EP2990605A1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP2990605A1
EP2990605A1 EP14182277.5A EP14182277A EP2990605A1 EP 2990605 A1 EP2990605 A1 EP 2990605A1 EP 14182277 A EP14182277 A EP 14182277A EP 2990605 A1 EP2990605 A1 EP 2990605A1
Authority
EP
European Patent Office
Prior art keywords
section
channel
turbine blade
fluid
channel section
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.)
Withdrawn
Application number
EP14182277.5A
Other languages
German (de)
English (en)
Inventor
Stefan Dahlke
Tilman Auf Dem Kampe
Marc Fraas
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP14182277.5A priority Critical patent/EP2990605A1/fr
Priority to JP2017511287A priority patent/JP6328847B2/ja
Priority to EP15760398.6A priority patent/EP3155227B1/fr
Priority to PCT/EP2015/069232 priority patent/WO2016030289A1/fr
Priority to CN201580045953.2A priority patent/CN106574507B/zh
Priority to US15/505,185 priority patent/US9915150B2/en
Publication of EP2990605A1 publication Critical patent/EP2990605A1/fr
Withdrawn legal-status Critical Current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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/14—Two-dimensional elliptical
    • F05D2250/141—Two-dimensional elliptical circular
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • 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

Definitions

  • the invention relates to a turbine blade for a turbomachine with a turbine blade wall, in which at least one fluid channel is formed, through which a cooling fluid from a cold side to a hot gas flow over surface, i. the hot gas side of the turbine blade wall can flow, and wherein the at least one fluid channel at its end face facing the cold gas side an inflow channel section, at its end face facing the hot gas side of the turbine blade wall, an outflow channel section and between the inflow channel section and the outflow channel section central channel portion having a constant over its length, circular or oval cross-section defining a longitudinal axis of the fluid channel, which forms an acute angle with the hot gas overflowed surface of the turbine blade wall.
  • Turbomachines in particular gas turbines (in the broad sense), have a gas turbine (in the narrower sense), in which a hot gas, which was previously compressed in a compressor and heated in a combustion chamber, is relaxed to work.
  • gas turbines are designed in Axialbauweise, wherein the gas turbine is formed by a plurality of successively located in the flow direction blade rings.
  • the blade rings have circumferentially disposed blades and vanes, with the blades attached to a rotor of the gas turbine and the vanes secured to the housing of the gas turbine.
  • thermodynamic efficiency of gas turbines is the higher, the higher the inlet temperature of the hot gas is in the gas turbine.
  • the height of the inlet temperature limits are set by the thermal load capacity of the turbine blades. Accordingly, an objective is to To create turbine blades, which have sufficient for the operation of the gas turbine mechanical strength even at high thermal loads.
  • turbine blades are provided with elaborate coating systems.
  • To further increase the allowable turbine inlet temperature turbine blades are cooled during operation of the gas turbine.
  • the film cooling is a very effective and reliable method for cooling of highly stressed turbine blades. In this case, cooling air is tapped from the compressor and fed into the provided with internal cooling channels turbine blades.
  • the air After convective cooling of the material from the inside of the turbine blades, the air is directed through fluid passages to the outer surface of the turbine blade. There it forms a film that flows along the outer surface of the turbine blade and cools it, while protecting it from the hot flow.
  • Ring vortex ⁇ 1 The cooling air jet acts like an inclined cylinder on the main flow and accelerates it. There are pressure differences between the upstream and downstream side and the top of the cooling air jet, which lead to a compensating flow. As a result, ring vortices ⁇ 1 are formed. The rotation of the exiting boundary layer of the cooling air supports this effect.
  • Kidney vertebra ⁇ 2 The kidney vertebrae are the result of a pair of vertebrae in the fluid channel. Frictional forces in the free shear layer between the exiting cooling fluid jet and the main flow additionally amplify the rotation.
  • Horseshoe vortices ⁇ 3 are formed in the dust area of a cylinder standing vertically in a boundary layer flow. Near the wall, the pressure in the boundary layer is minimal. In contrast, a positive pressure gradient forms in the outer layer of the main flow boundary layer. The boundary layer separates and rolls against the main flow in the direction of the pressure minimum on the wall. The resulting vortex lays on both sides of the cylinder.
  • the direction of rotation of the horseshoe vortices ⁇ 3 is opposite to that of the neighboring ealds ⁇ 2, and the horseshoe vortices ⁇ 3 run laterally below the cooling air jet in the case of single-hole blow-out.
  • Instationary vertebrae ⁇ 4 The unsteady vertebrae are comparable to Kärmän vertebrae in the wake of a cylinder. reason for vortex formation, boundary layer separation is on the suction side of the cylinder. The unsteady vortices ⁇ 4 arise perpendicular to the cooled surface.
  • each of the two vortex arms ⁇ 2 is formed by a vortex, wherein the velocity vectors of the hot gas on the two inner sides of the vortex arms point away from the outer wall.
  • an intermediate channel section is provided between the central channel section and the inflow channel section, which has a constant, preferably circular or oval cross-section over its length, wherein the longitudinal axis of the intermediate channel portion is offset from the longitudinal axis of the central fluid channel portion and in particular parallel thereto.
  • the flow of the cooling fluid in the fluid channel can be influenced by the change in geometry according to the invention in such a way that the local flow velocities in the fluid channel are adapted in such a way that, on the one hand, the in Figure 11 vortex pair ⁇ 2 turns exactly the other way round and on the other hand, the separation in the diffuser can be moved to the upstream side, as in the FIG. 9 is shown. Both effects have a positive influence on the film cooling efficiency and in particular can cause the lateral expansion of the cooling fluid jet.
  • the central channel section adjoins the intermediate channel section to form an intermediate, lying perpendicular to the longitudinal axis of the fluid channel shoulder surface.
  • a shoulder surface in the transition region between the intermediate channel section and the central channel section, a shoulder surface may be formed which lies in a plane inclined at an angle ⁇ 90 °, for example approximately 45 °, to the longitudinal axis of the fluid channel.
  • the shoulder surface is preferably formed on a wall region of the fluid channel, while on the opposite wall region the intermediate channel section and the central channel section are rectilinear, i. without shouldering, merge into each other.
  • the wall of the fluid channel can extend in a straight line over its entire length.
  • a shoulder with a low shoulder height can also be formed here.
  • the shoulder surface is preferably located on the hot gas side or the cold gas side facing wall region of the fluid channel.
  • the central channel section has a cross-sectional area which is smaller by at least 30%, in particular by at least 40% and preferably at least 60%, compared with the intermediate channel section.
  • the outflow channel section may be formed in a manner known per se diffuser-like with a widening cross-section.
  • the wall of the fluid channel extends at its side facing the cold gas side wall region in the direction of the longitudinal axis of the fluid channel and connects in a straight line to the central channel section.
  • the outflow channel section has a constant, in particular round cross-section over its entire length.
  • the outflow channel section preferably runs concentrically with the central channel section and has the same cross section as the latter.
  • FIG. 1 is a section of a turbine blade wall 1, in which a fluid channel 2 is formed, through which a cooling fluid such as cooling air from a cold gas side of the turbine blade - here the interior of the turbine blade - to a hot gas overflowed outer surface of the turbine blade wall 2, which a Hot gas side of the turbine blade forms, can flow.
  • a cooling fluid such as cooling air from a cold gas side of the turbine blade - here the interior of the turbine blade - to a hot gas overflowed outer surface of the turbine blade wall 2, which a Hot gas side of the turbine blade forms, can flow.
  • the fluid channel 2 has at its end pointing to the cold gas side an inflow channel section 2a with a fluid inlet 3, at its end region facing the hot gas side of the turbine blade wall 1 a diffuser-like expanding outflow channel section 2b with a fluid outlet opening 4 and between the inflow channel section 2a and Outflow channel section 2b has a central channel section 2c which defines a longitudinal axis X of the fluid channel 2 and has a constant circular or oval cross-section over its length.
  • the longitudinal axis X of the fluid channel 2 encloses an acute angle, which is measured between the longitudinal axis X and the surface on the upstream side and the upstream side of the fluid channel, with the surface of the turbine blade wall 1 overflowed by the hot gas.
  • an intermediate channel portion 2d having a larger cross sectional area than the central channel portion 2c.
  • the inflow channel portion 2a and the intermediate channel portion 2d are formed as a through hole, so that the intermediate channel portion 2d rectilinearly adjoins the inflow channel section 2a and has a constant cross section over its length.
  • the transition region between the intermediate channel section 2d and the central channel section 2c is sharp-edged, wherein the wall of the fluid channel 2 is rectilinear on that side of the fluid channel 2 which faces the cold gas side, and a shoulder surface 5 on the opposite wall region facing the hot gas side is formed between the intermediate channel portion 2d and the central channel portion 2c, which is perpendicular to the longitudinal axis X of the fluid channel 2.
  • the shoulder surface 5 between the intermediate channel section 2 d and the central channel section 2 c on the cold gas side facing wall region form, then on the opposite, ie facing the hot gas side wall region, the wall of the fluid channel 2 is rectilinear, ie without shouldering.
  • the transition from the intermediate channel section 2d to the central channel section 2c of the fluid channel 2 is clearly visible.
  • the intermediate channel section 2d and the central channel section 2c each have a circular cross-section, the diameter D of the intermediate channel section 2d being significantly larger than the diameter 2d of the central channel section 2c.
  • the diameter ratio D / d is about 1.5.
  • the cross-sectional area of the central channel portion 2c has a cross sectional area smaller by about 55% than the intermediate channel portion 2d.
  • the intermediate channel portion 2d goes straight into the central channel portion 2c, while in the remaining peripheral portions the shoulder surface 5 is formed between the two channel portions 2d, 2c.
  • the intermediate channel section 2d has an oval cross section and the central channel section 2c has a circular cross section. Due to the oval configuration of the intermediate channel section 2d, the shoulder surface 5 is present only at the upstream wall region of the fluid channel 2.
  • the sharp-edged constriction in the transition region between the intermediate channel section 2d and the central channel section 2c causes the flow of cooling fluid - as in FIG FIG. 13 shown in the diffuser-extended outflow channel section 2b from the wall of the fluid channel at the upstream side with respect to the hot gas flow H side dissolves.
  • the cooling fluid then optimally contacts the outer surface of the turbine blade wall 1 after leaving the fluid channel 2 in order to protect it from the hot gas flowing over it.
  • FIG. 5 a similar fluid channel 2 is shown in a turbine blade wall 1.
  • the fluid inlet opening 3 is formed in the end face of a bead 6, which protrudes inwardly from the inner surface of the turbine blade wall 1, so that the cooling fluid enters the front side into the fluid channel 2.
  • FIG. 6 a further embodiment of a fluid channel 2 in a turbine blade wall 1 is shown.
  • this comprises an inflow channel section 2a on the cold side of the turbine blade wall 1, an outflow channel section 2b on the hot side of the turbine blade wall 1, an inlet channel section 2a and the outflow channel section 2a.
  • Channel section 2b lying central channel section 2c with a constant over its length, circular cross section, and an intermediate passage portion 2d formed between the inflow passage portion 2a and the central passage portion 2c.
  • the inflow channel section 2a and the intermediate channel section 2d are formed in the manner of a cylindrical bore with a constant diameter over the length, which is larger than the diameter of the central channel section 2c.
  • the longitudinal axis defined by the intermediate fluid passage 2d and the inflow fluid passage 2a is offset from the longitudinal axis X of the central passage portion 2c.
  • the arrangement is such that between the intermediate channel section 2d and the central channel section 2c, a shoulder surface 5 is formed on the side facing the cold gas side of the fluid channel 2, while on the opposite, ie the hot gas side facing the Fluidkanalwandung in the transition region between the Intermediate channel section 2d and the central channel section 2c is rectilinear, so here takes place a continuous transition from the intermediate channel section 2d in the central channel section 2c without shouldering.
  • the shoulder surface 5 is not perpendicular to the longitudinal axis of the fluid channel, but in a relative to the longitudinal axis X by about 45 ° inclined plane.
  • the transition region is in the cross section of FIG. 11 recognizable.
  • the shoulder surface may also be formed on the wall region of the fluid channel 2 pointing to the hot gas side, while the fluid channel wall in the transitional region between the intermediate channel section 2d and the central channel section 2c runs rectilinearly on the opposite side, ie facing the cold gas side.
  • FIGS. 7 and 8 Such embodiments are in the FIGS. 7 and 8 shown.
  • FIG. 7 it can be seen that the plane in which the shoulder surface 5 lies encloses an angle ⁇ 90 ° with the wall area situated to the hot gas side, so that a kind of return is formed.
  • the shoulder surface. 5 enclose an angle ⁇ 90 ° with the area of the cold gas side, forming a return, as shown in FIG. 9 is shown.
  • the outflow channel section 2b is formed diffuser-like.
  • the outflow passage portion 2b may be as shown in FIG. 10 shown also represent a continuation of the central channel section 2c.
  • the inflow channel portion 2a and the intermediate channel portion 2d form a larger diameter bore
  • the central channel portion 2c and the outflow channel portion 2b have a smaller diameter bore, the bores being offset such that a shoulder surface 5 in the transitional region between the Inter-channel portion 2d and the central channel portion 2c formed on the downstream side of the Fluidkanalwandung.
  • the cooling fluid in the fluid channel 2 is initially delayed and then accelerated in the region of the inclined shoulder surface 5 and deflected such that a separation of the cooling fluid flow in the upstream side the Fluidkanalwandung takes place.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14182277.5A 2014-08-26 2014-08-26 Aube de turbine Withdrawn EP2990605A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP14182277.5A EP2990605A1 (fr) 2014-08-26 2014-08-26 Aube de turbine
JP2017511287A JP6328847B2 (ja) 2014-08-26 2015-08-21 タービンブレード
EP15760398.6A EP3155227B1 (fr) 2014-08-26 2015-08-21 Aube de turbine
PCT/EP2015/069232 WO2016030289A1 (fr) 2014-08-26 2015-08-21 Aube de turbine
CN201580045953.2A CN106574507B (zh) 2014-08-26 2015-08-21 涡轮叶片
US15/505,185 US9915150B2 (en) 2014-08-26 2015-08-21 Turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14182277.5A EP2990605A1 (fr) 2014-08-26 2014-08-26 Aube de turbine

Publications (1)

Publication Number Publication Date
EP2990605A1 true EP2990605A1 (fr) 2016-03-02

Family

ID=51392173

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14182277.5A Withdrawn EP2990605A1 (fr) 2014-08-26 2014-08-26 Aube de turbine
EP15760398.6A Not-in-force EP3155227B1 (fr) 2014-08-26 2015-08-21 Aube de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP15760398.6A Not-in-force EP3155227B1 (fr) 2014-08-26 2015-08-21 Aube de turbine

Country Status (5)

Country Link
US (1) US9915150B2 (fr)
EP (2) EP2990605A1 (fr)
JP (1) JP6328847B2 (fr)
CN (1) CN106574507B (fr)
WO (1) WO2016030289A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3354849A1 (fr) 2017-01-31 2018-08-01 Siemens Aktiengesellschaft Paroi pour composant à gaz chaud et composant à gaz chaud associé pour turbine à gaz
EP4134516A1 (fr) * 2021-08-13 2023-02-15 Raytheon Technologies Corporation Dispositifs pour un moteur à turbine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102019200985B4 (de) * 2019-01-25 2023-12-07 Rolls-Royce Deutschland Ltd & Co Kg Triebwerksbauteil mit mindestens einem Kühlkanal und Herstellungsverfahren
CN112922677A (zh) * 2021-05-11 2021-06-08 成都中科翼能科技有限公司 一种用于涡轮叶片前缘冷却的组合结构气膜孔
CN113719323B (zh) * 2021-07-09 2022-05-17 北京航空航天大学 一种燃气轮机涡轮叶片复合冷却结构
US12006837B2 (en) * 2022-01-28 2024-06-11 Rtx Corporation Ceramic matrix composite article and method of making the same

Citations (5)

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Publication number Priority date Publication date Assignee Title
US5223320A (en) * 1990-06-05 1993-06-29 Rolls-Royce Plc Perforated two layered sheet for use in film cooling
JP2006307842A (ja) * 2005-03-30 2006-11-09 Mitsubishi Heavy Ind Ltd ガスタービン用高温部材
US20090304499A1 (en) 2008-06-06 2009-12-10 United Technologies Corporation Counter-Vortex film cooling hole design
EP2492454A2 (fr) * 2011-02-24 2012-08-29 Rolls-Royce plc Composant de paroi d'extrémité pour étage de turbine à gaz
WO2013089255A1 (fr) 2011-12-15 2013-06-20 株式会社Ihi Lame de turbine

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US3542486A (en) * 1968-09-27 1970-11-24 Gen Electric Film cooling of structural members in gas turbine engines
US4738588A (en) * 1985-12-23 1988-04-19 Field Robert E Film cooling passages with step diffuser
US6092982A (en) * 1996-05-28 2000-07-25 Kabushiki Kaisha Toshiba Cooling system for a main body used in a gas stream
US7328580B2 (en) 2004-06-23 2008-02-12 General Electric Company Chevron film cooled wall
US20120107135A1 (en) 2010-10-29 2012-05-03 General Electric Company Apparatus, systems and methods for cooling the platform region of turbine rotor blades
EP2584147A1 (fr) 2011-10-21 2013-04-24 Siemens Aktiengesellschaft Aube de turbine refroidie par film pour une turbomachine
US8683813B2 (en) * 2012-02-15 2014-04-01 United Technologies Corporation Multi-lobed cooling hole and method of manufacture
US20140161625A1 (en) 2012-12-11 2014-06-12 General Electric Company Turbine component having cooling passages with varying diameter
US9835035B2 (en) 2013-03-12 2017-12-05 Howmet Corporation Cast-in cooling features especially for turbine airfoils
GB201311333D0 (en) 2013-06-26 2013-08-14 Rolls Royce Plc Component for use in releasing a flow of material into an environment subject to periodic fluctuations in pressure

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5223320A (en) * 1990-06-05 1993-06-29 Rolls-Royce Plc Perforated two layered sheet for use in film cooling
JP2006307842A (ja) * 2005-03-30 2006-11-09 Mitsubishi Heavy Ind Ltd ガスタービン用高温部材
US20090304499A1 (en) 2008-06-06 2009-12-10 United Technologies Corporation Counter-Vortex film cooling hole design
EP2492454A2 (fr) * 2011-02-24 2012-08-29 Rolls-Royce plc Composant de paroi d'extrémité pour étage de turbine à gaz
WO2013089255A1 (fr) 2011-12-15 2013-06-20 株式会社Ihi Lame de turbine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3354849A1 (fr) 2017-01-31 2018-08-01 Siemens Aktiengesellschaft Paroi pour composant à gaz chaud et composant à gaz chaud associé pour turbine à gaz
WO2018141739A1 (fr) 2017-01-31 2018-08-09 Siemens Aktiengesellschaft Paroi d'une partie de gaz chaud et partie de gaz chaud correspondante d'une turbine à gaz
EP4134516A1 (fr) * 2021-08-13 2023-02-15 Raytheon Technologies Corporation Dispositifs pour un moteur à turbine

Also Published As

Publication number Publication date
JP2017530291A (ja) 2017-10-12
WO2016030289A1 (fr) 2016-03-03
US20170268347A1 (en) 2017-09-21
CN106574507B (zh) 2018-05-11
US9915150B2 (en) 2018-03-13
EP3155227B1 (fr) 2019-01-02
JP6328847B2 (ja) 2018-05-23
EP3155227A1 (fr) 2017-04-19
CN106574507A (zh) 2017-04-19

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