EP3412866A1 - Gekühlte gasturbinenschaufel - Google Patents

Gekühlte gasturbinenschaufel Download PDF

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Publication number
EP3412866A1
EP3412866A1 EP17174863.5A EP17174863A EP3412866A1 EP 3412866 A1 EP3412866 A1 EP 3412866A1 EP 17174863 A EP17174863 A EP 17174863A EP 3412866 A1 EP3412866 A1 EP 3412866A1
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EP
European Patent Office
Prior art keywords
cooling
inlet
discharge
wall
blade according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP17174863.5A
Other languages
English (en)
French (fr)
Other versions
EP3412866B1 (de
Inventor
Shailendra Naik
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.)
Ansaldo Energia Switzerland AG
Original Assignee
Ansaldo Energia Switzerland 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 Ansaldo Energia Switzerland AG filed Critical Ansaldo Energia Switzerland AG
Priority to EP17174863.5A priority Critical patent/EP3412866B1/de
Priority to CN201810580261.3A priority patent/CN108999645B/zh
Publication of EP3412866A1 publication Critical patent/EP3412866A1/de
Application granted granted Critical
Publication of EP3412866B1 publication Critical patent/EP3412866B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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
    • 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
    • F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits

Definitions

  • the present invention relates to a blade for a gas turbine and to an electric power production plant comprising said blade.
  • the present invention relates to an improved cooling of the blades of a gas turbine.
  • the electric power production plant is connected to an electrical grid.
  • the blades of gas turbines are constantly exposed to a hot gas flow coming from the combustion chamber.
  • the temperature of the hot gas flowing in the gas turbine affects the performance of the plant.
  • performances of the plant increase with an increasing temperature of the hot gas flowing inside the turbine.
  • the object of the present invention is therefore to provide a blade having an optimized cooling system, capable of improving the thermal resistance of the blades, allowing a further increase of the temperature of the gases flowing in the gas turbine and reducing the thermodynamic losses thus consequently improving the plant performances.
  • a blade for a gas turbine comprising:
  • the flow rate of the cooling fluid exiting through the discharge arrangement is properly regulated. While thanks to the fact that the plurality of cooling fluid flows join at the outlet common slot the film cooling efficiency is improved.
  • the external face of the outer wall in fact, is lapped by a cooling flow which is wide and homogeneous.
  • the discharge arrangement comprises a plurality of connecting channels, each of which is configured to connect a respective hole with the outlet common slot.
  • the inlet holes are substantially identical to each other.
  • the connecting channels are substantially identical to each other.
  • each connecting channel have an inlet section and an outlet section; the inlet section of each connecting channel being in contact with the respective inlet hole and the outlet section of each connecting channel being in contact with the outlet common slot.
  • each inlet hole is smaller than the passage area of the inlet section of the respective connecting channels.
  • the connecting channels are diverging toward the outlet common slot.
  • the passage area of the inlet holes is constant.
  • the inlet holes are substantially aligned along a direction which is substantially a straight line extending from a base of the airfoil to a tip of the airfoil.
  • the inlet holes are arranged equally spaced from each other.
  • the discharge arrangement comprises at least two discharge groups; each discharge group comprises the plurality of inlet holes, the outlet common slot and the plurality of connecting channels.
  • the inlet holes of each discharge group are equally spaced one from the other.
  • the discharge groups are equally spaced one from the other.
  • the present invention relates to a plant for electric power production comprising at least one gas turbine, which extends along a longitudinal axis and comprises at least one row of blades circumferentially spaced and extending radially outwardly from a respective supporting disc of the gas turbine; at least one of the blades of the row being of the type claimed in anyone of the claims 1-12.
  • the plant comprises at least one compressor which is connected to the gas turbine by a suction line configured to draw cooling air from the compressor and supply it to the cooling arrangement of the at least one blade.
  • reference numeral 1 indicates a gas turbine plant for electrical energy production comprising a compressor 3, a combustor 4, a gas turbine 5 and a generator 7, which transforms the mechanical power supplied by turbine 5 into electrical power to be supplied to an electrical grid 8, connected to the generator 7 via a switch 9.
  • plant 1 to be of the combined cycle type and including, in addition to the gas turbine 5 and generator 7, also a steam turbine.
  • the gas turbine 5 extends along a longitudinal axis A and is provided with a shaft 10 (also extending along axis A) to which compressor 3 and generator 7 are also connected.
  • Gas turbine 5 comprises an expansion channel 12 wherein the hot gas working fluid coming from the combustor 4 flows in a direction D.
  • the expansion channel 12 has a section which radially increases along the axis A in the direction D.
  • each stage 13 comprises a row of fixed blades and a row of rotating blades (not illustrated in figure 1 ). Each row comprises circumferentially spaced blades extending radially outwardly from a respective supporting disc.
  • blade 15 is a rotating blade, but it is clear that the present invention can also be applied to stator blades.
  • the blade 15 comprises a root 17, an airfoil 18 and a platform 20.
  • the root 17 is configured to be coupled to a supporting disc (not illustrated in the accompanying figures) of the gas turbine 5.
  • the disc has a plurality of axial seats, which are circumferentially spaced and engaged by respective roots 17 of the rotating blades 15.
  • the airfoil 18 extends from the root 17 and is provided with base 21 coupled to the root 17 and a tip 22 which, in use, is radially opposite to the base 21.
  • the airfoil 18 is completely housed in the expansion channel 12 and defines the aerodynamic profile of the rotating blade 15.
  • the airfoil 18 has a concave pressure side 24 (better visible in figures 3 and 4 ) and a convex suction side 25, which, in use, extend axially between a leading edge 27 and a trailing edge 28 and radially between the base 21 and the tip 22.
  • the leading edge 27 is arranged upstream of the trailing edge 28 along the direction D of the hot working fluid in the expansion channel 12.
  • the platform 20 is arranged between the root 17 and the airfoil 18.
  • Blade 15 is provided with a cooling arrangement 29.
  • the cooling arrangement 29 comprise a plurality of feeding channels 30 made in the root 17 and a plurality of cooling paths 31 (not illustrated in figure 2 and better visible in figures 3 and 4 ) made in the airfoil 18.
  • the feeding channels 30 are supplied with a cooling fluid coming from a cooling fluid source 32.
  • the cooling fluid source 32 is a portion of the compressor 3.
  • a suction line 33 dedicated to the suction of cooling air from the compressor 3 and connected to the gas turbine 5 is shown.
  • each feeding channel 30 is coupled to a respective cooling path 31.
  • each feeding channels can be coupled to more than one cooling path.
  • the feeding channels 30 are four and the cooling paths 31 are four.
  • the cooling arrangement 29 comprises a suction side cooling path 31a mainly dedicated to the cooling of the suction side 25, a pressure side cooling path 31b mainly dedicated to the cooling of the pressure side 24, a leading edge cooling path 31c mainly dedicated to the cooling of the leading edge 27 and a trailing edge cooling path 31d mainly dedicated to the cooling of the trailing edge 28.
  • a dashed line is used to schematically indicate the cooling path 31a
  • a dashed-dotted line is used to schematically indicate the pressure side cooling path 31b
  • a dotted line is used to schematically indicate the leading edge cooling path 31c
  • a solid line is used to schematically indicate the trailing edge cooling path 31d.
  • the airfoil 18 comprises an outer wall 35 and an inner wall 36.
  • the outer wall 35 defines at least in part the aerodynamic profile of the blade 15 and has an external face 37 which, in use, is arranged in contact with the hot gas working fluid flowing in the expansion channel 12.
  • the inner wall 36 is enclosed by the outer wall 35 and may have cooling and structural functions.
  • the inner wall 36 defines an inner central cooling chamber 38, through which, in use, the cooling fluid coming from a respective feeding channel 30 flows as will be detailed in the following.
  • the suction side cooling path 31a is defined between the inner wall 36 and the outer wall 35 and extends at least partially along the suction side 25.
  • the suction side cooling path 31a comprises at least one inlet 40 (better visible in figure 2 ) and at least one discharge arrangement 41.
  • the inlet 40 being arranged closer to the trailing edge 28 than the discharge arrangement 41.
  • the suction side cooling path 31a comprises one inlet 40, which is defined by an aperture located at the base 21 of the airfoil 18 and in fluidic communication with the respective feeding channel 30 of the root 17.
  • the suction side cooling path 31a comprises one discharge arrangement 41 which will be described in detail later.
  • the suction side cooling path 31a comprises a plurality of suction side cooling chambers 42 which are in fluidic communication and arranged side by side between the inner wall 36 and the outer wall 35 along the suction side 25.
  • Each of the suction side cooling chambers 42 extends substantially along a direction going from the base 21 toward the tip 22.
  • the plurality of suction side cooling chambers 42 comprises a suction side inlet chamber 42a, which is the suction side cooling chamber 42 closest to the trailing edge 28, and a suction side discharge chamber 42b, which is the suction side cooling chamber 42 closest to the leading edge 27.
  • the suction side inlet chamber 42a comprises the inlet 40 and the suction side discharge chamber 42b comprises the discharge arrangement 41.
  • the suction side cooling path 31a comprises three suction side cooling chambers 42. In other words, between the suction side inlet chamber 42a and the suction side discharge chamber 42b only one suction side intermediate chamber 42c is arranged.
  • the cooling fluid coming from the respective feeding channel 30 of the root 17 flows along the suction side inlet chamber 41a, along the suction side intermediate chamber 42c along the suction side discharge chamber 42b and exits through the discharge arrangement 41 of the suction side discharge chamber 42b.
  • the flow of the cooling fluid along the suction side cooling path 31a is a counter-current flow with respect to the flow of the hot gas working fluid in the expansion channel 12 having direction D.
  • the pressure side cooling path 31b is defined between the inner wall 36 and the outer wall 35 and extends at least partially along the pressure side 24.
  • the pressure side cooling path 31b comprises at least one inlet 44 (better visible in figure 2 ) and at least one discharge arrangement 45.
  • the discharge arrangement 45 being arranged closer to the trailing edge 28 than the inlet 44.
  • the pressure side cooling path 31b comprises one inlet 44, which is defined by an aperture located at the base 21 of the airfoil 18 and in fluidic communication with the respective feeding channel 30 of the root 17.
  • the pressure side cooling path 31b comprises two discharge arrangements 45, which will be described in detail later.
  • the pressure side cooling path 31b comprises a plurality of pressure side cooling chambers 47 which are in fluidic communication and arranged side by side between the inner wall 36 and the outer wall 35 along the pressure side 24.
  • Each of the pressure side cooling chambers 47 extends substantially along a direction going from the base 21 toward the tip 22.
  • the plurality of pressure side cooling chambers 47 comprises a pressure side inlet chamber 47a, which is the pressure side cooling chamber 47 closest to the leading edge 27, and at least one pressure side discharge chamber 47b, which is the pressure side cooling chamber 47 closest to the trailing edge 28.
  • the pressure side inlet chamber 47a comprises the inlet 44 and the pressure side discharge chamber 47b comprises at least one discharge arrangement 45.
  • the pressure side cooling path 31b comprises three pressure side cooling chambers 47: one pressure side inlet chamber 47a and two subsequent discharge chambers 47b, each of which is provided with at least one discharge arrangement 45.
  • the cooling fluid coming from the respective feeding channel 30 of the root 17 flows along the pressure side inlet chamber 47a, along the pressure side discharge chamber 47b adjacent to the pressure side inlet chamber 47a and along the pressure side discharge chamber 47b closest to the trailing edge 28 and exits through the two discharge arrangements 45 of the pressure side discharge chambers 47b.
  • the flow of the cooling fluid along the pressure side cooling path 31b is a co-current flow with respect to the flow of the hot gas working fluid in the expansion channel 12 having direction D.
  • the leading edge cooling path 31c is defined by the inner central cooling chamber 38 and by a leading edge cooling chamber 49 arranged between the inner wall 36 and the outer wall 35 at the leading edge 27.
  • the inner central cooling chamber 38 being in fluidic communication with the leading edge cooling chamber 49 by at least one connecting aperture 50.
  • the inner central cooling chamber 38 and the leading edge cooling chamber 49 extend substantially along a direction going from the base 21 toward the tip 22.
  • the leading edge cooling path 31c comprising at least one inlet 51 (better visible in figure 2 ) and at least one discharge arrangement 53.
  • the discharge arrangement 53 being arranged closer to the leading edge 27 than the inlet 51.
  • the leading edge cooling path 31c comprises one inlet 51, which is defined by an aperture located at the base 21 of the airfoil 18 and in fluidic communication with the respective feeding channel 30 of the root 17.
  • the leading edge cooling path 31c comprises a plurality of discharge arrangements 53, which will be described in detail later.
  • the discharge arrangements 53 are at least three: at least one discharge arrangement 53 directed toward the leading edge 27, at least one discharge arrangement 53 directed toward the suction side 25 and at least one discharge arrangement 53 directed toward the pressure side 24.
  • leading edge cooling chamber 49 comprises the discharge arrangements 53, while the inner central cooling chamber 38 comprises the inlet 51.
  • the cooling fluid coming from the respective feeding channel 30 of the root 17 flows along the inner central cooling chamber 38, through the connecting aperture 50, along leading edge cooling chamber 49 and exits through the discharge arrangements 53 of the leading edge cooling chamber 49.
  • the flow of the cooling fluid along the leading edge cooling path 31c is a co-current flow with respect to the flow of the hot gas working fluid in the expansion channel 12 having direction D.
  • the trailing edge cooling path 31d is defined by a trailing edge cooling chamber 55 arranged between the inlet 40 of suction side cooling path 31a and the trailing edge 28.
  • the trailing edge cooling chamber 55 extends substantially along a direction going from the base 21 toward the tip 22.
  • the trailing edge cooling path 31d comprises at least one inlet 57 (better visible in figure 2 ) and at least one discharge arrangement 58.
  • the discharge arrangement 58 being arranged on the pressure side 24 and configured to direct the flow toward the trailing edge 28.
  • the trailing edge cooling path 31d comprises one inlet 57, which is defined by an aperture located at the base 21 of the airfoil 18 and in fluidic communication with the respective feeding channel 30 of the root 17.
  • trailing edge cooling path 31d comprises one discharge arrangement 58, which will be described in detail later.
  • the trailing edge cooling chamber 55 comprises the discharge arrangements 58 and the inlet 57.
  • the cooling fluid coming from the respective feeding channel 30 of the root 17 flows along the trailing edge cooling chamber 55 and exits through the discharge arrangement 58 toward the trailing edge 28.
  • suction side cooling chambers 42, the pressure side cooling chambers 47, the leading edge cooling chamber 49 and the trailing edge cooling chamber 55 can be optionally provided with at least one turbulator in order to improve the cooling effect.
  • suction side cooling chambers 42, the pressure side cooling chambers 47 and the trailing edge cooling chamber 55 may comprise turbulators defined by ribs which project from at least one internal face of the respective chamber and are angled with respect to the direction of the cooling fluid inside the chamber.
  • said turbulators project from three adjacent internal faces of the respective chamber.
  • the leading edge cooling chamber 49 may comprise a plurality of turbulators defined by ribs projecting from at least one internal face of the leading edge cooling chamber 49. Said ribs have a trapezoidal-shaped section. Preferably said turbulators are arranged staggered with respect to the inlet holes of the cooling arrangements 53 at least on the two internal faces of the leading edge cooling chamber 49 which are respectively closest to the pressure side 24 and to the suction side 25.
  • the discharging arrangement 41 of the suction side cooling path 31a, the discharge arrangements 45 of the pressure side cooling path 31b, the discharge arrangements 53 of the leading edge cooling path 31c and the discharge arrangement 58 of the trailing edge cooling path 31d have all the structure illustrated in figures 5 and 6 .
  • At least one of the discharge arrangement 41 45 53 58 have the structure illustrated in figures 5 and 6 .
  • Discharge arrangement 45 extends through the outer wall 35 from the respective internal face of the pressure side discharge cooling chamber 47b to the external face 37 of the outer wall 35.
  • the discharge arrangement 45 comprises a plurality of inlet holes 60, an outlet common slot 61 and a plurality of connecting channels 63, each of which is configured to connect a respective hole 60 with the outlet common slot 61.
  • the inlet holes 60 are identical to each other.
  • the connecting channels 63 are identical to each other.
  • the connecting channels 63 are diverging toward the outlet common slot 61.
  • the connecting channels 63 have a passage area which gradually increases toward the outlet common slot 61.
  • the increase of the passage area starts from an inlet section 65 of the connecting channels 63 and ends at an outlet section 66 of the connecting channels 63.
  • the inlet section 65 of each connecting channel 63 being in contact with the respective inlet hole 60 and the outlet section 66 of each connecting channel 63 being in contact with the outlet common slot 61.
  • the passage area of the inlet holes 60 is constant.
  • the passage area of the inlet hole 60 is smaller than the passage area of the inlet section 65 of the respective connecting channels 63.
  • the passage area of the inlet section 65 of the respective connecting channels 63 is 10-20% greater than the passage area of the inlet hole 60.
  • the area ratio between inlet section 65 and outlet section 66 of the connecting channels 63 is comprised between 3,5 to 5.
  • the inlet holes 60 are substantially aligned along a direction F on the respective internal face of the pressure side discharge cooling chamber 47b.
  • the inlet holes 60 are arranged equally spaced from each other.
  • the outlet common slot 61 is substantially aligned along a direction parallel to direction F.
  • Direction F is substantially a straight line extending from the base 21 to tip 22 of the airfoil 18.
  • the discharge arrangement 45 extends along a main axis G which is inclined with respect to the external face 37 of the outer wall with an angle ⁇ .
  • the inlet holes 60 and the connecting channels 63 and the outlet common slot 61 extends along said main axis G as shown in the cross section of figure 5 .
  • the depth DH of the inlet holes 60 is 10-20% of the total depth Dtot of the outer wall 35; wherein both depth DH and depth Dtot are measured along the main axis G.
  • the depth DC of the connecting channels 63 is 50%-70% of the total depth Dtot of the outer wall 35; wherein both depth DC and depth Dtot are measured along the main axis G.
  • Depth DS of the outlet common slot 61 is 20-30% of the total depth Dtot of the outer wall 35; wherein both depth DS and depth Dtot are measured along the main axis G.
  • angle ⁇ of inclination and the total depth of the outer wall 35 measured along the main axis G can be different for each one of the discharge arrangements 41 45 53 58.
  • the angle ⁇ of discharge arrangement 58 is equal or greater than the angle ⁇ of discharge arrangement 45.
  • the cooling fluid coming from the respective pressure side discharge cooling chamber 47b is divided by the plurality of inlet holes 60, flows into the respective connecting channels 63 and joins at the outlet common slot 61.
  • a single wide and homogenous flow of cooling fluid exits from the outlet common slot 61 as indicated also by the arrow in figure 6 .
  • outlet common slot 61 improves the film cooling efficiency as the external face 37 of the outer wall 35 is lapped by a cooling flow which is wide and homogeneous.
  • FIG 7 a further embodiment of the discharge arrangement 145 is illustrated.
  • the same reference numbers used for the cooling arrangement 45 of figures 5 and 6 are used also in figure 7 for indicating similar or identical parts.
  • the discharge arrangement 145 comprises at least two discharge groups 146
  • the discharge arrangement 145 comprises three discharge groups 146.
  • Each discharge group 146 comprises a plurality of inlet holes 160, an outlet common slot 161 and a plurality of connecting channels 163, each of which is configured to connect a respective hole 160 with the outlet common slot 161.
  • each connecting channel 163 have an inlet section 165 and an outlet section 166; the inlet section 165 of each connecting channel 163 being in contact with the respective inlet hole 160 and the outlet section 166 of each connecting channel 163 being in contact with the outlet common slot 161.
  • the passage area of each inlet hole 160 is preferably smaller than the passage area of the inlet section 165 of the respective connecting channels 163 analogously to the embodiment illustrated in figure 6 .
  • each discharge group 146 comprises a three inlet holes 160, an outlet common slot 161 and three connecting channels 163, each of which is configured to connect a respective hole 160 with the outlet common slot 161.
  • the inlet holes 160 of each group 146 are equally spaced one from the other.
  • the discharge groups 146 are spaced one from the other. Preferably the discharge groups 146 are equally spaced one from the other.
  • cooling fluid coming from the respective pressure side discharge cooling chamber 47b is divided by the plurality of inlet holes 160, flows into the respective connecting channels 163 and joins at the outlet common slots 161.
  • three homogenous flows of cooling fluid exits from the outlet common slots 161 as indicated also by the arrows in figure 7 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP17174863.5A 2017-06-07 2017-06-07 Gekühlte gasturbinenschaufel Active EP3412866B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17174863.5A EP3412866B1 (de) 2017-06-07 2017-06-07 Gekühlte gasturbinenschaufel
CN201810580261.3A CN108999645B (zh) 2017-06-07 2018-06-07 用于燃气涡轮的叶片和包括所述叶片的电力生成设备

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17174863.5A EP3412866B1 (de) 2017-06-07 2017-06-07 Gekühlte gasturbinenschaufel

Publications (2)

Publication Number Publication Date
EP3412866A1 true EP3412866A1 (de) 2018-12-12
EP3412866B1 EP3412866B1 (de) 2024-10-23

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EP17174863.5A Active EP3412866B1 (de) 2017-06-07 2017-06-07 Gekühlte gasturbinenschaufel

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EP (1) EP3412866B1 (de)
CN (1) CN108999645B (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3597859B1 (de) * 2018-07-13 2023-08-30 Honeywell International Inc. Turbinenschaufel mit staubtolerantem kühlsystem

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN117468992A (zh) * 2022-07-22 2024-01-30 中国航发商用航空发动机有限责任公司 高压涡轮的动叶片

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US4303374A (en) * 1978-12-15 1981-12-01 General Electric Company Film cooled airfoil body
US20070280832A1 (en) * 2006-06-06 2007-12-06 Siemens Power Generation, Inc. Turbine airfoil with floating wall mechanism and multi-metering diffusion technique
EP2107215A1 (de) 2008-03-31 2009-10-07 ALSTOM Technology Ltd Gasturbinenschaufel
US8864469B1 (en) * 2014-01-20 2014-10-21 Florida Turbine Technologies, Inc. Turbine rotor blade with super cooling

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US7029235B2 (en) * 2004-04-30 2006-04-18 Siemens Westinghouse Power Corporation Cooling system for a tip of a turbine blade
US7416390B2 (en) * 2005-03-29 2008-08-26 Siemens Power Generation, Inc. Turbine blade leading edge cooling system
US7780413B2 (en) * 2006-08-01 2010-08-24 Siemens Energy, Inc. Turbine airfoil with near wall inflow chambers
US8535004B2 (en) * 2010-03-26 2013-09-17 Siemens Energy, Inc. Four-wall turbine airfoil with thermal strain control for reduced cycle fatigue
CN103080477B (zh) * 2010-06-23 2015-08-12 西门子公司 燃气涡轮叶片
CN102022139A (zh) * 2010-12-10 2011-04-20 南京航空航天大学 地面燃气轮机涡轮叶片内部冷却装置及方法
EP2682565B8 (de) * 2012-07-02 2016-09-21 General Electric Technology GmbH Gekühlte Schaufel für eine Gasturbine
CN102979583B (zh) * 2012-12-18 2015-05-20 上海交通大学 用于燃气轮机涡轮叶片的分离式柱肋冷却结构
CN103277145A (zh) * 2013-06-09 2013-09-04 哈尔滨工业大学 一种燃气涡轮冷却叶片

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4303374A (en) * 1978-12-15 1981-12-01 General Electric Company Film cooled airfoil body
US20070280832A1 (en) * 2006-06-06 2007-12-06 Siemens Power Generation, Inc. Turbine airfoil with floating wall mechanism and multi-metering diffusion technique
EP2107215A1 (de) 2008-03-31 2009-10-07 ALSTOM Technology Ltd Gasturbinenschaufel
US8231349B2 (en) 2008-03-31 2012-07-31 Alstom Technology Ltd. Gas turbine airfoil
US8864469B1 (en) * 2014-01-20 2014-10-21 Florida Turbine Technologies, Inc. Turbine rotor blade with super cooling

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3597859B1 (de) * 2018-07-13 2023-08-30 Honeywell International Inc. Turbinenschaufel mit staubtolerantem kühlsystem

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EP3412866B1 (de) 2024-10-23
CN108999645A (zh) 2018-12-14
CN108999645B (zh) 2023-05-16

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