EP1555390A1 - Kühlluftauslass-Schlitze von Turbinenschaufeln - Google Patents

Kühlluftauslass-Schlitze von Turbinenschaufeln Download PDF

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Publication number
EP1555390A1
EP1555390A1 EP04293046A EP04293046A EP1555390A1 EP 1555390 A1 EP1555390 A1 EP 1555390A1 EP 04293046 A EP04293046 A EP 04293046A EP 04293046 A EP04293046 A EP 04293046A EP 1555390 A1 EP1555390 A1 EP 1555390A1
Authority
EP
European Patent Office
Prior art keywords
blade
slot
opening
wall
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.)
Granted
Application number
EP04293046A
Other languages
English (en)
French (fr)
Other versions
EP1555390B1 (de
Inventor
Jacques Boury
Maurice Judet
Jacky Tabardin
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 Moteurs SA
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 Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1555390A1 publication Critical patent/EP1555390A1/de
Application granted granted Critical
Publication of EP1555390B1 publication Critical patent/EP1555390B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/103—Multipart cores
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the present invention relates to the general field of turbine blades, and more particularly to the geometry of the slots exhaust air cooling located on the trailing edge of moving or fixed blades of a turbomachine turbine.
  • a turbomachine turbine (for example, the high-pressure turbine) consists of a plurality of stages each formed of a distributor and a moving wheel.
  • the distributor of the turbine comprises a plurality of fixed vanes for straightening the flow of gas on through and the impeller of the turbine is made up of a plurality of moving blades.
  • the blades and the blades of such a turbine are subject to very high temperatures of the gases from the combustion chamber and that pass through the turbine. These temperatures reach values far superior to those that can withstand blades which are in contact with these gases, which has the consequence of limit their life.
  • cooling circuit vanes In order to limit the damage caused by these hot gases on blades, it is known to provide these cooling circuit vanes to reduce the temperature of the latter. Thanks to such circuits, cooling air that is introduced into the dawn crosses this one following a path formed by cavities practiced in the dawn before being ejected by slots opening on the surface of the dawn, between the foot and the top of it.
  • FIG. 7 illustrates the location of such cracks for a mobile turbine blade.
  • This figure is a partial view and in perspective of a mobile blade 100 of high-pressure turbine.
  • Dawn 100 has an aerodynamic surface 102 which is connected to the level of the foot of dawn 104 to a platform 106 through a zone of connection 108.
  • the aerodynamic surface 102 of the dawn extends axially between a leading edge (not shown in the figure) and a trailing edge 110.
  • Each evacuation slot 112 is in particular formed of a side wall 114 provided with an opening (not shown) opening in the cavities traversed by the cooling air.
  • Each slot also has a recessed wall 116 extending between the side wall 114 and the trailing edge 110 of the blade, a top wall 118 and a bottom wall 120 which extend between the wall in recess 116 and the aerodynamic surface 102 of the blade.
  • one or more creeks 122 are formed at the level of the slot 112a which is the slot closest to the platform 106 (hereinafter called lower slot). More precisely, the creeks 122 are form at the recessed wall 116 of the lower slot 112a and propagate axially from the trailing edge 110 of dawn to the side wall 114.
  • Such cracks result mainly from a strong concentration of mechanical stresses at the lower slot 112a which are generated in particular by the lower wall 120 of this lower slot. There is a risk that such creeks spread on the entire aerodynamic surface 102 of the dawn, thus limiting its duration of life.
  • the US patent 6,062,817 provides, for a moving blade, to partially remove the bottom wall of the evacuation slot closest to the platform so that the recessed wall of this slot extends radially partly between the upper wall and the platform of the dawn.
  • the present invention therefore aims to overcome such drawbacks by proposing a turbine blade with the slot or slots closest to the platform or platforms has a geometry that allows both avoid the formation of creeks and ensure cooling of the area connection between the platform or platforms and the dawn.
  • a turbomachine turbine blade having an aerodynamic surface extending radially between a dawn foot and a dawn apex and axially between a leading edge and a trailing edge, at least one lower platform connected to the foot of the dawn by a lower connection area, and a circuit of cooling consisting of at least one radially extending cavity between the top and the blade root, at least one intake opening of air at a radial end of the or the cavities, of a plurality of slots evacuation along the trailing edge of the dawn, including a slot lower evacuation arranged in the vicinity of the blade root, the slot lower outlet having a side wall provided with a opening opening in the cavity or cavities, a recessed wall, a lower wall arranged on the side of the blade root, a lower edge formed between the recessed wall and the bottom wall, and a ledge lower formed between the bottom wall and the connection area lower, characterized in that the lower edge and the lower edge of the lower discharge slot each have a cross-section substantially rounded in shape so as to
  • the rounded shape of the straight section of the ridge lower and lower edge of the lower discharge slot avoids any formation of cracks at the recessed wall of this slot. Moreover, thanks to this rounded shape, an air film of cooling is created at the lower connection area between the platform and the dawn foot to cool this area. The temperature of the connection area is thus lowered.
  • the dawn further comprises a platform superior connected to the top of the dawn by a zone of connection, the cooling circuit comprising in in addition to an upper discharge slot disposed near the top blade and having a side wall with an opening opening in the cavity or recesses, a recessed wall, an upper wall disposed on the side of the blade tip, an upper edge formed between the recessed wall and top wall, and a top ledge formed between the upper wall and the upper connection zone; characterized in that the upper ridge and the upper rim of the slot top exhaust each have a straight cross-section substantially rounded so as to eliminate any salient angle between the opening of said slot and the upper connection area.
  • the rounded shapes of the cross section of the ridges and flanges each extend axially from the opening of the evacuation slot to an exit plane extending axially between said opening of the discharge slot and the trailing edge of the blade.
  • Rounded shapes of straight section of edges and edges advantageously each have a radius of curvature which is increasing from the opening of the evacuation slot to the exit plane.
  • these radii of curvature are preferably such that the wall recess of the evacuation slot and the connection area are confused.
  • the recessed wall of the lower vent slot can tilt toward the dawn top and the opening of the side wall of the evacuation slot lower can be formed essentially in the connection zone lower.
  • the subject of the invention is also a core for obtaining a dawn as described above, comprising a main part intended to reserve a location for the cooling cavity of dawn, the main part being provided with a plurality of tongues terminals that are intended to reserve as many locations for ventilation slots of the cooling circuit of the blade, characterized in that what the main part of the core includes in addition, at a level of slot for the lower vent slot, one tab lower shape complementary to this lower slot.
  • the invention also relates to a high-pressure turbine of turbomachine having a plurality of blades as defined previously, and a turbomachine distributor comprising a a plurality of vanes as defined above.
  • FIG. 1 represents in perspective a moving blade 10 of turbomachine high-pressure turbine.
  • Dawn 10 is fixed on a wheel mobile turbine (not shown) via a fitting 12 in the shape of fir.
  • Dawn 10 is in the form of a surface aerodynamic 14 which extends radially between a blade root 16 and a blade tip 18 and axially between a leading edge 20 and an edge of 22.
  • the aerodynamic surface 14 of the dawn thus defines the intrados 14a and the extrados 14b of dawn.
  • the fitting 12 of the dawn 10 is connected to the dawn foot 16 at a lower platform 24 defining a wall for the flow path of the combustion gases through the turbine.
  • the platform 24 is connected to the blade root 16 by a connection zone lower 26.
  • the blade 10 comprises one or more circuits internal cooling.
  • Each cooling circuit consists of at least one cavity 28 extending radially between the foot 16 and the apex 18 of blade.
  • the cavity is supplied with cooling air at one of its ends radial through an air inlet opening (not shown). This air intake opening is usually provided at the level of the fitting 12 of the blade 10.
  • a plurality of slots 30 are distributed along the trailing edge 22, between the foot 16 and the top 18 blade. These evacuation slots 30 open into the cavity 28 and lead to the intrados 14a of dawn, at its trailing edge 22.
  • the blade 10 has a lower discharge slot 30a which is disposed in the vicinity of the blade root 16. Compared to other slots 30, this lower slot 30a is the closest from the lower platform 24.
  • the lower discharge slot 30a consists of a wall recess (or recess) 32, a wall (or step) lower 34, and a side wall 36 provided with an opening 38 opening into the cavity 28 of the cooling circuit.
  • bottom wall is meant the wall which is arranged on the side at the blade root 16.
  • the recessed wall 32 extends radially from the bottom wall 34 to the blade tip 18 and axially between the side wall 36 and the trailing edge 22 of the blade.
  • the wall bottom 34 extends between the recessed wall 32 and the bottom connection 26.
  • a lower edge 40 formed between the recessed wall 32 and the lower wall 34.
  • a lower rim 42 is formed between the lower wall 34 and the lower connection zone 26.
  • This particular geometry of the lower vent slot 30a provides a guiding air from the cavity of the circuit of cooling through the opening 38 and thus allows to cool the edge of leaking 22 of dawn which is the part of the dawn the least thick and therefore the more exposed to high temperatures flue gas.
  • the lower edge 40 and the lower edge 42 of the lower vent slot 30a each have a section right shaped substantially rounded to remove any angle protruding between the opening 38 of the slot 30a and the connection zone bottom 26.
  • any formation of cracks at the wall in recess 32 of the lower vent slot 30a is avoided.
  • the shapes rounded off the right section of lower edge 40 and flange 42 each extend axially from the opening 38 of the slot lower discharge 30a to an outlet plane P extending axially between the opening of the discharge slot and the trailing edge 22 of dawn.
  • the output plane P can be defined with respect to a system of coordinates formed by X, Y and Z axes shown in FIG. relative to this coordinate system, the output plane P is parallel to the XY plane.
  • the rounded shapes of the straight section of ridge 40 and rim 42 lower ones each have a radius of curvature which is increasing from the opening 38 of the lower discharge slot 30a towards the plane P output.
  • the width (in the direction intrados / extrados) of the wall lower 34 decreases until disappearing completely at the level of the section represented by FIG. 3C (that is, at the plane of output P).
  • the radius of curvature of the rounded shapes of the ridge 40 and the rim 42 lower are such that the recessed wall 32 of the slot lower 30a and the lower connection zone 26 are combined.
  • FIG. 4 thus illustrates a fixed blade 50 of a distributor of high-pressure turbine of a turbomachine.
  • fixed blade 50 is mounted between two platforms; namely a platform lower 52 and an upper platform 54.
  • the platform upper 54 is connected to the top 18 of the blade by a zone of upper connection 56, while the lower platform 52 is connected to the blade root 16 by a lower connection zone 58.
  • the circuit of fixed blade cooling 50 has a plurality of slots 30 of which a lower slot 30a which opens into the cavity of cooling 28, which is disposed in the vicinity of the blade root 16 and which leads to the intrados 14a of dawn.
  • This lower evacuation slot 30a has the same peculiarities as those of the moving blade of the figure 1.
  • the cooling circuit of the fixed blade 50 further comprises an upper discharge slot 30b which opens also in the cooling cavity 28 and which is arranged at near the top of blade 18. This upper slot 30b leads to the intrados 14a of the dawn 50.
  • this upper slot 30b consists of a side wall 60 provided with an opening 62 opening in the cooling cavity 28, a recessed wall 64, and a upper wall 66 disposed on the side of the blade tip 18.
  • wall upper 66 we mean the wall which is located on the side of the dawn apex 18.
  • this slot 30b an upper edge 70 formed between the recessed wall 64 and the top wall 66, and an upper flange 72 formed between the upper wall 66 and the zone of upper connection 56.
  • the upper edge 70 and the rim upper 72 of the upper vent slot 30b each present a cross-section of substantially rounded shape so as to eliminate any projecting angle between the opening 62 of the slot 30b and the zone of upper connection 56.
  • the blades 10 and fixed 50 according to the invention are obtained directly by molding.
  • the dawn is made by casting a metal in a mold containing a ceramic core whose particular function is to reserve a location for the dawn cooling circuit (ie for the cavity 28 and each discharge slot 30, 30a and 30b). Once the metal is poured into the mold, the dawn is cooled and the ceramic core is removed.
  • FIG. 6 represents a ceramic core 80 making it possible to reserve a location for the dawn cooling circuit 10 of Figure 1. This Figure 6 illustrates this core of the extrados side of dawn.
  • the core 80 has a main portion 82 for reserve a location for the cooling cavity or cavities of dawn.
  • This main portion 82 is provided with a plurality of tongues terminals (or fingers) 84 which are intended to reserve as much locations for the cooling system exhaust slots of dawn.
  • the ceramic core 80 presents, at the level of the slot for this lower slot, one tab lower 84a complementary shape to these rounded shapes.
  • the lower tongue 84a has a first edge 86 of complementary shape to the recessed wall of the lower slot, a second edge 88 of complementary shape to the lower wall of this slot, and a third edge 90 of shape complementary to its side wall.
  • the lower edge 92 formed between the first 86 and second edge 88 edges thus has a cross section of substantially rounded.
  • the lower rim 94 formed between the second edge 88 and an edge (not shown) of complementary shape to the zone of lower connection of the dawn to the lower platform presents also a cross section of substantially rounded shape.
  • the recessed wall 32 of the slot lower vent 30a has an inclination towards the top blade.
  • This inclination (for example of the order of 10 ° to 30 °), which is illustrated in FIG. 1, also makes it possible to increase the cooling of the connection zone 26 between the platform 24 and the dawn foot 16.
  • the opening 38 of the evacuation slot lower 30a of such a moving blade 10 is preferably formed essentially in the connection zone 26 between the platform 24 and the dawn foot 16.

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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)
EP04293046A 2004-01-14 2004-12-20 Kühlluftauslass-Schlitze von Turbinenschaufeln Expired - Lifetime EP1555390B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0400289A FR2864990B1 (fr) 2004-01-14 2004-01-14 Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine haute-pression
FR0400289 2004-01-14

Publications (2)

Publication Number Publication Date
EP1555390A1 true EP1555390A1 (de) 2005-07-20
EP1555390B1 EP1555390B1 (de) 2006-11-22

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP04293046A Expired - Lifetime EP1555390B1 (de) 2004-01-14 2004-12-20 Kühlluftauslass-Schlitze von Turbinenschaufeln

Country Status (9)

Country Link
US (1) US7278827B2 (de)
EP (1) EP1555390B1 (de)
JP (1) JP4619135B2 (de)
CA (1) CA2493094C (de)
DE (1) DE602004003331T2 (de)
ES (1) ES2276254T3 (de)
FR (1) FR2864990B1 (de)
RU (1) RU2294438C2 (de)
UA (1) UA84846C2 (de)

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EP1840329A1 (de) * 2006-03-30 2007-10-03 Snecma Optimierte Leitschaufel eines Gleichrichters, Gleichrichtersektor, Verdichtungsstufe, Verdichter und Strömungsmaschine, die eine solche Leitschaufel umfasst
EP1840328A1 (de) * 2006-03-30 2007-10-03 Snecma Gleichrichtersektor, Verdichtungsstufe, Verdichter und Strömungsmaschine, die eine solcher Sektor umfasst
EP1726782A3 (de) * 2005-05-27 2010-05-05 United Technologies Corporation Konfiguration der Abströmkante einer Turbinenschaufel
WO2014163694A3 (en) * 2013-03-13 2014-12-24 Moody Jack K Trenched cooling hole arrangement for a ceramic matrix composite vane
WO2021259569A1 (de) * 2020-06-22 2021-12-30 Siemens Aktiengesellschaft Turbinenschaufel und verfahren zum bearbeiten einer solchen

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US7503749B2 (en) * 2005-04-01 2009-03-17 General Electric Company Turbine nozzle with trailing edge convection and film cooling
US7575414B2 (en) * 2005-04-01 2009-08-18 General Electric Company Turbine nozzle with trailing edge convection and film cooling
FR2924156B1 (fr) * 2007-11-26 2014-02-14 Snecma Aube de turbomachine
DE202008010121U1 (de) 2008-07-29 2009-05-14 Koltun, Mykhaylo Einrichtung zur Durchführung des Abgasreinigungsverfahrens (Dieselmotor)
DE102008035271B4 (de) 2008-07-29 2023-06-29 Genady Maslov Verfahren und Einrichtung zur Verarbeitung von Abgasen (Dieselmotor)
DE202008010119U1 (de) 2008-07-29 2009-05-07 Koltun, Mykhaylo Einrichtung zur Reinigung von Abgasen der Turbostrahltriebwerke
CH699601A1 (de) * 2008-09-30 2010-03-31 Alstom Technology Ltd Schaufel für eine gasturbine.
US8113784B2 (en) * 2009-03-20 2012-02-14 Hamilton Sundstrand Corporation Coolable airfoil attachment section
US8632297B2 (en) * 2010-09-29 2014-01-21 General Electric Company Turbine airfoil and method for cooling a turbine airfoil
EP2639004B1 (de) * 2012-03-15 2016-05-11 MTU Aero Engines GmbH Schaufelkranzsegment mit Ringraumbegrenzungsfläche mit einem welligen Höhenprofil sowie Verfahren zur Herstellung desselben
US9175569B2 (en) * 2012-03-30 2015-11-03 General Electric Company Turbine airfoil trailing edge cooling slots
US20130302176A1 (en) * 2012-05-08 2013-11-14 Robert Frederick Bergholz, JR. Turbine airfoil trailing edge cooling slot
US20130302177A1 (en) * 2012-05-08 2013-11-14 Robert Frederick Bergholz, JR. Turbine airfoil trailing edge bifurcated cooling holes
US20130302179A1 (en) * 2012-05-09 2013-11-14 Robert Frederick Bergholz, JR. Turbine airfoil trailing edge cooling hole plug and slot
DE102013213416B4 (de) * 2013-07-09 2017-11-09 MTU Aero Engines AG Schaufel für eine Gasturbomaschine
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
US20160208626A1 (en) * 2015-01-19 2016-07-21 United Technologies Corporation Integrally bladed rotor with pressure side thickness on blade trailing edge
US10196904B2 (en) 2016-01-24 2019-02-05 Rolls-Royce North American Technologies Inc. Turbine endwall and tip cooling for dual wall airfoils
US10240462B2 (en) 2016-01-29 2019-03-26 General Electric Company End wall contour for an axial flow turbine stage
EP3954882B1 (de) * 2016-03-30 2023-05-03 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Turbolader mit variabler geometrie
FR3108364B1 (fr) 2020-03-18 2022-03-11 Safran Aircraft Engines Aube de turbine comportant des nervures entre des sorties de refroidissement avec des orifices de refroidissement
FR3108363B1 (fr) 2020-03-18 2022-03-11 Safran Aircraft Engines Aube de turbine comportant trois types d’orifices de refroidissement du bord de fuite
CN112343666B (zh) * 2020-12-14 2021-08-24 北京航空航天大学 一种应用于涡轮叶片尾缘半劈缝的波纹型肋导流结构
CN113236370B (zh) * 2021-05-25 2023-04-25 杭州汽轮动力集团有限公司 一种燃气轮机涡轮高压动叶片的冷却结构
US12158083B2 (en) * 2021-11-18 2024-12-03 Rtx Corporation Airfoil with axial cooling slot having diverging ramp

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EP1840329A1 (de) * 2006-03-30 2007-10-03 Snecma Optimierte Leitschaufel eines Gleichrichters, Gleichrichtersektor, Verdichtungsstufe, Verdichter und Strömungsmaschine, die eine solche Leitschaufel umfasst
EP1840328A1 (de) * 2006-03-30 2007-10-03 Snecma Gleichrichtersektor, Verdichtungsstufe, Verdichter und Strömungsmaschine, die eine solcher Sektor umfasst
FR2899270A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Aube de redresseur a amenagement de forme localise, secteur de redresseurs, etage de compression, compresseur et turbomachine comportant une telle aube
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US7857584B2 (en) 2006-03-30 2010-12-28 Snecma Stator vane with localized reworking of shape, stator section, compression stage, compressor and turbomachine comprising such a vane
RU2434141C2 (ru) * 2006-03-30 2011-11-20 Снекма Сектор направляющих лопаток газотурбинного двигателя, ступень сжатия, компрессор и газотурбинный двигатель
WO2014163694A3 (en) * 2013-03-13 2014-12-24 Moody Jack K Trenched cooling hole arrangement for a ceramic matrix composite vane
US9719357B2 (en) 2013-03-13 2017-08-01 Rolls-Royce Corporation Trenched cooling hole arrangement for a ceramic matrix composite vane
WO2021259569A1 (de) * 2020-06-22 2021-12-30 Siemens Aktiengesellschaft Turbinenschaufel und verfahren zum bearbeiten einer solchen
KR20230027211A (ko) 2020-06-22 2023-02-27 지멘스 에너지 글로벌 게엠베하 운트 코. 카게 터빈 블레이드 및 그 가공 방법
US11867083B2 (en) 2020-06-22 2024-01-09 Siemens Energy Global GmbH & Co. KG Turbine blade and method for machining same

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DE602004003331T2 (de) 2007-06-21
EP1555390B1 (de) 2006-11-22
JP4619135B2 (ja) 2011-01-26
RU2294438C2 (ru) 2007-02-27
CA2493094C (fr) 2011-10-11
DE602004003331D1 (de) 2007-01-04
FR2864990A1 (fr) 2005-07-15
RU2005100467A (ru) 2006-06-20
CA2493094A1 (fr) 2006-07-14
US20050249593A1 (en) 2005-11-10
UA84846C2 (ru) 2008-12-10
JP2005201273A (ja) 2005-07-28
US7278827B2 (en) 2007-10-09
ES2276254T3 (es) 2007-06-16
FR2864990B1 (fr) 2008-02-22

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