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EP3155227A1 - Aube de turbine - Google Patents

Aube de turbine

Info

Publication number
EP3155227A1
EP3155227A1 EP15760398.6A EP15760398A EP3155227A1 EP 3155227 A1 EP3155227 A1 EP 3155227A1 EP 15760398 A EP15760398 A EP 15760398A EP 3155227 A1 EP3155227 A1 EP 3155227A1
Authority
EP
European Patent Office
Prior art keywords
section
channel
turbine blade
channel section
central
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
EP15760398.6A
Other languages
German (de)
English (en)
Other versions
EP3155227B1 (fr
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
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of EP3155227A1 publication Critical patent/EP3155227A1/fr
Application granted granted Critical
Publication of EP3155227B1 publication Critical patent/EP3155227B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/186—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
    • 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

  • Turbine blade the invention relates to a turbine blade for a Strö ⁇ mung machine according to the preamble of claim 1.
  • Such turbine blades 206 307 842 A are known from JP.
  • 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 several in the flow direction ⁇ consecutive 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 of the turbine show ⁇ feln.
  • an object is to provide turbine blades that have sufficient mechanical strength for the operation of the gas turbine even at high thermal loads.
  • turbine screens are provided with elaborate coating systems.
  • turbine blades are cooled during operation of the gas turbine.
  • the film cooling is a very effective and reli ⁇ permeable method for cooling of turbine blades is highly stressed. In this case, cooling air is draws taps ⁇ from the compressor and recycled to the provided in with internal cooling passages turbine blades.
  • Fluid channels or fluid channels with oval cross section ⁇ set. Furthermore, it is known to expand the cross-section of the fluid channels at the outlet, ie in the outflow channel section, in a diffuser-like manner, in accordance with the principle of slot cooling. In this case, the outlet cross-section is increased by a certain factor. This leads to an on ⁇ fanning of the cooling air jet, which is associated depending on the Strö ⁇ mung situation with a lowering of the beam pulse, lower mixing losses and greater lateral cover. In general, contoured holes lead to an increase in the effectiveness in the area of the fluid channel longitudinal axis and overall to a better lateral Abde ⁇ ckung.
  • 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 compensation 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 enhance the rotation.
  • Horseshoe vortex ⁇ 3 arise in the dust ⁇ rich of an upright in a boundary layer flow cylinder. 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 is peeled off and rolls against the Hauptströ ⁇ mung in the direction of the minimum pressure on the wall a. The resulting vortex lays on both sides of the cylinder. The direction of rotation of the horseshoe vertebrae ⁇ 3 is opposite to that of the neighboring kidney vertebra ⁇ 2, and the horseshoe vortices ⁇ 3 run laterally below the cooling air jet during single-hole blow-out.
  • Unsteady vortex ⁇ 4 The unsteady vortices are ver ⁇ parable with Karman vortices in the wake of a cylinder.
  • the cause of vortex formation is the boundary layer separation on the suction side of the cylinder.
  • the unsteady vortices ⁇ 4 arise perpendicular to the cooled surface.
  • 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 may be lying in a direction inclined to the longitudinal axis of the fluid channel at an angle a ⁇ 90 °, for example approximately 45 ° level.
  • the shoulder surface is formed at a Wandbe ⁇ area of the fluid channel, while the particularlylie ⁇ constricting wall portion of the intermediate duct portion and the center ⁇ rale channel-section straight, that is without shoulder formation, merge into one another.
  • 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.
  • an intermediate channel portion is provided between the central channel portion and the inflow channel portion having over its length section ei ⁇ NEN constant, preferably circular or oval cross, the longitudinal axis of the intermediate
  • Channel section is offset relative to the longitudinal axis of the central fluid channel section and in particular runs parallel to this. It has been found that the geometry due to the inventively vorgenom ⁇ mene change the flow of the cooling fluid can be influenced in the fluid channel in such a way that the local flow speeds are fitted in such a way reasonable in the fluid channel, on the one hand, the overall in Figure 15 showed vortex pair ⁇ 2 rotates the other way around and on the other hand, the separation in the diffuser ⁇ toward the upstream side can be displaced, as shown in FIG. 13 Both effects have a positive influence on the film ⁇ cooling effectiveness and can cause particular the lateral Ausdeh- voltage of the cooling fluid jet.
  • the central channel section is smaller than the intermediate channel section by at least 30%, in particular by at least 40%, and preferably at least 60%
  • the outflow channel portion may be formed in known manner ⁇ diffuser-out with a widening cross-section.
  • the wall of the fluid channel runs at its wall region facing the cold gas side in the flow path. tion of the longitudinal axis of the fluid channel and connects straight ⁇ linig to the central channel section.
  • the outflow channel section has a constant, in particular round cross-section over its entire length.
  • the outflow channel extends from ⁇ cut preferably concentric with the central cut Kanalab ⁇ and has the same cross-section as this.
  • FIG. 1 shows a longitudinal section through a turbine blade wall with a fluid channel, which is designed according to the invention
  • Figure 2 shows a variant of the turbine blade wall shown in Figure 1 in a longitudinal section
  • Figure 3 is a cross-sectional view taken along the line V-V in
  • Figure 1 in which the cross-sectional geometries of the fluid channel in the intermediate channel portion and the central channel portion can be seen
  • Figure 4 is a cross-sectional view taken along the line V-V in
  • Figure 1 in the illustrated inter-channel portion and the central channel portion in the alternative cross-sectional geometries of the fluid channel,
  • Figure 5 is a sectional view through a Turbinenschaufelwan- dung with a further according to the invention having formed ⁇ th fluid passage according to the present invention
  • FIG. 6 shows a sectional view through a turbine blade wall with a third embodiment of a fluid channel according to the present invention
  • FIG. 7 to 9 variants of the turbine blade wall shown in FIG. 6 in longitudinal section
  • FIG. 10 shows a longitudinal section through a turbine blade wall with a fourth embodiment of a fluid channel according to the present invention
  • Figure 11 is a cross-sectional view along lines A-A in Figures 6 and 10, in which
  • FIG. 12 shows a three-dimensional representation of the fluid channel illustrated in FIG. 10 in the transition region between the intermediate channel section and the central channel section,
  • Figure 13 is a schematic representation showing the position of
  • FIG. 14 shows a schematic representation which shows the detachment behavior of the cooling fluid in the diffuser in the case of conventional fluid ducts with a diffuser
  • Figure 15 is a schematic representation showing the vortex ⁇ formation of a cylindrical film cooling hole.
  • FIG. 1 shows a longitudinal section of a detail of a turbine blade wall 1 is shown, in which a fluid channel 2 is formed, through which a cooling fluid, such as Example ⁇ example cooling air from a cold-gas side of the turbine blade - here the interior of the turbine blade - to one of
  • a cooling fluid such as Example ⁇ example cooling air from a cold-gas side of the turbine blade - here the interior of the turbine blade - to one of
  • Hot gas flowing over the outer surface of the turbine blade wall 2, which forms a hot gas side of the turbine blade, can flow.
  • the fluid channel 2 has at its side facing end portion of an inflow channel portion 2a with a fluid inlet port 3, at its pointing to the hot gas side of the turbine blade wall end portion 1 a diffuser-like expanding Ausström- channel section 2b with a Fluidauslassö réelle 4 and between the inflow channel section 2a and the Ausström- channel section 2b a central Channel section 2 c, which defines a longitudinal axis X of the fluid channel 2 and over its length has a constant circular or oval cross-section on.
  • the fluid channel 2 has at its side facing end portion of an inflow channel portion 2a with a fluid inlet port 3, at its pointing to the hot gas side of the turbine blade wall end portion 1 a diffuser-like expanding Ausström- channel section 2b with a Fluidauslassö réelle 4 and between the inflow channel section 2a and the Ausström- channel section 2b a central Channel section 2 c, which defines
  • Longitudinal axis X of the fluid channel 2 encloses an acute angle with the surface of the turbine blade wall 1 overflowed by the hot gas, which is measured between the longitudinal axis X and the surface on the upstream side and the upstream side of the fluid channel.
  • an intermediate channel section 2d having a larger one
  • transition region between the intermediate channel section 2d, and the central channel portion 2c sharp out ⁇ forms, with the wall of the fluid channel 2 at the side of the fluid channel 2, which faces the cold-gas side, is straight, and facing the opposite, the hot gas side wall area a Shoulder surface 5 between the intermediate channel portion 2 d and the central channel portion 2 c is formed, which is perpendicular to the longitudinal axis X of the fluid channel 2.
  • the shoulder surface 5 2c form on which the cold-gas side facing Wan ⁇ dung region between the intermediate channel section 2d, and the central channel portion, then on the opposite, ie, to the hot gas side facing wall area the Wall of the fluid channel 2 in a straight line, that runs without Schulterbil ⁇ tion.
  • FIGS. 3 and 4 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 have 2d and the central Kanalab ⁇ section 2c each have a circular cross-section, wherein the diameter D of the intermediate channel section 2d is significantly larger than the diameter 2d of the central passage portion 2c. In the illustrated embodiment, this is
  • the cross-sectional area of the central passage portion 2c has a cross sectional area smaller by about 55% than the intermediate passage portion 2d.
  • the intermediate channel section 2d transitions rectilinearly into the central channel section 2c, while in the remaining peripheral regions the shoulder surface 5 is formed between the two channel sections 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 Kanalab ⁇ section 2 d, the shoulder surface 5 is present only at the upstream wall region of the fluid channel 2.
  • cooling air is flowed through during operation of the fluid passage 2 of a cooling fluid, the sharp-Kant ⁇ ge constriction results in the transition region between the intermediate channel section 2d, and the central channel portion 2c to the fact that the cooling fluid stream - as shown in Figure 13 - in diffuser-like 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 thus optimally contacts the outer surface after leaving the fluid channel 2. surface of the turbine blade wall 1, in order to protect them from the over ⁇ flowing hot gas.
  • FIG. 5 shows a similar fluid channel 2 in a turbine blade wall 1.
  • the fluid inlet opening 3 is formed in the end face of a bead 6 which protrudes inwards from the inner surface of the turbine blade wall 1, so that the cooling fluid enters the fluid channel 2 at the end entry.
  • FIG. 6 shows a further embodiment of a fluid channel 2 in a turbine blade wall 1.
  • This includes, in the same way as the fluid channel 2 according to FIG. 1, 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, one between the inflow channel section 2a and Outflow channel portion 2b lying central channel portion 2c with a constant over its length, circular cross section, and an intermediate channel portion 2d, which is formed between the inflow channel portion 2a and the central channel portion 2c.
  • the inflow channel section 2a and the intermediate channel section 2d are formed in the manner of a cylindrical bore with a diameter that is constant over the length, which is greater than the diameter of the central channel section 2c.
  • the longitudinal axis wel ⁇ surface is through the intermediate fluid passage 2d and the inflow fluid passage 2a is defined offset from the longitudinal axis X of the central passage portion 2c.
  • the on ⁇ arrangement is so made that 5 is formed on the side facing the cold gas side of the fluid channel 2 between the intermediate channel section 2d, and the central channel portion 2c a shoulder surface, while on the opposite, ie facing the hot gas side the Fluidkanalwan - Formation in the transition region between the intermediate channel section 2d and the central channel section 2c is rectilinear, so here is a steady transition from the intermediate channel section 2d takes place 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 can be seen in the cross section of FIG.
  • the shoulder surface can be formed on the side facing the hot gas side wall region of the fluid passage 2, whereas on the opposite, that is facing the cold-gas side the Fluidkanalwandung in the transition region between the intermediate channel portion 2d and the central Kanalab ⁇ cut 2c is straight.
  • FIGS. 7 and 8 Figure 7 can furthermore be seen that the plane in which the Schulterflä ⁇ surface 5 is located, including ⁇ with the nearest the hot gas side Wandungsbe reaching an angle ⁇ 90 °, so that a type of return jump is formed.
  • the shoulder surface 5 may include an angle ⁇ 90 ° with the cold gas side wall portion to form a recess, as shown in FIG.
  • the embodiment shown in Figure 6 is the
  • Outflow channel section 2b diffuser-like design.
  • the outflow channel section 2b as shown in Figure 10 ge ⁇ shows 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 and the central channel portion 2c and the
  • Outflow channel section 2b a bore smaller diameter ⁇ sers, wherein the bores are offset so that a shoulder surface 5 is formed in the transition region between the intermediate channel section 2d and the central channel section 2c on the downstream side of the Fluidkanalwandung. Due to the design of the fluid channel 2 according to Figures 6 and 10, the same effect is achieved in operation as by the configuration of the fluid channel 2 according to Figures 1 and 4. Due to the increased diameter of the fluid channel 2 in the inflow channel section 2a and intermediate channel section 2d the cooling fluid is initially delayed in the fluid channel 2 and then be ⁇ accelerated and deflected in such a way that a separation of the cooling fluid flow takes place in the region of the inclined shoulder surface 5 in the region of the upstream side of the Fluidkanalwandung.

Landscapes

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

Abstract

Aube de turbine destinée à une turbomachine, comprenant une paroi d'aube de turbine (1) et un canal fluidique (2) qui présente au niveau de sa partie d'extrémité orientée vers le côté froid, une section de canal d'entrée de flux (2a), au niveau de sa partie d'extrémité orientée vers le côté chaud de la paroi d'aube de turbine, une section de canal de sortie de flux (2b), entre les deux une section de canal centrale (2c) qui présente une section transversale circulaire ou ovale constante sur la longueur, et qui forme un angle aigu avec la surface de la paroi d'aube de turbine parcourue par du gaz chaud, et entre la section de canal d'entrée de flux et la section de canal centrale, une section de canal intermédiaire (2d) qui possède une surface de section transversale supérieure à celle de la section de canal centrale, la section de canal centrale se raccordant à la section de canal intermédiaire en formant une surface d'épaulement (5) intercalée entre elles, la surface d'épaulement étant formée au niveau d'une zone de paroi du canal fluidique, et la section de canal intermédiaire et la section de canal centrale fusionnant l'une dans l'autre de manière linéaire avec une hauteur d'épaulement faible au niveau de la zone de paroi opposée.
EP15760398.6A 2014-08-26 2015-08-21 Aube de turbine Not-in-force EP3155227B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14182277.5A EP2990605A1 (fr) 2014-08-26 2014-08-26 Aube de turbine
PCT/EP2015/069232 WO2016030289A1 (fr) 2014-08-26 2015-08-21 Aube de turbine

Publications (2)

Publication Number Publication Date
EP3155227A1 true EP3155227A1 (fr) 2017-04-19
EP3155227B1 EP3155227B1 (fr) 2019-01-02

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 Before (1)

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

Families Citing this family (7)

* 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
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
US11732590B2 (en) * 2021-08-13 2023-08-22 Raytheon Technologies Corporation Transition section for accommodating mismatch between other sections of a cooling aperture in a turbine engine component
US12006837B2 (en) * 2022-01-28 2024-06-11 Rtx Corporation Ceramic matrix composite article and method of making the same
JP2025117176A (ja) * 2024-01-30 2025-08-12 本田技研工業株式会社 壁部材及びその製造方法

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
GB2244673B (en) * 1990-06-05 1993-09-01 Rolls Royce Plc A perforated sheet and a method of making the same
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
JP4898253B2 (ja) * 2005-03-30 2012-03-14 三菱重工業株式会社 ガスタービン用高温部材
US8128366B2 (en) 2008-06-06 2012-03-06 United Technologies Corporation Counter-vortex film cooling hole design
US20120107135A1 (en) * 2010-10-29 2012-05-03 General Electric Company Apparatus, systems and methods for cooling the platform region of turbine rotor blades
GB201103176D0 (en) * 2011-02-24 2011-04-06 Rolls Royce Plc Endwall component for a turbine stage of a gas turbine engine
EP2584147A1 (fr) 2011-10-21 2013-04-24 Siemens Aktiengesellschaft Aube de turbine refroidie par film pour une turbomachine
JP5982807B2 (ja) 2011-12-15 2016-08-31 株式会社Ihi タービン翼
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

Also Published As

Publication number Publication date
JP2017530291A (ja) 2017-10-12
WO2016030289A1 (fr) 2016-03-03
CN106574507B (zh) 2018-05-11
EP2990605A1 (fr) 2016-03-02
US9915150B2 (en) 2018-03-13
CN106574507A (zh) 2017-04-19
EP3155227B1 (fr) 2019-01-02
JP6328847B2 (ja) 2018-05-23
US20170268347A1 (en) 2017-09-21

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