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EP1790819B1 - Turbinenschaufel umfassend einen Kühlkreislauf - Google Patents

Turbinenschaufel umfassend einen Kühlkreislauf Download PDF

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Publication number
EP1790819B1
EP1790819B1 EP06124041.2A EP06124041A EP1790819B1 EP 1790819 B1 EP1790819 B1 EP 1790819B1 EP 06124041 A EP06124041 A EP 06124041A EP 1790819 B1 EP1790819 B1 EP 1790819B1
Authority
EP
European Patent Office
Prior art keywords
cavity
blade
suction
pressure
cooling circuit
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.)
Active
Application number
EP06124041.2A
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English (en)
French (fr)
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EP1790819A1 (de
Inventor
Pascal Deschamps
Patrice Eneau
Thomas Potier
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1790819A1 publication Critical patent/EP1790819A1/de
Application granted granted Critical
Publication of EP1790819B1 publication Critical patent/EP1790819B1/de
Active legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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
    • F05D2260/2214—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 present invention relates to the general field of cooling turbomachine moving blades, and in particular to the blades of the high-pressure turbine.
  • EP-A-1,584,790 discloses a blade according to the preamble of claim 1.
  • the main object of the present invention is thus to overcome such disadvantages by proposing a central cooling circuit of a mobile blade for efficient cooling of the blade at a low manufacturing cost.
  • a turbomachine moving blade is provided according to claim 1.
  • the intrados and extrados cooling circuits thus defined present an asymmetry of configuration between the intrados and the extrados and are specific to each wall (intrados, extrados) of the dawn.
  • the levels of heat exchange which are lower on the intrados than on the upper surface of the dawn.
  • the extrados cooling circuit may comprise a first cavity and a second cavity extending on the extrados side of the blade, a third cavity extending from the intrados to the extrados of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other radial end of the second cavity with a radial end adjacent to the third cavity, and outlet orifices opening in the third cavity and opening on the intrados face of the blade.
  • the third cavity of such an extrados cooling circuit can be arranged on the side of the leading edge or trailing edge of the blade.
  • the extrados cooling circuit may comprise a first cavity and a second cavity extending on the extrados side of the blade, a third cavity extending on the intrados side of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other end; radial of the second cavity with a radial end adjacent to the third cavity, and outlet orifices opening in the third cavity and opening on the intrados face of the blade.
  • the third cavity of such an extrados cooling circuit can be disposed on the leading edge side or the trailing edge of the blade.
  • the intrados cooling circuit may comprise a first, a second and a third cavity extending on the intrados side of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other radial end of the second cavity with a radial end adjacent to the third cavity; , and outlets opening in the third cavity and opening on the intrados face of the blade.
  • the blade may also comprise a cooling circuit of the leading edge of the blade and a cooling circuit of the trailing edge of the blade.
  • the invention also relates to a gas turbine comprising at least one moving blade as defined above.
  • the invention also relates to a turbomachine comprising at least one moving blade as defined above.
  • the figure 1 represents a moving blade 10 of a turbomachine, such as a moving blade of a high-pressure turbine.
  • a turbomachine such as a moving blade of a high-pressure turbine.
  • the invention can also be applied to other blades of the turbomachine, for example to the blades of the low-pressure turbine thereof.
  • the blade 10 has an aerodynamic surface (or blade) which extends radially between a blade root 12 and a blade tip 14 ( figures 3 and 4 ).
  • This aerodynamic surface consists of a leading edge 16 disposed opposite the flow of hot gases from the combustion chamber of the turbomachine, a trailing edge 18 opposite to the leading edge 16, of a lateral face 20 and an extrados lateral face 22, these lateral faces 20, 22 connecting the leading edge 16 to the trailing edge 18.
  • the blade 10 has a central portion C which occupies the geometric zone of the blade for which the distance between its intrados 20 and extrados faces 22 is the largest.
  • the central part C of the blade is divided geometrically into four adjacent intrados zones Z1 to Z4 disposed on the intrados side of the blade and in four adjacent extrados zones Z5 to Z8 disposed on the extrados side, the intrados and extrados zones being distributed from on both sides of the skeleton S of dawn.
  • Skeleton of the dawn means the geometric line S points equidistant from the side faces intrados 20 and extrados 22 of the blade.
  • the skeleton S of the blade defines two main areas of the central portion C of the blade which are each divided into four adjacent zones by three geometric lines L1 to L3 radially cutting the blade in the direction of its thickness.
  • the intrados geometrical zones Z1 to Z4 and extrados Z5 to Z8 thus defined constitute the smallest elements that can contain a cooling cavity.
  • these zones extend in cross-section on a surface typically comprised between 3 and 10 mm 2 approximately.
  • the central portion C of the blade is provided with a lower pressure cooling circuit and an extrados cooling circuit, the intrados cooling circuit comprising three radial cavities occupying three adjacent intrados zones, and the cooling circuit extrados cooling comprising three radial cavities occupying the four extrados areas and the remaining intrados area.
  • radial cavity is meant for the rest of the description, a cavity extending radially between the foot 12 and the top 14 of the blade.
  • the inner cooling circuit of the blade 10a comprises three radial cavities 24a, 26a and 28a respectively occupying the three adjacent intrados zones Z3, Z2 and Z1 of the figure 1 .
  • the extrados cooling circuit of the blade comprises three extrados radial cavities 30a, 32a and 34a occupying the four extrados zones Z5 to Z8 and the remaining intrados zone Z4.
  • the upper surface of the blade has a first cavity 30a extending on the upper surface of the blade and occupying the extrados zone Z5, a second cavity 32a extending on the upper surface of the blade and occupying the zones. extrados Z6 and Z7, and a third cavity 34a extending from the intrados face 20 to the extrados face 22 of the blade and occupying the extrados zone Z8 and the intrados zone Z4.
  • cavity extending on the upper surface of the blade is meant a cavity which extends in the direction of the thickness of the blade from the extrados face 22 of the blade to its skeleton S.
  • the cavities 30a to 34a of the extrados cooling circuit are cavities having cross sections greater than about 4 mm 2 .
  • the third cavity 34a of this extrados circuit which extends from the intrados face 20 to the extrados face 22 of the blade is disposed on the side of the trailing edge 18 of the blade.
  • the extrados cooling circuit also comprises an air inlet opening 36 at a radial end of the first cavity 30a (here at the foot 12 of the blade) to supply air to the extrados circuit.
  • a first passage 38 communicates the other radial end of the first cavity 30a (that is to say at the top 14 of the blade) with a radial end adjacent to the second cavity 32a.
  • a second passage 40 communicates the other radial end of the second cavity 32a with a radial end adjacent to the third cavity 34a.
  • outlet orifices 42a open into the third cavity 34a and open on the underside face 20 of the blade. These outlet orifices 42a are regularly distributed over the entire radial height of the blade.
  • the circulation of the cooling air which runs through this extrados circuit derives evidently from the foregoing.
  • the circuit is supplied with cooling air through the inlet opening 36.
  • the air first passes through the first cavity 30a (according to a centrifugal flow) and then the second extrados cavity 32a (according to a centripetal flow) and finally the cavity central 34a (according to a centrifugal flow) before being emitted at the underside 20 of the blade through the outlet orifices 42a.
  • the cooling circuit intrados dawn comprises a first cavity 24a occupying the intrados zone Z3, a second cavity 26a occupying the intrados zone Z2 and a third cavity 28a occupying the intrados zone Z1.
  • cavities 24a to 28a extend on the intrados side of the blade, that is to say they extend in the direction of the thickness of the blade from the intrados face 20 of the blade until 'to his skeleton S.
  • cavities 24a to 28a are cavities having cross sections less than about 15 mm 2 .
  • the intrados cooling circuit also comprises an air inlet opening 44 at a radial end of the first cavity 24a (here at the foot 12 of the blade) for supplying air to the intrados circuit.
  • a first passage 46 communicates the other radial end (at the top 14 of the blade) of the first cavity 24a with a radial end adjacent to the second cavity 26a.
  • a second passage 48 communicates the other radial end of the second cavity 26a with a radial end adjacent to the third cavity 28a.
  • Outlets 50a open in the third cavity 28a and open on the underside face 20 of the blade.
  • the circulation of the cooling air which runs through this intrados circuit follows clearly from the foregoing.
  • the circuit is supplied with cooling air through the inlet opening 44.
  • the air then travels through the first 24a, second 26a and third cavities 28a before being emitted on the underside 20 of the blade by the orifices of exit 50a.
  • the inner walls of the cavities 24a, 26a, 28a, 30a, 32a and 34a of the lower and upper suction cooling circuits may advantageously be equipped with flow disruptors 52 intended to increase heat transfer along these walls. .
  • These flow disruptors may be in the form of ribs which are straight or inclined relative to the axis of rotation of the blade or in the form of pins (or any other equivalent forms).
  • the figure 5 represents an alternative embodiment of the cooling circuits intrados and extrados of the blade.
  • the extrados cooling circuit of the blade 10b comprises a first cavity 34b occupying the extrados zone Z8, a second cavity 36b occupying the extrados zones Z6 and Z7 and a third cavity 38b occupying the extrados zone Z5 and the intrados zone Z1.
  • the extrados circuit is distinguished in particular in that the third cavity 38b is disposed on the side of the leading edge 16 of the blade (and not the side of the trailing edge thereof).
  • An unrepresented air inlet opening is provided at a radial end (at the root of blade) of the first cavity 34b and passages (not shown) allow communication between the different cavities 34b, 36b and 38b according to a realization similar to that of the extrados circuit of Figures 2 to 4 .
  • Outlets 42b open in the third cavity 38b and open on the underside face 20 of the blade. The direction of air circulation in this extrados circuit is therefore reversed with respect to that of the embodiment of the Figures 2 to 4 .
  • the inner cooling circuit of the blade 10b comprises a first cavity 24b occupying the intrados zone Z2, a second cavity 26b occupying the intrados zone Z3 and a third cavity 28b occupying the intrados zone Z4.
  • an inlet opening (not shown) is provided at a radial end (at the root of blade) of the first cavity 24b and passages (not shown) allow communication between the different cavities 24b, 26b and 28b according to an embodiment similar to that of the intrados Figures 2 to 4 .
  • Outlets 50b open in the third cavity 28b and open on the underside face 20 of the blade. The direction of air circulation in this intrados circuit is therefore reversed with respect to that of the embodiment of the Figures 2 to 4 .
  • the figure 6 represents another alternative embodiment of the cooling circuits intrados and extrados of the blade.
  • the extrados cooling circuit of the blade 10c comprises a first cavity 34c occupying the extrados zones Z7 and Z8, a second cavity 36c occupying the extrados zones Z5 and Z6 and a third cavity 38c occupying the intrados zone Z1.
  • the third cavity 38c of the extrados cooling circuit is thus disposed on the side of the leading edge 16 of the blade.
  • cooling air is admitted into the first cavity 34c via an air inlet opening (not shown) and passages (not shown) allow communication between the different cavities 34c, 36c and 38c.
  • Outlets 42c open in the third cavity 38c and open on the underside face 20 of the blade.
  • the figure 7 represents yet another alternative embodiment of the cooling circuits intrados and extrados of the blade.
  • the extrados cooling circuit of the blade 10c comprises a first cavity 34d occupying the extrados zones Z5 and Z6, a second cavity 36d occupying the extrados zones Z7 and Z8 and a third cavity 38d occupying the intrados zone Z4.
  • the third cavity 38d of this extrados circuit is disposed on the trailing edge 18 side of the blade (rather than the leading edge side).
  • the cooling air is admitted into the first cavity 34d through an air inlet opening (not shown) and passages (not shown) allow communication between the various cavities 34d, 36d and 38d according to a realization similar to that of the extrados circuit of Figures 2 to 4 .
  • Outlets 42d open in the third cavity 38d and open on the underside face 20 of the blade. The direction of air flow in this extrados circuit is therefore reversed with respect to that of the embodiment of the figure 6 .
  • the intrados cooling circuit it is identical in its implementation to that described in connection with the Figures 2 to 4 .
  • the downward and upward cooling circuits each have their own air intake opening and that there is no air communication from one circuit to the other so that these circuits are completely independent of each other.
  • the leading edge cooling circuit of the blade comprises a first radial cavity 54 extending in the vicinity of the leading edge 16 of the blade and a second radial cavity 56 extending from the intrados face 20 to the extrados face 22 of the blade, this second cavity 56 being disposed between the first cavity 54 and the central portion C of the blade.
  • At least one air intake port 58 opens into the second cavity 56 to supply air to the leading edge circuit.
  • a plurality of communication holes 60 distributed over the entire radial height of the blade open into the second cavity 56 and open into the first cavity 54.
  • outlet orifices 62 opening into the first cavity 54 open onto the leading edge 16 and on the intrados 20 and extrados 22 faces of the blade.
  • the cooling circuit of the trailing edge of the blade comprises a first radial cavity 64 extending in the vicinity of the trailing edge 18 of the blade and a second radial cavity 66 extending from the underside face 20 to at the extrados face 22 of the blade, this second cavity 66 being disposed between the first cavity 64 and the central portion C of the blade.
  • At least one air intake port 68 opens into the second cavity 66 to supply air to the trailing edge circuit.
  • a plurality of communication holes 70 distributed over the entire radial height of the blade open into the second cavity 66 and open into the first cavity 64.
  • outlet orifices 72 open into the first cavity 64 and open on the underside 20 of the dawn, at the trailing edge 18.

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

Claims (12)

  1. Laufschaufel (10a, 10b, 10c, 10d) einer Turbomaschine, wobei der mittlere Teil (C) der Schaufel geometrisch in vier benachbarte vorderseitige Bereiche (Z1 bis Z4), die auf der Vorderseite der Schaufel angeordnet sind, und in vier benachbarte rückseitige Bereiche (Z5 bis Z8), die auf der Rückseite angeordnet sind, unterteilt ist, wobei die vorderseitigen und rückseitigen Bereiche auf beiden Seiten der Skelettlinie (S) der Schaufel verteilt sind, wobei jeder vorderseitige Bereich eine mit einem rückseitigen Bereich gemeinsame Seite hat, und wobei jeder rückseitige Bereich eine mit einem vorderseitigen Bereich gemeinsame Seite hat, wobei die vorderseitigen (Z1 bis Z4) und rückseitigen (Z5 bis Z8) Bereiche, welche die kleinsten Elemente bilden, einen Kühlhohlraum enthalten können, wobei die Schaufel in ihrem mittleren Teil (C) einen vorderseitigen Kühlkreis und einen rückseitigen Kühlkreis, welche voneinander unabhängig sind, umfasst, dadurch gekennzeichnet, dass der vorderseitige Kühlkreis drei radiale Hohlräume (24a bis 28a; 24b bis 26b), die drei benachbarte vorderseitige Bereiche einnehmen, umfasst, und dass der rückseitige Kühlkreis aus drei radialen Hohlräumen (30a bis 34a; 34b bis 38b; 34c bis 38c; 34d bis 38d), welche die vier rückseitigen Bereiche und den verbleibenden vorderseitigen Bereich einnehmen, besteht.
  2. Schaufel nach Anspruch 1, bei der der rückseitige Kühlkreis umfasst:
    einen ersten Hohlraum (30a; 34b) und einen zweiten Hohlraum (32a; 36b), die sich auf der Rückseite der Schaufel erstrecken,
    einen dritten Hohlraum (34a; 38b), der sich von der Vorderseite bis zur Rückseite der Schaufel erstreckt,
    eine Luftzufuhröffnung (36) an einem radialen Ende des ersten Hohlraums (30a; 34b),
    einen ersten Durchgang (38), welcher das andere radiale Ende des ersten Hohlraums (30a; 34b) mit einem benachbarten radialen Ende des zweiten Hohlraums (32a; 36b) verbindet,
    einen zweiten Durchgang (40), der das andere radiale Ende des zweiten Hohlraums (32a; 36b) mit einem benachbarten radialen Ende des dritten Hohlraums (34a; 38b) verbindet, und
    Auslassöffnungen (42a; 42b), die sich in den dritten Hohlraum (34a; 38b) öffnen und an der Vorderseite (20) der Schaufel ausmünden.
  3. Schaufel nach Anspruch 2, bei der der dritte Hohlraum (34a) des rückseitigen Kühlkreises auf der Seite der Austrittskante (18) der Schaufel angeordnet ist.
  4. Schaufel nach Anspruch 2, bei der der dritte Hohlraum (38b) des rückseitigen Kühlkreises auf der Seite der Eintrittskante (16) der Schaufel angeordnet ist.
  5. Schaufel nach Anspruch 1, bei der der rückseitige Kühlkreis umfasst:
    einen ersten Hohlraum (34c; 34d) und einen zweiten Hohlraum (36c; 36d), die sich auf der Rückseite der Schaufel erstrecken,
    einen dritten Hohlraum (38c; 38d), der sich auf der Vorderseite der Schaufel erstreckt,
    eine Luftzufuhröffnung an einem radialen Ende des ersten Hohlraums,
    einen ersten Durchgang, welcher das andere radiale Ende des ersten Hohlraums (34c; 34d) mit einem benachbarten radialen Ende des zweiten Hohlraums (36c; 36d) verbindet,
    einen zweiten Durchgang, der das andere radiale Ende des zweiten Hohlraums (36c; 36d) mit einem benachbarten radialen Ende des dritten Hohlraums (38c; 38d) verbindet, und
    Auslassöffnungen (42c; 42d), die sich in den dritten Hohlraum (38c; 38d) öffnen und an der Vorderseite (20) der Schaufel ausmünden.
  6. Schaufel nach Anspruch 5, bei der der dritte Hohlraum (38c) des rückseitigen Kühlkreises auf der Seite der Eintrittskante (16) der Schaufel angeordnet ist.
  7. Schaufel nach Anspruch 5, bei der der dritte Hohlraum (38d) des rückseitigen Kühlkreises auf der Seite der Austrittskante (18) der Schaufel angeordnet ist.
  8. Schaufel nach einem der Ansprüche 1 bis 7, bei der der vorderseitige Kühlkreis umfasst:
    einen ersten (24a; 24b), einen zweiten (26a; 26b) und einen dritten (28a; 28b) Hohlraum, die sich auf der Vorderseite der Schaufel erstrecken,
    eine Luftzufuhröffnung (44) an einem radialen Ende des ersten Hohlraums (24a; 24b),
    einen ersten Durchgang (46), welcher das andere radiale Ende des ersten Hohlraums (24a; 24b) mit einem benachbarten radialen Ende des zweiten Hohlraums (26a; 26b) verbindet,
    einen zweiten Durchgang (48), der das andere radiale Ende des zweiten Hohlraums (26a; 26b) mit einem benachbarten radialen Ende des dritten Hohlraums (28a; 28b) verbindet, und
    Auslassöffnungen (50a; 50b), die sich in den dritten Hohlraum (28a; 28b) öffnen und an der Vorderseite (20) der Schaufel ausmünden.
  9. Schaufel nach einem der Ansprüche 1 bis 8, ferner mit einem Eintrittskantenkühlkreis, der umfasst:
    einen ersten radialen Hohlraum (54), der sich in der Nähe der Eintrittskante (16) der Schaufel erstreckt,
    einen zweiten radialen Hohlraum (56) der sich von der Vorderseite bis zur Rückseite der Schaufel erstreckt, wobei der zweite Hohlraum (56) zwischen dem ersten Hohlraum (54) und dem mittleren Teil (C) der Schaufel angeordnet ist,
    wenigstens eine Luftzufuhröffnung (58), welche in den zweiten Hohlraum (56) mündet,
    eine Vielzahl von Verbindungslöchern (60), die über die gesamte radiale Höhe der Schaufel verteilt sind, sich in den zweiten Hohlraum (56) öffnen und in den ersten Hohlraum (54) münden, und
    Auslassöffnungen (62), die sich in den ersten Hohlraum (54) öffnen und an der Eintrittskante (16) sowie an den Vorder- (20) und Rückseiten (22) der Schaufel ausmünden.
  10. Schaufel nach einem der Ansprüche 1 bis 9, ferner mit einem Austrittskantenkühlkreis, der umfasst:
    einen ersten radialen Hohlraum (64), der sich in der Nähe der Austrittskante (18) der Schaufel erstreckt,
    einen zweiten radialen Hohlraum (66) der sich von der Vorderseite bis zur Rückseite der Schaufel erstreckt, wobei der zweite Hohlraum (66) zwischen dem ersten Hohlraum (64) und dem mittleren Teil (C) der Schaufel angeordnet ist,
    wenigstens eine Luftzufuhröffnung (68), welche in den zweiten Hohlraum (66) mündet,
    eine Vielzahl von Verbindungslöchern (70), die über die gesamte radiale Höhe der Schaufel verteilt sind, sich in den zweiten Hohlraum (66) öffnen und in den ersten Hohlraum (64) münden, und
    Auslassöffnungen (72), die sich in den ersten Hohlraum (64) öffnen und an der Austrittskante (18) der Schaufel ausmünden.
  11. Gasturbine, dadurch gekennzeichnet, dass sie wenigstens eine Laufschaufel (10a, 10b, 10c, 10d) nach einem der Ansprüche 1 bis 10 umfasst.
  12. Turbomaschine, dadurch gekennzeichnet, dass sie wenigstens eine Laufschaufel (10a, 10b, 10c, 10d) nach einem der Ansprüche 1 bis 10 umfasst.
EP06124041.2A 2005-11-28 2006-11-14 Turbinenschaufel umfassend einen Kühlkreislauf Active EP1790819B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0512003A FR2893974B1 (fr) 2005-11-28 2005-11-28 Circuit de refroidissement central pour aube mobile de turbomachine

Publications (2)

Publication Number Publication Date
EP1790819A1 EP1790819A1 (de) 2007-05-30
EP1790819B1 true EP1790819B1 (de) 2017-06-21

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EP06124041.2A Active EP1790819B1 (de) 2005-11-28 2006-11-14 Turbinenschaufel umfassend einen Kühlkreislauf

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Country Link
US (1) US7661930B2 (de)
EP (1) EP1790819B1 (de)
JP (1) JP4823872B2 (de)
CA (1) CA2569566C (de)
FR (1) FR2893974B1 (de)
RU (1) RU2421623C2 (de)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7862299B1 (en) * 2007-03-21 2011-01-04 Florida Turbine Technologies, Inc. Two piece hollow turbine blade with serpentine cooling circuits
US7985049B1 (en) * 2007-07-20 2011-07-26 Florida Turbine Technologies, Inc. Turbine blade with impingement cooling
WO2009016744A1 (ja) * 2007-07-31 2009-02-05 Mitsubishi Heavy Industries, Ltd. タービン用翼
US10156143B2 (en) * 2007-12-06 2018-12-18 United Technologies Corporation Gas turbine engines and related systems involving air-cooled vanes
JP5953136B2 (ja) * 2012-06-15 2016-07-20 三菱日立パワーシステムズ株式会社 ガスタービン動翼およびガスタービン、ガスタービン動翼の調整方法
KR101411347B1 (ko) 2012-11-16 2014-06-27 연세대학교 산학협력단 회전 블레이드에서 냉각성능 향상을 위한 블레이드 내부 유로 구조
US9376922B2 (en) * 2013-01-09 2016-06-28 General Electric Company Interior configuration for turbine rotor blade
WO2014163694A2 (en) * 2013-03-13 2014-10-09 Moody Jack K Trenched cooling hole arrangement for a ceramic matrix composite vane
JP5567180B1 (ja) * 2013-05-20 2014-08-06 川崎重工業株式会社 タービン翼の冷却構造
GB201314222D0 (en) 2013-08-08 2013-09-25 Rolls Royce Plc Aerofoil
FR3020402B1 (fr) * 2014-04-24 2019-06-14 Safran Aircraft Engines Aube pour turbine de turbomachine comprenant un circuit de refroidissement a homogeneite amelioree
CN106844839B (zh) * 2016-12-14 2020-01-31 中国长江动力集团有限公司 用于优化汽轮机叶片型线的方法
US10724391B2 (en) * 2017-04-07 2020-07-28 General Electric Company Engine component with flow enhancer
FR3067388B1 (fr) * 2017-04-10 2020-01-17 Safran Aube a circuit de refroidissement perfectionne
GB201806821D0 (en) 2018-04-26 2018-06-13 Rolls Royce Plc Coolant channel
FR3095834B1 (fr) * 2019-05-09 2021-06-04 Safran Aube de turbomachine à refroidissement amélioré
FR3097786B1 (fr) * 2019-06-27 2021-06-04 Safran Procede de percage d'une aube de turbomachine en fonction de la geometrie interne de l'aube et aube associee
CN112943380A (zh) * 2021-02-04 2021-06-11 大连理工大学 一种采用丁字形隔墙的回转式冷却通道涡轮叶片

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH06102963B2 (ja) * 1983-12-22 1994-12-14 株式会社東芝 ガスタ−ビン空冷翼
JPH0233843B2 (ja) * 1984-03-23 1990-07-31 Kogyo Gijutsuin Gasutaabindoyokunoreikyakukozo
US5165852A (en) * 1990-12-18 1992-11-24 General Electric Company Rotation enhanced rotor blade cooling using a double row of coolant passageways
JPH05195704A (ja) * 1992-01-22 1993-08-03 Hitachi Ltd タービン翼及びガスタービン
US5356265A (en) * 1992-08-25 1994-10-18 General Electric Company Chordally bifurcated turbine blade
US6402471B1 (en) * 2000-11-03 2002-06-11 General Electric Company Turbine blade for gas turbine engine and method of cooling same
FR2829175B1 (fr) * 2001-08-28 2003-11-07 Snecma Moteurs Circuits de refroidissement pour aube de turbine a gaz
US6981840B2 (en) * 2003-10-24 2006-01-03 General Electric Company Converging pin cooled airfoil
US7097426B2 (en) * 2004-04-08 2006-08-29 General Electric Company Cascade impingement cooled airfoil
US7217092B2 (en) * 2004-04-14 2007-05-15 General Electric Company Method and apparatus for reducing turbine blade temperatures
US7442008B2 (en) * 2004-08-25 2008-10-28 Rolls-Royce Plc Cooled gas turbine aerofoil
FR2887287B1 (fr) * 2005-06-21 2007-09-21 Snecma Moteurs Sa Circuits de refroidissement pour aube mobile de turbomachine

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US7661930B2 (en) 2010-02-16
FR2893974B1 (fr) 2011-03-18
JP4823872B2 (ja) 2011-11-24
RU2006141862A (ru) 2008-06-10
EP1790819A1 (de) 2007-05-30
RU2421623C2 (ru) 2011-06-20
JP2007146842A (ja) 2007-06-14
FR2893974A1 (fr) 2007-06-01
CA2569566A1 (fr) 2007-05-28
CA2569566C (fr) 2013-12-24
US20070122282A1 (en) 2007-05-31

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