EP1840331A1 - Einheit aus einer Laufradschaufel und einem Kühlmantel, Leitrad einer Strömungsmaschine, die diese Einheit umfasst, sowie Verfahren zur Montage und Reparatur dieser Einheit - Google Patents

Einheit aus einer Laufradschaufel und einem Kühlmantel, Leitrad einer Strömungsmaschine, die diese Einheit umfasst, sowie Verfahren zur Montage und Reparatur dieser Einheit Download PDF

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Publication number
EP1840331A1
EP1840331A1 EP07290365A EP07290365A EP1840331A1 EP 1840331 A1 EP1840331 A1 EP 1840331A1 EP 07290365 A EP07290365 A EP 07290365A EP 07290365 A EP07290365 A EP 07290365A EP 1840331 A1 EP1840331 A1 EP 1840331A1
Authority
EP
European Patent Office
Prior art keywords
flange
blade
opening
liner
wall
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
EP07290365A
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English (en)
French (fr)
Other versions
EP1840331B1 (de
Inventor
Alexandre Dervaux
Olivier Jean Daniel Baumas
Jean-Luc Bacha
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1840331A1 publication Critical patent/EP1840331A1/de
Application granted granted Critical
Publication of EP1840331B1 publication Critical patent/EP1840331B1/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
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • the invention relates to a set of a blade and a cooling jacket of the blade, in a distributor of a turbomachine.
  • a turbomachine comprises rotor stages - compressor and / or turbine - separated by distributors.
  • the latter comprise a plurality of vanes, intended to guide the flow of gas.
  • the vanes extend in the gas vein between an outer shell and an inner shell. Due to the temperature of the gases flowing through them, in particular in the distributors separating the turbine stages, the vanes are subjected to very severe operating conditions; it is therefore necessary to cool them, usually by forced convection or by air impact, inside the blades.
  • multi-perforated longitudinal liners can be used. These jackets are generally made of a hot-resistant alloy, for example based on Chromium (Cr), Cobalt (Co) and Nickel (Ni).
  • Cr Chromium
  • Co Cobalt
  • Ni Nickel
  • Such a shirt is slid longitudinally into the cavity of a blade. It is supplied with cooling air at the outer shell. Due to the pressure difference between the inner cavity of the liner and the cavity between the liner and the blade, a portion of the air is projected, via the perforations of the liner, against the inner wall of the liner. dawn, thus ensuring its cooling. This air is then evacuated along the trailing edge of the blade by calibrated perforations in the gas vein. The remainder of the air is discharged through the inner shroud to other parts of the engine to be cooled, such as the turbine disk or bearings.
  • the dawn cavity provides two openings in the inner and outer platforms.
  • the liner is generally attached externally to the wall of the outer opening by soldering or welding, for example. This gives a kind of brazed slide connection.
  • the liner is further guided, at its other end portion, in the inner opening, whose wall slid form for this purpose and which makes it possible to compensate for the differential expansions between the liner and the blade.
  • the jacket comprises, on its external side, a flange, brazed on the dispenser.
  • a collared shirt is known from the document US 2002/0028133 . Compared to the shirts whose outer portion is brazed at a slide, a collarless shirt presents various advantages: it allows a simple mounting of the liner in the blade, with a determined radial positioning, and the brazing of the collar on the distributor is easy to implement and can be visually controlled.
  • Such a connection can be obtained by brazing.
  • brazing can be visually controlled on the flange, there is a risk of incomplete or failed brazing, leaving room for a possible air leak.
  • the present invention aims to provide an assembly of a blade and a cooling collar jacket of the blade in which the sealing of the fastener at the collar is provided.
  • the invention relates to a set of a blade and a cooling jacket of the blade, here in a distributor of a turbomachine, the blade having a central cavity, with at least a first opening , in which the liner extends, the liner comprising a flange fixed to the rim of the opening, characterized in that it comprises, at proximity of the flange, a peripheral interposition element between the wall of the jacket and the wall of the opening.
  • Such an interposition element creates a pressure drop.
  • loss of load is meant not only a conventional pressure loss created by a narrowing of the passage section of a flow or a baffle, but also an pressure drop - infinite - created by a seal.
  • the applicant has also discovered that it was possible to greatly simplify the assembly of the assembly. Indeed, the presence of an interposing element near the collar has a very effective effect on air leakage, so it is no longer necessary to perfectly braze the flange on the distributor. It is therefore possible to simply fix, by spot welding between the flange and the flange, the jacket on the blade, the leaks being avoided thanks to the interposing element. The time and cost savings are considerable in comparison with soldering over the entire periphery of the collar.
  • the interposer may serve a baffle and / or seal function.
  • the liner has an end portion, opposite the flange, which is guided in the second opening, the wall forming a slide for this purpose.
  • a clearance is provided between the jacket and the wall of the first opening.
  • the interposing element comprises a peripheral ring forming a baffle.
  • the interposing element comprises an elastic lamella.
  • the interposing element comprises a peripheral spring.
  • the invention also relates to a turbomachine distributor, comprising a plurality of assemblies as presented above, and a turbomachine comprising such a distributor.
  • Such a method has the advantage of its simplicity of implementation.
  • the invention is particularly applicable to an assembly whose jacket is open on both sides, the end portion opposite the flange being guided in an opening whose wall form slider, but it goes without saying that the The invention also applies to an assembly whose jacket is open only on the side of the collar, without necessarily being guided in a slide at its other end.
  • a distributor 1 comprises a plurality of stationary blades 2, forming a grid that straighten the flow of air passing through the gas stream of the engine.
  • the arrow in Figure 2 shows the flow direction of the gas, from upstream to downstream. This vein is delimited by an outer shell 3 and an inner shell 4, supporting the blades 2.
  • Each blade 2 is hollow and comprises a central cavity 5 within which is inserted a cooling jacket 6.
  • the leftmost cooling jacket 6 has been shown partially out of the cavity 5 of its blade 2 reception, to help understand the shape of the various elements. We will describe later a particular set of a dawn 2 and a jacket 6, it being understood that all the sets 2, 6 of the distributor 1 are similar in their structure.
  • the cavity 5 of the blade 2 has an external opening 7 and an internal opening 8, respectively in the outer and inner ring 3 4 of the distributor.
  • the jacket 6 is inserted through the external opening 7.
  • the jacket 6 comprises a hollow body 9 pierced, here on the upstream side, with a plurality of orifices 10 through which is projected, against the inner wall of the blade 2, air fed into the body 9 of the jacket 6 at a supply pipe 11 located near the outer opening 7 of the blade 2.
  • the inner wall of the blade 2 comprises, facing these orifices 10, a plurality of disruptive fins 11, for better cooling of the blade 2, in known manner.
  • the liner 6 further includes, on its outer surface, a plurality of bosses 12 - also shown schematically in Figure 2, although the latter is in section - whose function is to allow the positioning of the liner 2 in the cavity 5 of dawn 2.
  • the liner 6 comprises, on the external side, a flange 13.
  • This flange 13 is here obtained by forming the sheet forming the liner 6. It could also be reported on the latter.
  • the flange 13 is arranged to bear on the flange 14 formed by the distributor around the outer opening 7 formed by the cavity 5 of the blade 2.
  • the flange 13 is fixed to this rim 14, by soldering or welding, as will be detailed below.
  • the liner 6 On its internal side, the liner 6 comprises an end portion 15, in the extension of its body 6, inserted into the internal opening 8 formed by the blade 2, whose wall 8 'slider form to guide this portion of end 15, in known manner. Due to this freedom of movement, the differences in thermal expansion between the blade 2 and the liner 6 can be absorbed.
  • the assembly of the blade 2 and the liner 6 further includes, near the collar 13, an interposing element 16.
  • the function of the interposing element 16 is to create a pressure drop in the vicinity collar 13, to avoid or at least limit air leakage, in one direction or the other.
  • This interposing element 16 is peripheral around the jacket 6. It can be secured to either the jacket 6 or the distributor 1. It is located at close to the flange 13, that is to say that it is in an area in which its effects can be combined with those of the collar 13. In other words, the pressure losses generated by the interposition element 16 must be sufficient to prevent air leakage through the possible gaps between the flange 13 and the flange 14. In this case, the interposing element 16 is located, under the flange 13, at the wall 7 'of the external opening 7, which is extended by the flange 14 where the flange 13 is fixed.
  • the interposition element 16 is shown integral with the jacket 6, but It goes without saying that the skilled person will transpose without difficulty to an interposing element 16 secured to the wall 7 'of the outer opening 7 formed by the blade 2. In the three figures, the interposing element is designated by the same reference 16.
  • the interposition element 16 comprises, according to a first embodiment, a peripheral ring 16, or peripheral strip, fixed around the jacket 6, under the collar 13.
  • This ring 16, metallic is arranged to extend radially to a distance less than that separating the wall of the liner 16 from the wall 7 'of the outer opening 7 at this point, preferably flush with the latter.
  • radially is meant radially with respect to the overall axis of the liner, that is to say with respect to its longitudinal direction between the flange 13 and the end portion 15. The pressure loss thus created is sufficient to avoid or limit satisfactorily leaks between the flange 13 and the flange 14.
  • the interposing element forms a baffle, for the air flows, over the entire periphery of the jacket 6.
  • the interposing element 16 comprises, according to a second embodiment, a strip 16 peripheral, having a certain elasticity.
  • This lamella 16, metal has a radial dimension which may possibly be greater than the average distance between the wall of the liner 6 of the wall 7 'of the outer opening 7 at this location.
  • the sipe 16 bears on the wall portions 7 ' of opening 7 whose shirt 6 is closer and elastically bends outwards during the introduction of the liner 6, thus compensating for the play. It may also be provided that the dimension of the sipe 16 is such that the sipe comes into contact with the wall 7 'of the opening 7 over the entire periphery of the liner 6, thereby forming a seal.
  • the interposing element 16 can either perform the function of a baffle, or perform the function of a seal, or both, depending on whether it touches the wall 7 'of external opening 7 (seal function) or not touching it (baffle function). In all cases, it induces a loss of load at its level.
  • the sealing element 16 fills on certain portions - where the strip 16 is not in contact with the wall 7 'of the opening 7 - a baffle function and on others portions - where the blade 16 is in contact with the wall 7 'of the opening 7 - a seal function.
  • the interposing element 16 comprises, according to a third embodiment, a peripheral spring 16.
  • This spring 16 made of metal, comprises a lamella, the edges of which are fixed to the surface of the jacket 6 , the slat having a U-shaped section flared between the two fixed edges.
  • a spring member 16 compensates for a possible play at the outer opening 7 and may, depending on the areas of the jacket 6, perform a seal function and / or baffle, depending on whether the spring 16 is in contact or not with the wall 7 'of the opening 7.
  • interposing element has been presented according to three preferred embodiments, but it goes without saying that it is possible to envisage other structures, insofar as they extend between the wall of the jacket 6 and that of the opening 7 to create a pressure drop. We could also combine several elements of interposition and create a kind of labyrinth seal.
  • Such a mounting method is very fast and inexpensive. Indeed, instead of being soldered over its entire circumference, the collar 13 is simply welded in a plurality of points (usually referred to as "pointing").
  • the assembly is viable in operation because the weld points are sufficient to ensure the holding of the liner 6 on the blade 2, while the interposing element 16 seals or at least the limitation of leaks at the It should be noted that the point-welding fastening between the liner 6 and the flange 14 is sufficiently strong because the mechanical stresses at the level of a distributor liner are not too great.
  • the method of attachment can freely be adapted according to mechanical constraints on the one hand, time constraints and mounting cost on the other hand.
  • This freedom of adaptation is conferred by the presence of an interposing element between the wall of the liner 6 and the wall 7 'of the opening 7, which makes it possible to choose between brazing and spot welding.
  • the step of leveling the flange 13 may be implemented by machining, or preferably by ripping by an EDM machine (this type of routing is well known to those skilled in the art under its English acronym EDM, meaning "Electro-Discharge Machine”).
  • EDM Electro-Discharge Machine
  • the routing to be operated is very quickly implemented, because it suffices to break down the flange 13, which does not have, in general, a very large thickness. It is simple then, once the liner 6 removed from the central cavity 5 of the blade 2, to report a flange on the body 9 of the liner 6, for example by welding, to reform a new liner. The latter can then be inserted again in the central cavity 5 of the blade 2.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP07290365.1A 2006-03-29 2007-03-26 Turbomachinendüse Active EP1840331B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0602716A FR2899271B1 (fr) 2006-03-29 2006-03-29 Ensemble d'une aube et d'une chemise de refroidissement, distributeur de turbomachine comportant l'ensemble, turbomachine, procede de montage et de reparation de l'ensemble

Publications (2)

Publication Number Publication Date
EP1840331A1 true EP1840331A1 (de) 2007-10-03
EP1840331B1 EP1840331B1 (de) 2017-05-31

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ID=37429322

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07290365.1A Active EP1840331B1 (de) 2006-03-29 2007-03-26 Turbomachinendüse

Country Status (7)

Country Link
US (1) US7819628B2 (de)
EP (1) EP1840331B1 (de)
JP (1) JP2007263115A (de)
CN (1) CN101122243B (de)
CA (1) CA2582638C (de)
FR (1) FR2899271B1 (de)
RU (1) RU2439334C2 (de)

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* Cited by examiner, † Cited by third party
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FR2955145A1 (fr) * 2010-01-14 2011-07-15 Snecma Distributeur de turbine haute pression d'un turboreacteur
FR2976616A1 (fr) * 2011-06-17 2012-12-21 Snecma Systeme de ventilation pour une pale creuse d un distributeur de turbine dans une turbomachine
EP2613004A3 (de) * 2012-01-09 2017-06-28 General Electric Company Leitschaufelnmontageverfahren
WO2023012421A1 (fr) * 2021-08-05 2023-02-09 Safran Aircraft Engines Chemise de refroidissement de pale creuse de distributeur

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2919897B1 (fr) * 2007-08-08 2014-08-22 Snecma Secteur de distributeur de turbine
FR2970666B1 (fr) 2011-01-24 2013-01-18 Snecma Procede de perforation d'au moins une paroi d'une chambre de combustion
EP2540969A1 (de) 2011-06-27 2013-01-02 Siemens Aktiengesellschaft Aufprallkühlung von Turbinenschaufeln oder -flügeln
US9011079B2 (en) * 2012-01-09 2015-04-21 General Electric Company Turbine nozzle compartmentalized cooling system
US20130223987A1 (en) * 2012-02-29 2013-08-29 Scott Stafford Turbine Nozzle Insert
US20140356155A1 (en) * 2013-06-03 2014-12-04 General Electric Company Nozzle Insert Rib Cap
US10822976B2 (en) 2013-06-03 2020-11-03 General Electric Company Nozzle insert rib cap
BR112015032787A2 (pt) * 2013-07-19 2017-08-22 Gen Electric Aparelho de bocal de turbina
CN106255806B (zh) * 2014-05-08 2019-05-31 西门子股份公司 涡轮组件和相应的操作方法
EP2949872A1 (de) * 2014-05-27 2015-12-02 Siemens Aktiengesellschaft Turbomaschine mit einer Dichtung zur Trennung von Arbeitsflüssigkeit und Kühlflüssigkeit der Turbomaschine und Verwendung der Turbomaschine
WO2016025056A2 (en) 2014-05-29 2016-02-18 General Electric Company Turbine engine and particle separators therefore
US11033845B2 (en) 2014-05-29 2021-06-15 General Electric Company Turbine engine and particle separators therefore
RU2581010C1 (ru) * 2014-11-18 2016-04-10 Акционерное общество "Научно-производственный центр газотурбостроения "Салют" (АО "НПЦ газотурбостроения "Салют") Способ ремонта механизма управления направляющим аппаратом компрессора двухконтурного газотурбинного двигателя
US10450880B2 (en) * 2016-08-04 2019-10-22 United Technologies Corporation Air metering baffle assembly
DE102016216858A1 (de) * 2016-09-06 2018-03-08 Rolls-Royce Deutschland Ltd & Co Kg Laufschaufel für eine Turbomaschine und Verfahren für den Zusammenbau einer Laufschaufel für eine Turbomaschine
US10677091B2 (en) * 2016-11-17 2020-06-09 Raytheon Technologies Corporation Airfoil with sealed baffle
US10577943B2 (en) 2017-05-11 2020-03-03 General Electric Company Turbine engine airfoil insert
DE102017208678A1 (de) 2017-05-23 2018-11-29 Siemens Aktiengesellschaft Turbinenschaufel mit Blecheinsatz
US10815806B2 (en) * 2017-06-05 2020-10-27 General Electric Company Engine component with insert
EP3421722A1 (de) * 2017-06-29 2019-01-02 Siemens Aktiengesellschaft Turbinenanordnung zur prallkühlung und verfahren zur montage
FR3074521B1 (fr) 2017-12-06 2019-11-22 Safran Aircraft Engines Secteur de distributeur de turbine pour une turbomachine d'aeronef
FR3076852B1 (fr) * 2018-01-16 2020-01-31 Safran Aircraft Engines Anneau de turbomachine
FR3094034B1 (fr) 2019-03-20 2021-03-19 Safran Aircraft Engines Chemise tubulaire de ventilation pour un distributeur de turbomachine
PL431184A1 (pl) * 2019-09-17 2021-03-22 General Electric Company Polska Spółka Z Ograniczoną Odpowiedzialnością Zespół silnika turbinowego
US11174794B2 (en) * 2019-11-08 2021-11-16 Raytheon Technologies Corporation Vane with seal and retainer plate
US11156105B2 (en) * 2019-11-08 2021-10-26 Raytheon Technologies Corporation Vane with seal
US11261748B2 (en) 2019-11-08 2022-03-01 Raytheon Technologies Corporation Vane with seal
FR3107733B1 (fr) * 2020-02-28 2022-07-08 Safran Aircraft Engines Pale de distributeur haute ou basse pression pour turbomachine, distributeur et turbomachine comportant de telles pales
CN112228905B (zh) * 2020-10-13 2022-01-21 西北工业大学 一种可抑制超临界流体流量分配偏差的通道结构
FR3129429B1 (fr) 2021-11-24 2024-08-09 Safran Aircraft Engines Secteur de distributeur de turbine pour une turbomachine d’aéronef
FR3130314B1 (fr) 2021-12-14 2024-07-19 Safran Aircraft Engines Secteur de distributeur de turbine pour une turbomachine d’aéronef
FR3152038A1 (fr) 2023-08-11 2025-02-14 Safran Aircraft Engines Distributeur, notamment pour une turbine d’une turbomachine d’aéronef

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE685320A (de) * 1965-05-03 1967-01-16
FR2094033A1 (de) * 1970-06-04 1972-02-04 Westinghouse Electric Corp
FR2205097A5 (de) * 1972-10-31 1974-05-24 Avco Corp
US5630700A (en) * 1996-04-26 1997-05-20 General Electric Company Floating vane turbine nozzle
EP1496205A1 (de) * 2003-06-30 2005-01-12 Snecma Moteurs Gekühlte Gasturbinenschaufel
EP1544414A1 (de) * 2003-12-17 2005-06-22 General Electric Company Innen gekühltes Leitschaufelpaar
EP1626162A1 (de) * 2004-08-11 2006-02-15 United Technologies Corporation Temperaturtolerante Leitschaufelanordnung

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3759038A (en) * 1971-12-09 1973-09-18 Westinghouse Electric Corp Self aligning combustor and transition structure for a gas turbine
CA1125660A (en) * 1979-06-29 1982-06-15 David L. Brown Cooled vane structure for a combustion turbine engine
US4381173A (en) * 1980-08-25 1983-04-26 United Technologies Corporation Coolable rotor blade assembly for an axial flow rotary machine
US5145315A (en) * 1991-09-27 1992-09-08 Westinghouse Electric Corp. Gas turbine vane cooling air insert
JPH06129204A (ja) * 1992-10-19 1994-05-10 Mitsubishi Heavy Ind Ltd ガスタービン静翼の冷却構造
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
JP3324256B2 (ja) * 1994-02-01 2002-09-17 石川島播磨重工業株式会社 タービン静翼の組立方法
JP3480069B2 (ja) * 1994-10-11 2003-12-15 石川島播磨重工業株式会社 ジェットエンジンの固定冷却翼
US6453557B1 (en) * 2000-04-11 2002-09-24 General Electric Company Method of joining a vane cavity insert to a nozzle segment of a gas turbine
EP1191189A1 (de) * 2000-09-26 2002-03-27 Siemens Aktiengesellschaft Gasturbinenschaufel
US6561757B2 (en) * 2001-08-03 2003-05-13 General Electric Company Turbine vane segment and impingement insert configuration for fail-safe impingement insert retention

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE685320A (de) * 1965-05-03 1967-01-16
FR2094033A1 (de) * 1970-06-04 1972-02-04 Westinghouse Electric Corp
FR2205097A5 (de) * 1972-10-31 1974-05-24 Avco Corp
US5630700A (en) * 1996-04-26 1997-05-20 General Electric Company Floating vane turbine nozzle
EP1496205A1 (de) * 2003-06-30 2005-01-12 Snecma Moteurs Gekühlte Gasturbinenschaufel
EP1544414A1 (de) * 2003-12-17 2005-06-22 General Electric Company Innen gekühltes Leitschaufelpaar
EP1626162A1 (de) * 2004-08-11 2006-02-15 United Technologies Corporation Temperaturtolerante Leitschaufelanordnung

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2955145A1 (fr) * 2010-01-14 2011-07-15 Snecma Distributeur de turbine haute pression d'un turboreacteur
WO2011086305A1 (fr) * 2010-01-14 2011-07-21 Snecma Distributeur de turbine haute pression d'un turboreacteur
GB2488958A (en) * 2010-01-14 2012-09-12 Snecma Dispenser for a high-pressure turbine of a jet engine
GB2488958B (en) * 2010-01-14 2016-04-13 Snecma A high-pressure turbine nozzle for a turbojet
US9328618B2 (en) 2010-01-14 2016-05-03 Snecma High-pressure turbine nozzle for a turbojet
FR2976616A1 (fr) * 2011-06-17 2012-12-21 Snecma Systeme de ventilation pour une pale creuse d un distributeur de turbine dans une turbomachine
EP2613004A3 (de) * 2012-01-09 2017-06-28 General Electric Company Leitschaufelnmontageverfahren
WO2023012421A1 (fr) * 2021-08-05 2023-02-09 Safran Aircraft Engines Chemise de refroidissement de pale creuse de distributeur
FR3126020A1 (fr) * 2021-08-05 2023-02-10 Safran Aircraft Engines Chemise de refroidissement de pale creuse de distributeur
US12196105B2 (en) 2021-08-05 2025-01-14 Safran Aircraft Engines Cooling jacket of a hollow blade of a distributor

Also Published As

Publication number Publication date
CA2582638C (fr) 2015-04-28
US7819628B2 (en) 2010-10-26
CN101122243A (zh) 2008-02-13
CA2582638A1 (fr) 2007-09-29
FR2899271B1 (fr) 2008-05-30
CN101122243B (zh) 2011-04-20
US20070231150A1 (en) 2007-10-04
JP2007263115A (ja) 2007-10-11
EP1840331B1 (de) 2017-05-31
RU2007111392A (ru) 2008-10-10
RU2439334C2 (ru) 2012-01-10
FR2899271A1 (fr) 2007-10-05

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