EP2611990B1 - Aube de turbine pour une turbine à gaz - Google Patents

Aube de turbine pour une turbine à gaz Download PDF

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Publication number
EP2611990B1
EP2611990B1 EP11749827.9A EP11749827A EP2611990B1 EP 2611990 B1 EP2611990 B1 EP 2611990B1 EP 11749827 A EP11749827 A EP 11749827A EP 2611990 B1 EP2611990 B1 EP 2611990B1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
side wall
inwardly facing
channel
trailing edge
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.)
Not-in-force
Application number
EP11749827.9A
Other languages
German (de)
English (en)
Other versions
EP2611990A1 (fr
Inventor
Fathi Ahmad
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 EP11749827.9A priority Critical patent/EP2611990B1/fr
Publication of EP2611990A1 publication Critical patent/EP2611990A1/fr
Application granted granted Critical
Publication of EP2611990B1 publication Critical patent/EP2611990B1/fr
Not-in-force 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/60—Structure; Surface texture
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a turbine blade with an airfoil which can be flowed around by a hot gas and which comprises a suction sidewall and a pressure sidewall which extend in the direction of flow of the hot gas from a common leading edge to a trailing edge, wherein at the rear edge at least one opening for blowing out a previously cooling the blade Coolant is arranged, which is in flow communication with at least one opening with a arranged in the airfoil cavity by means of a channel, wherein the channel is also bounded by an inwardly facing surface of the suction side wall and an inwardly facing surface of the pressure side wall and for adjusting the from the Opening exiting coolant amount is provided a throttle element.
  • An aforementioned turbine blade and a casting core for producing such a turbine blade are, for example, from WO 2003/042503 A1 known.
  • the arranged at the trailing edge of a common cavity is preceded by in the three rows of columnar sockets - also known under the name "Pin-Fins" - are arranged, which increases the heat transfer of them passing cooling air and to increase the Pressure loss are provided there.
  • the casting core required for producing such a turbine blade is shown in FIG WO 2003/042503 A1 shown in perspective.
  • the space occupied by the casting core remains after production of the cast turbine blade as Cavity in the turbine blade, wherein arranged in the casting core openings are filled with casting material.
  • the casting core represents the negative image of the interior of the turbine blade.
  • pins are arranged in the form of a grid in the cavity of the double wall.
  • the pins have a diamond shape in principle, with their corners rounded and their edges are concave inward. Between the pins thus creates a network of passages for cooling air, each having a narrowed inlet and a narrowed outlet opening, between which a diffuser and nozzle section is arranged.
  • the sections aim to slow down and accelerate the cooling air for efficient cooling.
  • the object of the invention is therefore to provide an initially mentioned turbine blade for a gas turbine, which is efficient and sufficiently coolable with the smallest possible amount of coolant.
  • the turbine blade for a gas turbine comprises an airfoil which can be flowed around by a hot gas and which comprises a suction sidewall and a pressure sidewall which extend from a common leading edge to a trailing edge in the direction of flow of the hot gas, at least one opening for blowing out the airfoil at or in the trailing edge previously cooling coolant is arranged, which is at least one opening in fluid communication with an arranged in the airfoil cavity by means of a channel, wherein the channel is also bounded by an inwardly facing surface of the suction side wall and an inwardly facing surface of the pressure side wall and adjusting the is provided from the opening exiting cooling air amount, a throttle element, according to the invention, the throttle element upstream - in relation to the flow direction of the channel - the respective opening is arranged and comprises two surveys, each a n one of the two inwardly facing surfaces are arranged.
  • the throttle element comprises on the inwardly facing surfaces arranged elevations which extend transversely to the flow direction of the channel and between which the minimum flow cross-section of the channel is arranged.
  • the minimum vertical distance between each of the neutral fibers of the coolant flow and one of the two side surfaces in the cooling channel is to be detected.
  • the invention is based on the finding that the coolant consumption with the proposed construction is particularly simple and precisely adjustable, in which the throttle element is arranged in the blade interior upstream of the trailing edge opening.
  • the throttle element is to be formed by two mutually related elevations, each of which are arranged on the inwardly facing surface of the suction side wall and pressure side wall. None of the elevations connects the suction side wall with the pressure side wall.
  • This embodiment of the throttle element is particularly advantageous for turbine blades produced in the casting process.
  • turbine blades are usually produced in casting processes in which so-called lost casting cores are used to produce the internal cooling system. The production of these cores is usually done with the help of a core tool.
  • the core tool comprises two slider elements which can be moved towards and away from each other.
  • these slide elements When pushed together, these slide elements surround a cavity which has the same contour as the cavity of the turbine blade to be cast.
  • the casting core material is inserted into the cavity of the slider elements. After the casting core material has dried, the casting core is available for producing the turbine blade.
  • the slide elements for producing a first prototype of the turbine blade series to be produced are designed such that in the turbine blade prototype to be produced the throttling, minimum distance between the surveys is definitely smaller than the theoretically required.
  • the first turbine blade prototype produced therewith is then subjected to a coolant flow measurement. Desirably, due to the first time too small distance between the surveys, the throttle effect is too large, which initially leads to a low flow rate.
  • the slide elements are changed. Their elevations are slightly changed, which increases in the collapsed state whose minimum distance. Subsequently, another casting core is produced with it. With this another turbine blade prototype is produced, the flow rate is then determined again and compared with the desired amount.
  • the manufacturing process of the slide elements is completed.
  • the slide elements are then designed so that casting cores are always produced with them, which can be used to manufacture serial turbine blades in series.
  • all steps for the production of a further turbine blade prototype are again carried out, the minimum distance of which is slightly larger than the previous prototype.
  • each of the two slides can be processed by itself - such as by grinding the survey arranged thereon - without fundamentally changing the construction of the turbine blade and its cooling system. It is possible that only one of the slide elements or both slide elements are processed during an iteration step.
  • This method is also particularly suitable for modifications of existing blades in the event that more cooling air is needed for sufficient cooling. In this case, there are only minor changes in the blade design required. An additional qualification because of an otherwise required casting change is therefore not necessary.
  • the two elevations - seen in the flow direction of the cooling channel - offset from one another.
  • the vertical distance between the inner surface of the pressure sidewall and the inner surface of the suction sidewall can be further reduced, resulting in particularly narrow trailing edge regions of airfoils. This reduces aerodynamic losses in hot gas flowing around the airfoil.
  • the invention leads to the reduction of the scrap rate in the manufacture of turbine blades, which significantly improves the production costs and the production time of turbine blades.
  • elevation which is arranged on the inwardly facing surface of the pressure side wall, arranged downstream of that elevation, which is arranged on the inwardly facing surface of the suction side wall.
  • This construction forces coolant flow in the channel, which flows more intensively past the inwardly facing surface of the suction sidewall.
  • cut-back trailing edges an extended film cooling effect of the unprotected end of the suction-side trailing edge can be achieved, which reduces wear phenomena there and extends the service life of the turbine blade.
  • a plurality of openings are arranged at the trailing edge, wherein the cooling channel jointly connects a plurality of openings with the cavity.
  • elevations are formed as ribs, with the help of this angular contour of the inwardly facing surfaces of the side walls of the airfoil in operation and turbulence be generated in the coolant.
  • these turbulences can contribute to the throttle effect and, on the other hand, to increase the heat transfer due to more turbulent coolant flow.
  • the interior of the turbine blade proposed by the invention can be used both for turbine blades with (for the side walls) common trailing edge and for turbine blades with a so-called cut-back trailing edge.
  • FIG. 1 A gas turbine blade 10 relating to the invention is shown in FIG FIG. 1 shown in perspective.
  • the gas turbine blade 10 is according to FIG. 1 designed as a blade.
  • the invention can also be used in a guide vane not shown a gas turbine.
  • the turbine blade 10 comprises a cross-sectionally fir-tree-shaped blade root 12 and a platform 14 arranged thereon.
  • the platform 14 is adjoined by an aerodynamically curved blade 16, which has a leading edge 18 and a trailing edge 20.
  • Provided at the front edge 18 are cooling holes arranged as so-called "shower heads", from which a coolant flowing inside, preferably cooling air, can emerge.
  • the airfoil 16 includes a - with respect FIG. 1 - Rear suction side wall 22 and a front side pressure side wall 24.
  • the trailing edge 20 Along the trailing edge 20 a plurality of openings 28 are provided, which are separated by interposed webs 30 from each other.
  • the trailing edge 20 is designed as a so-called cut-back trailing edge, so that the openings 28 are located on the pressure side rather than centrally in the trailing edge 20th
  • FIG. 2 shows the interior of a turbine blade known in the prior art in a longitudinal section along a plane, spanned by a center line extending from the leading edge 18 to the trailing edge 20 of the airfoil 16, and the blade longitudinal direction extending from the blade root 12 to the blade tip extends.
  • FIG. 2 are further to the right arranged the trailing edge openings 28 shown, between which the webs 30 are arranged.
  • the webs 30 extend substantially parallel to a hot gas flow which, during operation, flows around the airfoil 16 from the front edge 18 to the rear edge 20.
  • FIG. 2 shown on the left is a plurality of arranged in a grid column or sockets 32 are provided. Both the sockets 32 and the webs 30 extend from an inner surface 34 of the suction side wall 22 to an in FIG. 2 Consequently, the sockets 32 are arranged in a cavity 38 of the turbine blade 10, which is bounded laterally by the suction side wall 22 and the pressure side wall 24.
  • a coolant for example cooling air 40 or cooling steam
  • a coolant flows through the cavity 38 during operation.
  • the in FIG. 2 not shown part of the turbine blade 10 formed in the interior so that the field of sockets 32 is substantially uniformly flowed through by cooling air 40.
  • the uniform flow of the arranged in grid base 32 is shown by the arrows marked 40.
  • the cooling air 40 impinges on individual pedestals 32 and is thereby deflected by them, the main flow direction of which remains essentially unchanged. This creates 40 turbulences in the cooling air.
  • the introduced from the hot gas in the blade walls 22, 24 heat is passed from these further into the base 32. There, the cooling air 40 impinging on the base 32 absorbs the heat and transports it.
  • cooling air 40 After the cooling air 40 has flowed through the base field, this enters into passages 41 which connect the cavity 38 with the openings 28. After flowing through the passages 41, the cooling air 40 passes out of the turbine blade 10 through the openings 28 and mixes with the hot gas flowing around the blade 16.
  • elevations 42, 44 are provided on the inner surfaces 34, 36 of the suction side wall 22 and the pressure side wall 24, respectively. 3, FIG. 4 ) intended.
  • One (42) of the two elevations 42, 44 is arranged on the inner surface 34 or part thereof, the other (44) of the two elevations 42, 44 is located on the inner surface 36 or part of this.
  • the inner surfaces 34, 36 define a cavity 38 and a cooling channel 46, which connects the cavity 38 with the openings 28. It is possible that cavity 38 and channel 46 merge into one another.
  • the minimum distance between the inner surface 34 and the inner surface 36 in the region of the two elevations 42, 44 is now provided. This is - in FIG.
  • the minimum distance A forming the throttle element is located between the two elevations 42, 44, whereby they are in relation to one another.
  • the elevations 42, 44 replace neither the base 32 nor the webs 30th
  • the elevations 42, 44 extend along the blade longitudinal direction (perpendicular to the sheet plane) over the entire height of the cooling channel 46.
  • the contour of the elevations 42, 44 are, as in the cross section shown in FIG. 3 , Such that they allow a stepless and edge-free course of the cooling channel in the flow direction of the coolant to the trailing edge opening 28 out.
  • the cooling channel 46 converges.
  • the elevations are also designed in the form of ribs, as in FIG. 4 shown.
  • each iteration comprises producing a turbine blade with a defined rib height H 1 and H 2 and determining the coolant consumption of the corresponding turbine blade prototype.
  • a turbine blade 10 is provided which allows a simple and inexpensive test phase during the tooling phase to provide, after completion of the iterations for a series of turbine blades 10, precisely manufactured core tooling.
  • the throttle element instead of two surveys 42, 44 comprises only a single survey 44 (or 42), so that the flow rate determining minimum distance between a single survey 44 (or 42) and its opposite, then after inside facing surface 34 (or 36) of the suction side wall 22 (or the pressure side wall 36) is located.
  • the opposing surface 34 or 36 may then also be designed flat in the region of the minimum distance, this embodiment not forming part of the invention.
  • the invention specifies a turbine blade 10 whose amount of coolant 40 flowing out of the trailing edge 20 is set comparatively simply and exactly immediately upon casting of the turbine blade 10, without requiring reworking of the cast turbine blade 10 with regard to adjusting the coolant consumption.
  • elevations 42, 44 are located on the inner surfaces 34, 36 of the suction side wall 22 or pressure side wall 24, between which the throttle element is located, by means of which the amount of coolant flowing out is set. This arrangement allows the simple production of a core tool with which the casting cores required for casting the turbine blade 10 can always be produced many times with the desired accuracy.

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

Claims (6)

  1. Aube ( 10 ) de turbine pour une turbine à gaz,
    comprenant une lame ( 16 ) d'aube sur laquelle peut passer un gaz chaud, et qui comprend une paroi ( 22 ) d'extrados et une paroi ( 24 ) d'intrados, qui s'étendent dans la direction du courant du gaz chaud d'un bord ( 18 ) avant commun à un bord ( 20 ) arrière,
    dans laquelle il est ménagé, sur le bord ( 20 ) arrière, au moins une ouverture ( 28 ) d'insufflation d'un fluide ( 40 ) de refroidissement, refroidissant d'abord la lame ( 16 ) de l'aube, ouverture qui, au moyen d'un canal ( 46 ), est en communication avec une cavité ( 38 ) disposée dans la lame ( 16 ) de l'aube,
    dans laquelle le canal ( 46 ) est délimité aussi par une surface ( 34 ), tournée vers l'intérieur, de la paroi ( 22 ) d'extrados et par une surface ( 36 ), tournée vers l'intérieur, de la paroi ( 24 ) d'intrados et il est prévu un élément d'étranglement pour le réglage de la quantité de fluide de refroidissement sortant de l'ouverture ( 28 ), caractérisée en ce que
    l'élément d'étranglement comprend en amont - par rapport au sens de passage dans le canal ( 46 ) - de l'ouverture ( 28 ) concernée, deux surélévations ( 42, 44 ), qui - considérées dans le sens de passage dans le canal ( 46 ) de refroidissement - sont décalées l'une par rapport à l'autre et entre lesquelles se trouve la section transversale de passage minimum du canal, les deux éléments d'étranglement étant mis respectivement sur l'une des deux surfaces ( 34, 36 ) tournées vers l'intérieur.
  2. Aube ( 10 ) de turbine suivant la revendication 1,
    dans laquelle la surélévation ( 42, 44 ), qui se trouve sur la surface ( 36 ), tournée vers l'intérieur, de la paroi ( 24 ) d'intrados, est disposée en aval de la surélévation ( 42, 44 ) qui est disposée sur la surface ( 34 ), tournée vers l'intérieur, de la paroi ( 22 ) d'extrados.
  3. Aube ( 10 ) de turbine suivant la revendication 1 ou 2,
    dans laquelle il est prévu, sur le bord ( 20 ) arrière, plusieurs ouvertures ( 28 ) et le canal ( 46 ) de refroidissement met en communication commune plusieurs ouvertures ( 28 ) avec la cavité ( 38 ).
  4. Aube ( 10 ) de turbine suivant l'une des revendications précédentes,
    dans laquelle les surélévations ( 42, 44 ) sont constituées sous la forme de nervures.
  5. Aube ( 10 ) de turbine suivant l'une des revendications 1 à 3,
    dans laquelle le canal ( 46 ) de refroidissement converge et les deux surélévations ( 42, 44 ) sont implantées sur les surfaces ( 34, 36 ) tournées vers l'intérieur, suivant un tracé sans palier et sans arête.
  6. Aube ( 10 ) de turbine suivant l'une des revendications précédentes,
    dans laquelle les ouvertures ( 28 ) sont prévues du côté de l'intrados.
EP11749827.9A 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz Not-in-force EP2611990B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11749827.9A EP2611990B1 (fr) 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10175235A EP2426317A1 (fr) 2010-09-03 2010-09-03 Aube de turbine pour une turbine à gaz
PCT/EP2011/064811 WO2012028574A1 (fr) 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz
EP11749827.9A EP2611990B1 (fr) 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz

Publications (2)

Publication Number Publication Date
EP2611990A1 EP2611990A1 (fr) 2013-07-10
EP2611990B1 true EP2611990B1 (fr) 2015-01-28

Family

ID=43545953

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10175235A Withdrawn EP2426317A1 (fr) 2010-09-03 2010-09-03 Aube de turbine pour une turbine à gaz
EP11749827.9A Not-in-force EP2611990B1 (fr) 2010-09-03 2011-08-29 Aube de turbine pour une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10175235A Withdrawn EP2426317A1 (fr) 2010-09-03 2010-09-03 Aube de turbine pour une turbine à gaz

Country Status (5)

Country Link
US (1) US20130156599A1 (fr)
EP (2) EP2426317A1 (fr)
JP (1) JP5738996B2 (fr)
CN (1) CN103080478B (fr)
WO (1) WO2012028574A1 (fr)

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US7780415B2 (en) * 2007-02-15 2010-08-24 Siemens Energy, Inc. Turbine blade having a convergent cavity cooling system for a trailing edge
US7785070B2 (en) * 2007-03-27 2010-08-31 Siemens Energy, Inc. Wavy flow cooling concept for turbine airfoils
CH700321A1 (de) * 2009-01-30 2010-07-30 Alstom Technology Ltd Gekühlte schaufel für eine gasturbine.

Also Published As

Publication number Publication date
EP2426317A1 (fr) 2012-03-07
WO2012028574A1 (fr) 2012-03-08
JP2013536913A (ja) 2013-09-26
JP5738996B2 (ja) 2015-06-24
CN103080478A (zh) 2013-05-01
EP2611990A1 (fr) 2013-07-10
CN103080478B (zh) 2015-05-20
US20130156599A1 (en) 2013-06-20

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