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EP0562944A1 - Gekühlte Schaufel für eine Turbomaschine - Google Patents

Gekühlte Schaufel für eine Turbomaschine Download PDF

Info

Publication number
EP0562944A1
EP0562944A1 EP93400741A EP93400741A EP0562944A1 EP 0562944 A1 EP0562944 A1 EP 0562944A1 EP 93400741 A EP93400741 A EP 93400741A EP 93400741 A EP93400741 A EP 93400741A EP 0562944 A1 EP0562944 A1 EP 0562944A1
Authority
EP
European Patent Office
Prior art keywords
blade
orifices
dawn
channels
central line
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
EP93400741A
Other languages
English (en)
French (fr)
Other versions
EP0562944B1 (de
Inventor
Xavier Gérard André Coudray
Mischael François Louis Derrien
Philippe Marc Pierre Pichon
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0562944A1 publication Critical patent/EP0562944A1/de
Application granted granted Critical
Publication of EP0562944B1 publication Critical patent/EP0562944B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • 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
    • F05D2250/12—Two-dimensional rectangular
    • F05D2250/121—Two-dimensional rectangular square

Definitions

  • the performance of a gas turbine is closely dependent on the temperature at which the gases enter the turbine.
  • the turbine distributor vanes are obviously those which are exposed to the highest temperatures.
  • the invention relates to such a device allowing the turbine blades to withstand increased temperatures.
  • the invention therefore relates to a turbo-machine blade comprising internal recesses for the circulation of a coolant and an external wall traversed by rows of orifices connecting said internal recesses to the external environment of the blade and comprising a leading edge which has a central line, on which are located the points of tangency to the outer face of the blade of the tangents contained in the various cross sections of the blade and perpendicular to the main direction of the gas flow entering contact with the blade, and which (the leading edge) is formed by the part of said outer face of the blade immediately adjacent to this central line, which separates the upper surface from the lower surface.
  • the leading edge is provided with two first rows of orifices which extend substantially parallel to the central line, the orientations of said orifices in each row connecting a recess internal to the external environment of dawn moving away from said central line with respect to said row of orifices, each orifice of a first row of orifices being inclined with respect to a longitudinal axis of the blade which extends from the foot towards the head of the blade, the inner edge an orifice being closer to the foot of the blade than the outer edge of said orifice, so that the possible gaseous flow of cooling fluid which passes through said orifice is directed, furthermore, from the foot towards the head of the blade, the section of an orifice of a first row of orifices having an increasing value from the section (small) of the inner edge to the section (large) of the outer edge, said section of orifice having an oblong shape , so that said orifices are arranged in an angle with respect to said central line,
  • the main advantage of the blades which have just been defined lies in the possibility of exposing them to temperatures higher than those which the known blades bear, and consequently of producing new turbines whose performance is better than that of known turbines.
  • the various blades shown each have a longitudinal axis AB which, when said blade is fixed in its blade, has a substantially radial direction.
  • the letter A of the axis AB corresponds to the dawn fixing foot, and the letter B corresponds to the head of the dawn.
  • the blade shown in FIGS. 1 to 8 comprises a face 1 delimiting the lower surface and a face 2 delimiting the upper surface of the blade, separated by the leading edge of the blade.
  • F being the general direction of flow of the gas flow outside the blade
  • a direction G contained in each cross section of the blade perpendicular to the axis AB, orthogonal to the direction F of the gas flow, is tangent to the curve defining said cross section of the blade on a line 3 substantially parallel to the axis AB.
  • Line 3 is the center line of the leading edge.
  • the blade is hollowed out and comprises an external wall 4 and a first internal wall 5 which connects the two parts distant from each other of the external wall 4 delimiting the lower surface 1 and the upper surface 2, the internal wall 5 being located near the edge attack 3 and delimiting inside the blade a first chamber 6A communicating with a stack of lamellas 6B spaced from each other and arranged substantially perpendicular to the axis AB.
  • the lower part of the chamber 6A further communicates with a refrigerant inlet.
  • the leading edge is constituted by two zones of small widths, situated on either side of the central line 3, in which are formed two first rows of orifices 81 and 82 which pass through the external wall 4.
  • the orifices 81 are located in the part of the external wall which delimits the lower surface 1, the orifices 82 being situated in the part of the external wall which delimits the upper surface 2, each first row of the orifices 81 and orifices 82 extending substantially parallel to the axis AB and to the central line 3.
  • the orifices 91 are located in the part of the external wall delimiting the lower surface 1, the orifices 92 being located in the part of the external wall delimiting the upper surface 2.
  • longitudinal internal walls 10, 11, 12 extend perpendicular to the lower surface 1.
  • longitudinal external walls 13, 14, 15, 16 and 17 extend perpendicular to the upper surface 2.
  • An attached inner wall 18 is welded to the edges of the various internal walls 10, 11, 12, 13, 14, 15, 16 and 17, as well as the internal wall 5, defines with the external wall 4 longitudinal channels 110 between the internal walls 10 and 11; 111 between the internal walls 11 and 12; 112, between the internal walls 12 and 5; 113 between the internal walls 13 and 14; 114 between the internal walls 14 and 15; 115 between the internal walls 15 and 16; 116 between the internal walls 16 and 17; a first longitudinal cavity 19 with which the orifices 81, 82, 91 and 92 communicate, and a second longitudinal cavity 20.
  • the walls 10, 11, 12 are in one piece with the part of the external wall 4 delimiting the lower surface 1, the walls 13, 14, 15, 16 and 17 being integral with the part of the external wall 4 delimiting the upper surface 2.
  • Each orifice 81 has a double orientation.
  • the axis A 81 of this orifice 81 is first oriented obliquely with respect to the direction G and, oriented from the first cavity 19 towards the outside of the blade, departs from the central line 3 with respect to the first row of the orifices 81.
  • the axis A 81 is furthermore oblique with respect to the direction of the longitudinal axis AB, having a component oriented from the foot A towards the head B of dawn.
  • the orifice 81 opens into the interior of the cavity 19 by an inner edge 81 A and outside the blade by an outer edge 81 B, of similar shape but greater than the shape of the inner edge 81, the inner edge 81 A being located below the outer edge 81 B. Furthermore, in the embodiment shown, the cross section of an orifice 81 increases from the inner edge 81 A to the outer edge 81 B. A point of the upper edge homologous to a point of the lower edge is further from the foot of the dawn than said point of the lower edge: in other words, the axis A 81 does indeed have a parallel component and in the same direction as the longitudinal axis AB.
  • each orifice 82 has a double orientation.
  • the axis A 82 of this orifice 82 is first oriented obliquely relative to the direction G and, oriented from the first cavity 19 towards the outside of the blade, departs from the central line 3 with respect to the first row of the orifices 82.
  • the axis A 82 is also oblique with respect to the direction of the longitudinal axis AB, having an oriented component of the foot A towards head B of dawn.
  • the orifice 82 opens into the interior of the cavity 19 by an inner selvedge 82 A and outside the blade by an outer selvedge 82 B, of similar shape but greater than the shape of the inner selvedge 82 A, the inner edge 82 A being below the outer edge 82 B. Furthermore, in the embodiment shown, the cross section of an orifice 82 increases from the inner edge 82 A to the outer edge 82 B. A point of the upper edge homologous to a point of the lower edge is further from the foot of the dawn than said point of the lower edge: in other words, the axis A 82 does indeed have a parallel component and in the same direction as the longitudinal axis AB.
  • the second orientations of the axes A 81 and A 82 having components parallel to the axis AB could also alternatively be oriented from the head B towards the foot A of the dawn.
  • the axes A 81 and A 82 are orthogonal to the axis AB.
  • the cavity 19, as well as the channels 110, 111, 112, 113, 114, 115, 116 are supplied with a refrigerant under pressure, via a fluid inlet located either in the area of foot A of dawn, or in the area of head B of dawn.
  • the choice of the second orientations of the axes A 81 and A 82, with components parallel to the axis AB naturally depends in particular on the choice of the admission of the coolant in the zone of the foot or in the zone of the head of the blade .
  • the section of an orifice 81, as well as that of an orifice 82, may each be constant between the inner edge 81 A, 82 A and the outer edge 81 B, 82 B.
  • Each of the orifices 91, 92 is constituted by an elongated slot substantially parallel to the longitudinal axis AB.
  • the holes 91 are aligned on the same straight line, the holes 92 also being.
  • the channel 114 adjacent to the channel 113 closest to the orifices 92 communicates, on the one hand with the first longitudinal cavity 19 by orifices 21, on the other hand with the outside of the blade, on the upper surface, by holes 22.
  • the channel 113 closest to the orifices 92 and the channel 110 closest to the orifices 91 are both fitted with devices, such as turbulence-promoting disrupters of the circulation of the refrigerant.
  • the second longitudinal cavity 20 communicates with the outside of the blade, on the upper surface, through orifices 23. Furthermore, the channels 110, 111, 112, 113, 115, 116, on the one hand, are connected to their ends closest to the foot of the blade (A) to a supply 24 of coolant, on the other hand open at their ends closest to the head (B) of the blade in the second longitudinal cavity 20 ( arrows H in figure 8).
  • the cavity 19 is also provided with an inlet in the area of the foot A of the dawn.
  • the channels 110 to 116, and the cavity 19 can be supplied with coolant via an inlet 24 which, this time is located in the region of the head B of the blade, the channels opening into the second cavity 20 at their ends closest to the foot A of the blade, as shown in FIG. 9.
  • the axes A 91, A 92 of the orifices 91, 92 substantially contained in transverse sections of the blade, perpendicular to the axis AB, have components oriented in the directions away from the leading edge (or orifices 81, 82 which pass through the wall).
  • the blade of FIG. 10 comprises only the two rows of orifices 81, 82, which communicate with the first longitudinal cavity 19.
  • a removable jacket 39 is introduced inside the blade and, in cooperation with small walls monoblock longitudinal with the outer wall 4, with which it is in sealed contact, defines longitudinal channels 124, 125, 126, 127, 128, 129, 130, 131, 132, 133, 134, 135, 136, 137, 138, as well as inside the second longitudinal cavity 20.
  • Holes 25 pass through the wall of the jacket 39 and the external wall 4 and put the second longitudinal cavity 20 into communication with the outside of the blade.
  • first longitudinal cavity 19, as well as the channels 124 to 138 are connected, by their ends close to the foot of the blade (A) to an inlet 24 for refrigerant. Furthermore, at their ends close to the head B of the blade, the channels 124 to 138 communicate with the second longitudinal cavity 20 (arrows J in FIG. 11).
  • a third longitudinal cavity 26, delimited by a part of the external wall 4 delimiting the upper surface 2 and by an internal wall 27, which separates this third cavity 26 from the first longitudinal cavity 19, is connected to the intake.
  • 24 of refrigerant, in the area of the foot A of the blade, and in the area close to the head B of the blade communicates with the second cavity 20 (FIG. 13).
  • FIG. 12 shows such a variant, in which the intake refrigerant in the various channels 124 to 138 (and, in the third cavity 26) is produced in the area of the head B of the blade, said channels and the third cavity 26 communicating (arrows J) in the area of the foot At dawn, with the second cavity 20.
  • the choice between admitting coolant at the head or at the foot of the blade is made, in particular, taking into account the orientation (direction AB, or, direction BA) axes of the orifices 81, 82.
  • the outer wall 4 of the blade of FIGS. 1 to 8 is well refrigerated and is therefore able to be exposed to very high temperatures, this ability being one of the conditions for obtaining a turbo-machine having high performance and efficiency.
  • the cooling of the wall 4, at the places most exposed to high temperatures, in the area of the leading edge, lower side 1 and upper side 2, is provided first by the films of the refrigerant which has passed through the orifices 81 , 82, and is supplemented, in the embodiment of FIGS. 1 to 8, by the films of the coolant coming from the orifices 91, 92.
  • the orientations of the axes A 81 and A 82 of the orifices 81, 82 allow, on the one hand to direct the coolant towards the lower surface 1 and the upper surface 2, respectively, on the other hand to cover with a film of this coolant all the faces of the lower surface and the upper surface from the foot A of the dawn to the head B of the dawn, or, in the variant of FIG. 9, from the head to the foot of the dawn.
  • the zones located beyond the orifices 81, 82, 91, 92 of FIGS. 1 to 8, or only 81, 82 of FIG. 10, are cooled by the circulation of the refrigerant fluid in the channels 110, 111, 112, 113, 115, 116 or 124 to 138.
  • This fluid is still able, after passing through the second longitudinal cavity 20, escaping through the orifices 23 in FIG. 2, or 25 in FIG. 10, to constitute a cooling film of the part of the upper surface 2 substantially opposite the leading edge.
  • the fluid which passes through the orifices 22 produces an effective cooling film in an area of the upper surface 2 partly substantially parallel to the direction F of the general flow of the gas flow.
  • the devices promoting turbulence in the circulation of the refrigerant gives this fluid time to effectively cool these areas of the outer wall 4 closest to the leading edge, particularly exposed to the high temperatures of hot gases.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP93400741A 1992-03-25 1993-03-23 Gekühlte Schaufel für eine Turbomaschine Expired - Lifetime EP0562944B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9203583 1992-03-25
FR9203583A FR2689176B1 (fr) 1992-03-25 1992-03-25 Aube refrigeree de turbo-machine.

Publications (2)

Publication Number Publication Date
EP0562944A1 true EP0562944A1 (de) 1993-09-29
EP0562944B1 EP0562944B1 (de) 1996-05-15

Family

ID=9428058

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93400741A Expired - Lifetime EP0562944B1 (de) 1992-03-25 1993-03-23 Gekühlte Schaufel für eine Turbomaschine

Country Status (4)

Country Link
US (1) US5342172A (de)
EP (1) EP0562944B1 (de)
DE (1) DE69302614T2 (de)
FR (1) FR2689176B1 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995015430A1 (en) * 1993-11-30 1995-06-08 United Technologies Corporation Airfoil having coolable leading edge region
FR2715693A1 (fr) * 1994-02-03 1995-08-04 Snecma Aube fixe ou mobile refroidie de turbine.
WO1995031631A1 (en) * 1994-05-16 1995-11-23 Solar Turbines Incorporated Low thermal stress ceramic turbine nozzle
EP0785339A1 (de) 1996-01-04 1997-07-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Gekühlte Turbinenleitschaufel
US6050777A (en) * 1997-12-17 2000-04-18 United Technologies Corporation Apparatus and method for cooling an airfoil for a gas turbine engine
US6264428B1 (en) 1999-01-21 2001-07-24 Rolls-Royce Plc Cooled aerofoil for a gas turbine engine
EP1898051A3 (de) * 2006-08-25 2013-05-15 Alstom Technology Ltd Gasturbinenschaufel mit Kühlung der Leitkante
FR3067390A1 (fr) * 2017-04-10 2018-12-14 Safran Aube de turbine presentant une structure amelioree

Families Citing this family (49)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2310896A (en) * 1996-03-05 1997-09-10 Rolls Royce Plc Air cooled wall
US5772397A (en) * 1996-05-08 1998-06-30 Alliedsignal Inc. Gas turbine airfoil with aft internal cooling
US5601399A (en) * 1996-05-08 1997-02-11 Alliedsignal Inc. Internally cooled gas turbine vane
US5779437A (en) * 1996-10-31 1998-07-14 Pratt & Whitney Canada Inc. Cooling passages for airfoil leading edge
US6004100A (en) * 1997-11-13 1999-12-21 United Technologies Corporation Trailing edge cooling apparatus for a gas turbine airfoil
JPH11336503A (ja) * 1998-05-27 1999-12-07 Mitsubishi Heavy Ind Ltd 蒸気タービン静翼
US6099251A (en) * 1998-07-06 2000-08-08 United Technologies Corporation Coolable airfoil for a gas turbine engine
US6164912A (en) * 1998-12-21 2000-12-26 United Technologies Corporation Hollow airfoil for a gas turbine engine
US6126397A (en) * 1998-12-22 2000-10-03 United Technologies Corporation Trailing edge cooling apparatus for a gas turbine airfoil
US6102658A (en) * 1998-12-22 2000-08-15 United Technologies Corporation Trailing edge cooling apparatus for a gas turbine airfoil
US6247896B1 (en) 1999-06-23 2001-06-19 United Technologies Corporation Method and apparatus for cooling an airfoil
US6174135B1 (en) * 1999-06-30 2001-01-16 General Electric Company Turbine blade trailing edge cooling openings and slots
KR20010020925A (ko) 1999-08-11 2001-03-15 제이 엘. 차스킨, 버나드 스나이더, 아더엠. 킹 가동성 노즐 리브를 갖는 노즐 날개
US6257831B1 (en) 1999-10-22 2001-07-10 Pratt & Whitney Canada Corp. Cast airfoil structure with openings which do not require plugging
US6406260B1 (en) 1999-10-22 2002-06-18 Pratt & Whitney Canada Corp. Heat transfer promotion structure for internally convectively cooled airfoils
US6280140B1 (en) 1999-11-18 2001-08-28 United Technologies Corporation Method and apparatus for cooling an airfoil
US6478535B1 (en) * 2001-05-04 2002-11-12 Honeywell International, Inc. Thin wall cooling system
GB0114503D0 (en) * 2001-06-14 2001-08-08 Rolls Royce Plc Air cooled aerofoil
JP4798416B2 (ja) * 2001-08-09 2011-10-19 株式会社Ｉｈｉ タービン翼部品
US6599092B1 (en) 2002-01-04 2003-07-29 General Electric Company Methods and apparatus for cooling gas turbine nozzles
US6602047B1 (en) 2002-02-28 2003-08-05 General Electric Company Methods and apparatus for cooling gas turbine nozzles
US6932570B2 (en) * 2002-05-23 2005-08-23 General Electric Company Methods and apparatus for extending gas turbine engine airfoils useful life
US6746209B2 (en) 2002-05-31 2004-06-08 General Electric Company Methods and apparatus for cooling gas turbine engine nozzle assemblies
FR2858352B1 (fr) * 2003-08-01 2006-01-20 Snecma Moteurs Circuit de refroidissement pour aube de turbine
US6923616B2 (en) * 2003-09-02 2005-08-02 General Electric Company Methods and apparatus for cooling gas turbine engine rotor assemblies
US7600972B2 (en) * 2003-10-31 2009-10-13 General Electric Company Methods and apparatus for cooling gas turbine engine rotor assemblies
US6984112B2 (en) * 2003-10-31 2006-01-10 General Electric Company Methods and apparatus for cooling gas turbine rotor blades
US7371048B2 (en) * 2005-05-27 2008-05-13 United Technologies Corporation Turbine blade trailing edge construction
US7220934B2 (en) * 2005-06-07 2007-05-22 United Technologies Corporation Method of producing cooling holes in highly contoured airfoils
US7510367B2 (en) * 2006-08-24 2009-03-31 Siemens Energy, Inc. Turbine airfoil with endwall horseshoe cooling slot
US7597540B1 (en) * 2006-10-06 2009-10-06 Florida Turbine Technologies, Inc. Turbine blade with showerhead film cooling holes
US7669425B2 (en) * 2006-10-25 2010-03-02 Siemens Energy, Inc. Closed loop turbine cooling fluid reuse system for a turbine engine
US7806658B2 (en) * 2006-10-25 2010-10-05 Siemens Energy, Inc. Turbine airfoil cooling system with spanwise equalizer rib
GB2466791B (en) * 2009-01-07 2011-05-18 Rolls Royce Plc An aerofoil
US9422816B2 (en) * 2009-06-26 2016-08-23 United Technologies Corporation Airfoil with hybrid drilled and cutback trailing edge
US8511994B2 (en) * 2009-11-23 2013-08-20 United Technologies Corporation Serpentine cored airfoil with body microcircuits
EP2392775A1 (de) * 2010-06-07 2011-12-07 Siemens Aktiengesellschaft Rotationsschaufel zur Verwendung in einem Fluidstrom einer Turbine und zugehörige Turbine
CA2867960A1 (en) * 2012-03-22 2013-09-26 Alstom Technology Ltd. Turbine blade
US9322279B2 (en) * 2012-07-02 2016-04-26 United Technologies Corporation Airfoil cooling arrangement
CA2880540A1 (en) * 2012-08-06 2014-02-13 General Electric Company Rotating turbine component with preferential hole alignment
JP6230383B2 (ja) * 2013-11-21 2017-11-15 三菱日立パワーシステムズ株式会社 蒸気タービンの静翼と蒸気タービン
US9708915B2 (en) * 2014-01-30 2017-07-18 General Electric Company Hot gas components with compound angled cooling features and methods of manufacture
US9963982B2 (en) * 2014-09-08 2018-05-08 United Technologies Corporation Casting optimized to improve suction side cooling shaped hole performance
US10208602B2 (en) * 2015-04-27 2019-02-19 United Technologies Corporation Asymmetric diffuser opening for film cooling holes
US10364681B2 (en) 2015-10-15 2019-07-30 General Electric Company Turbine blade
US10731474B2 (en) * 2018-03-02 2020-08-04 Raytheon Technologies Corporation Airfoil with varying wall thickness
US10753210B2 (en) * 2018-05-02 2020-08-25 Raytheon Technologies Corporation Airfoil having improved cooling scheme
JP7293011B2 (ja) * 2019-07-10 2023-06-19 三菱重工業株式会社 蒸気タービン用静翼、蒸気タービン及び蒸気タービン用静翼の加熱方法
FR3099522B1 (fr) * 2019-07-30 2021-08-20 Safran Aircraft Engines Aube mobile de turbomachine à circuit de refroidissement ayant une double rangée de fentes d’évacuation

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1601730A (de) * 1965-08-26 1970-09-14
DE1601561A1 (de) * 1966-02-26 1970-12-17 Gen Electric Gekuehlte Schaufel fuer mit hohen Temperaturen arbeitendes Turbinentriebwerk
GB2066372A (en) * 1979-12-26 1981-07-08 United Technologies Corp Coolable wall element
US4653983A (en) * 1985-12-23 1987-03-31 United Technologies Corporation Cross-flow film cooling passages
GB2184492A (en) * 1985-12-23 1987-06-24 United Technologies Corp Film cooled vanes for turbines
WO1989001564A1 (en) * 1987-08-06 1989-02-23 United Technologies Corporation Airfoil with nested cooling channels
EP0473991A2 (de) * 1990-09-04 1992-03-11 Westinghouse Electric Corporation Gasturbine mit gekühlten Schaufeln

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3533711A (en) * 1966-02-26 1970-10-13 Gen Electric Cooled vane structure for high temperature turbines
GB1565361A (en) * 1976-01-29 1980-04-16 Rolls Royce Blade or vane for a gas turbine engien
NO811831L (no) * 1980-06-05 1981-12-07 United Technologies Corp Tupphette for rotorblader.
JPS5851202A (ja) * 1981-09-24 1983-03-25 Hitachi Ltd ガスタ−ビンのタ−ビン翼前縁部の冷却装置
GB2121483B (en) * 1982-06-08 1985-02-13 Rolls Royce Cooled turbine blade for a gas turbine engine
FR2678318B1 (fr) * 1991-06-25 1993-09-10 Snecma Aube refroidie de distributeur de turbine.

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1601730A (de) * 1965-08-26 1970-09-14
DE1601561A1 (de) * 1966-02-26 1970-12-17 Gen Electric Gekuehlte Schaufel fuer mit hohen Temperaturen arbeitendes Turbinentriebwerk
GB2066372A (en) * 1979-12-26 1981-07-08 United Technologies Corp Coolable wall element
US4653983A (en) * 1985-12-23 1987-03-31 United Technologies Corporation Cross-flow film cooling passages
GB2184492A (en) * 1985-12-23 1987-06-24 United Technologies Corp Film cooled vanes for turbines
WO1989001564A1 (en) * 1987-08-06 1989-02-23 United Technologies Corporation Airfoil with nested cooling channels
EP0473991A2 (de) * 1990-09-04 1992-03-11 Westinghouse Electric Corporation Gasturbine mit gekühlten Schaufeln

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 7, no. 137 (M-222)(1282) 15 Juin 1983 & JP-A-58 051 202 ( HITACHI ) 25 Mars 1983 *

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995015430A1 (en) * 1993-11-30 1995-06-08 United Technologies Corporation Airfoil having coolable leading edge region
FR2715693A1 (fr) * 1994-02-03 1995-08-04 Snecma Aube fixe ou mobile refroidie de turbine.
EP0666406A1 (de) * 1994-02-03 1995-08-09 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Gekühltes Turbinenschaufel
US5496151A (en) * 1994-02-03 1996-03-05 Societe Nationale D'etude Et De Construction De Moteures D'aviation "Snecma" Cooled turbine blade
WO1995031631A1 (en) * 1994-05-16 1995-11-23 Solar Turbines Incorporated Low thermal stress ceramic turbine nozzle
US5772398A (en) * 1996-01-04 1998-06-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Cooled turbine guide vane
EP0785339A1 (de) 1996-01-04 1997-07-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Gekühlte Turbinenleitschaufel
US6050777A (en) * 1997-12-17 2000-04-18 United Technologies Corporation Apparatus and method for cooling an airfoil for a gas turbine engine
US6264428B1 (en) 1999-01-21 2001-07-24 Rolls-Royce Plc Cooled aerofoil for a gas turbine engine
EP1898051A3 (de) * 2006-08-25 2013-05-15 Alstom Technology Ltd Gasturbinenschaufel mit Kühlung der Leitkante
FR3067390A1 (fr) * 2017-04-10 2018-12-14 Safran Aube de turbine presentant une structure amelioree
WO2018189434A3 (fr) * 2017-04-10 2018-12-20 Safran Aube de turbine présentant une structure améliorée
US11073025B2 (en) 2017-04-10 2021-07-27 Safran Turbine blade having an improved structure

Also Published As

Publication number Publication date
EP0562944B1 (de) 1996-05-15
FR2689176B1 (fr) 1995-07-13
DE69302614D1 (de) 1996-06-20
FR2689176A1 (fr) 1993-10-01
DE69302614T2 (de) 1996-11-28
US5342172A (en) 1994-08-30

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