 forming the pressure side 30.
  • One or more second pressure side impingement orifices 98 may extend between the first trailing edge collection chamber 74 and the second trailing edge pressure side impingement cavity 96.
  • the double trailing edge impingement cooling flow scheme 20 may include one or more second trailing edge suction side impingement cavities 100 with at least a portion at the outer wall 70 forming the suction side 32.
  • One or more second suction side impingement orifices 102 may extend between the first trailing edge collection chamber 74 and the second trailing edge suction side impingement cavity 100.
  • the second pressure side impingement orifices 98 and the second suction side impingement orifices 102 may have any appropriate configuration.
  • the second pressure side impingement orifices 98 and the second suction side impingement orifices 102 may have tapered inlets 80 or outlets 82.
  • the inlets 80 and outlets 82 may be tapered linearly or nonlinearly.
  • the second trailing edge pressure side impingement cavity 96 may have a generally triangular cross-section with a side 140 generally aligned with the pressure side 30 of the airfoil 40.
  • the second trailing edge suction side impingement cavity 100 may have a generally triangular cross-section with a side 142 generally aligned with the suction side 32 of the airfoil 40.
  • the first trailing edge collection chamber 74 may have a side 144 generally aligned with a side 146 of the second trailing edge pressure side impingement cavity 96 and a side 148 generally aligned with a side 150 of the second trailing edge suction side impingement cavity 100.
  • the first suction side impingement orifice 72 may be generally aligned with the second pressure side impingement orifice 98, and the first pressure side impingement orifice 64 may be generally aligned with the second suction side impingement orifice 102.
  • Such a configuration may form a generally crisscross configuration in which cooling fluids flow from suction side 32 to the pressure side 30 and vice versa.
  • the configuration of the double trailing edge impingement cooling flow scheme 20 set forth may be repeated one or more times to achieve a desired cooling design and effectiveness.
  • the trailing edge impingement cooling system 12 may include a single trailing edge impingement cooling flow scheme 14 positioned between the double trailing edge impingement cooling flow scheme 20 and the trailing edge 16.
  • the single trailing edge impingement cooling flow scheme 14 may include one or more first pressure side single impingement cavities 106 with at least a portion at an outer wall 70 forming the pressure side 30.
  • the single trailing edge impingement cooling flow scheme 14 may include one or more first suction side single impingement cavities 108 with at least a portion at an outer wall 70 forming the suction side 32.
  • the first pressure side single impingement cavity 106 and the first suction side single impingement cavities 108 may be offset from each other in a chordwise direction 1 10 and may be in fluid communication with each other via a first single trailing edge impingement cooling flow scheme impingement orifice 1 12.
  • the single trailing edge impingement cooling flow scheme 14 may include a repetitive, alternating pattern of the first pressure side single impingement cavity 106 and the first suction side single impingement cavity 108 in fluid
  • the first pressure side single impingement cavity 106 of the single trailing edge impingement cooling flow scheme 14 may have a cross-section with a side 1 14 generally aligned with the pressure side 30 of the airfoil 40 and a side 1 16 generally aligned with a side 1 18 of a trailing edge suction side impingement cavity 120.
  • the first suction side single impingement cavity 108 of the single trailing edge impingement cooling flow scheme 14 may have a triangular cross-section with a side 122 generally aligned with the suction side 32 of the airfoil 40 and a side 124 aligned with a side 126 of the first pressure side single
  • the trailing edge impingement cooling system 12 may include one or more cooling fluid exhaust slots 128 having one or more exhaust openings 130 proximate to the trailing edge 16.
  • the cooling fluid exhaust slot 128 may extend between a single trailing edge impingement cooling flow scheme 14 and an outer surface 132 of the airfoil 40 proximate to the trailing edge 16.
  • the first trailing edge suction side impingement cavity 68 may include one or more micro pin fins 152 extending from a radially outer surface 156 of the first trailing edge suction side impingement cavity 68.
  • one or more, or all, of the cavities 60, 68, 96, 100, 106, 108 within the double trailing edge impingement cooling flow scheme 20 or the single trailing edge impingement cooling flow scheme 14, or both, may include one or more micro pin fins 152 extending radially inward from a surface at the outer walls 62, 70 forming the pressure or suction sides 30, 32 of the airfoil 40.
  • the micro pin fins 152 may have any appropriate shape and configuration. In at least one embodiment, the micro pin fins 152 may have a generally cylindrical shape. In other embodiments, the micro pin fins 152 may have other configurations.
  • the trailing edge impingement cooling system 12 may be formed from a crisscross cooling geometry by the use of print part manufacturing technologies.
  • the cavities 60, 68, 96, 100, 106, 1 08 within the double trailing edge impingement cooling flow scheme 20 and the single trailing edge impingement cooling flow scheme 14 may be formed by a trust core 160 that extends spanwise and includes outer surfaces at angles of between 30 degrees and 50 degrees relattive to the pressure side 30 and suction side 32 outer walls 62, 70.
  • the slanted impingement cooling holes 64, 72, 76, 78, 98 and 102 can be printed onto the trust core 160.
  • cooling fluid such as, but not limited to, air
  • the double trailing edge impingement cooling flow scheme 20 may form multiple rows of impingement baffles with crisscross forming form impingement of cooling fluid onto the trailing edge 16 of the airfoil 40 in between the outer walls 62, 70 forming the pressure and suction sides 30, 32.
  • the cooling fluid may flow from the trailing edge cooling fluid feed supply channel 58 into the double trailing edge impingement cooling flow scheme 20 through the first pressure side impingement orifices 64 and the first suction side impingement orifices 72.
  • the cooling fluids impinge onto the micro pin fins 152 extending radially inward from the inner surfaces of the outer walls 62, 70 forming the pressure and suction sides 30, 32.
  • impingement cooling flow scheme 20 reduces the impingement cooling air mass flux by 50 percent, thereby yielding less internal convective cooling effectiveness in the double trailing edge impingement cooling flow scheme 20 at the upstream portion 158 of the trailing edge impingement cooling system 12. Subsequently, the cooling fluid undergoes lower heat up within the upstream portion 158 of the trailing edge impingement cooling system 12. The cooling fluid with lower heat up will provide high cooling potential for the cooling fluid to cool the airfoil 40 within a downstream portion 160 of the trailing edge impingement cooling system 12 at the trailing edge 16.
  • the internal flow channels are narrower while the heat load is higher than the upstream section 158.
  • the single trailing edge impingement cooling flow scheme 14 combines both flow paths 22, 24 into a single flow path of cooling fluids which yields twice the impingement mass flux when the cooling fluids impinge onto the inner surfaces of the outer walls 62, 70 forming the pressure and suction sides 30, 32.
  • a higher concentrated impingement jet may be achieved, thus creating a much higher impingement heat transfer coefficient at the high heat load region of the airfoil 40, which is the downstream portion 160 of the trailing edge impingement cooling system 12.
  • the spent cooling fluid may be discharged through the exhaust openings 130 of the cooling fluid exhaust slots 128 to cooling the portions of the airfoil 40 at the trailing edge 16.

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

Abstract

La présente invention concerne un profil de turbine (10) avec un système de refroidissement par impact de bord de fuite (12) configuré pour produire un profil thermique équilibré. Le système de refroidissement par impact de bord de fuite (12) peut comprendre un schéma d'écoulement de refroidissement par impact de bord arrière simple (14) positionné entre un bord de fuite (44) d'un profil (10) et un schéma d'écoulement de refroidissement par impact de bord arrière double (20). Le schéma d'écoulement de refroidissement par impact de bord arrière double (20) peut comprendre des premier et deuxième trajets d'écoulement approximativement en forme de serpentin (22, 24) faisant passer des fluides de refroidissement entre des cavités d'impact côté pression de bord de fuite positionnées vers l'extérieur (26) et des chambres de collecte de bord de fuite positionnées de façon centrale (28) positionnées radialement vers l'intérieur des côtés de pression et d'aspiration (30, 32). Le schéma d'écoulement de refroidissement par impact de bord arrière simple (14) est configuré de façon similaire avec un trajet d'écoulement unique. Le schéma d'écoulement de refroidissement par impact de bord arrière double (20) produit un chauffage plus faible des fluides de refroidissement, ce qui produit un potentiel de refroidissement plus élevé pour des fluides de refroidissement s'écoulant dans le schéma d'écoulement de refroidissement par impact de bord arrière simple (14).
PCT/US2015/013254 2015-01-28 2015-01-28 Profil de turbine avec système de refroidissement par impact de bord de fuite WO2016122483A1 (fr)

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Cited By (3)

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Publication number Priority date Publication date Assignee Title
CN106761950A (zh) * 2017-01-13 2017-05-31 大连理工大学 一种热板均温无掺混涡轮叶片冷却装置及方法
US11111857B2 (en) 2019-07-18 2021-09-07 Raytheon Technologies Corporation Hourglass airfoil cooling configuration
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CN106761950A (zh) * 2017-01-13 2017-05-31 大连理工大学 一种热板均温无掺混涡轮叶片冷却装置及方法
US11111857B2 (en) 2019-07-18 2021-09-07 Raytheon Technologies Corporation Hourglass airfoil cooling configuration
US11624322B2 (en) 2019-07-18 2023-04-11 Raytheon Technologies Corporation Hourglass airfoil cooling configuration
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US20240175373A1 (en) * 2022-11-29 2024-05-30 Raytheon Technologies Corporation Gas turbine engine component having an airfoil with internal cross-ribs

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