EP3564484A1 - Paroi de composant d'un composant à gaz chaud - Google Patents

Paroi de composant d'un composant à gaz chaud Download PDF

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Publication number
EP3564484A1
EP3564484A1 EP18170851.2A EP18170851A EP3564484A1 EP 3564484 A1 EP3564484 A1 EP 3564484A1 EP 18170851 A EP18170851 A EP 18170851A EP 3564484 A1 EP3564484 A1 EP 3564484A1
Authority
EP
European Patent Office
Prior art keywords
wall
inlet
cavity
outlet
openings
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Withdrawn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
EP18170851.2A
Other languages
German (de)
English (en)
Inventor
Ole Geisen
Michael Hajduk
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
Siemens Corp
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
Priority to EP18170851.2A priority Critical patent/EP3564484A1/fr
Priority to US17/048,584 priority patent/US11220915B2/en
Priority to EP19720433.2A priority patent/EP3762586B1/fr
Priority to PCT/EP2019/059392 priority patent/WO2019211082A1/fr
Publication of EP3564484A1 publication Critical patent/EP3564484A1/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Withdrawn legal-status Critical Current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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • 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
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • 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
    • F05D2260/231—Preventing heat transfer
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a component wall of a hot gas component for a gas turbine, which is configured as a double-walled hotter outer wall and a colder during operation inner wall and its interposed interior is divided by itself between the inner wall and the outer wall extending partitions, wherein by in the inner wall arranged inlet openings a coolant can be flowed into the interior and can be flowed out of the interior through outlet openings arranged in the outer wall.
  • Such a component wall comes, for example, according to the EP 0 954 680 B1 used in a turbine blade.
  • the component wall is that of an airfoil, which is provided aerodynamically curved for deflecting a hot gas flowing in a gas turbine.
  • heat transfer elements are provided inside the hollow component wall with which the heated during operation outer wall can be cooled due to the flow through the hollow component wall with cooling air.
  • the object of the invention is to provide a component wall of a hot gas component for a gas turbine, which has a longer service life.
  • the object is achieved by such a component wall having at least a first cavity in the interior, which is connected directly to at least one of the inlet openings as an inlet cavity without being directly connected to outlet openings and immediately adjacent to the at least one inlet cavity at least one second cavity is provided, which is directly connected as an outlet cavity only with at least one of the outlet openings without being directly connected to inlet openings and that, forming a flow path which the relevant inlet cavity from the adjacent outlet cavity dividing partition at least a passage opening for the passage of the coolant from the respective inlet cavity into the outlet cavity.
  • the interior is subdivided into at least one inlet cavity, preferably a plurality of inlet cavities, and into at least one outlet cavity, preferably a plurality of outlet cavities, to each of which specific openings are assigned: inlet openings only adjoin the inlet cavity, however no outlet openings on and at the outlet cavity are adjacent only outlet openings but no inlet openings.
  • the inlet opening is preferably designed for impingement cooling of the hotter outer wall in operation, whereby a particularly effective reduction of the temperature of the outer wall is caused.
  • the partition wall having at least one passage opening for impingement irradiation of the inner wall which is cooler during operation is preferably designed in the region of the outlet cavity with coolant heated during operation.
  • the invention pursues the approach of not only reducing the temperature of the outer wall as much as possible in order to reduce the temperature gradient between the inner wall and the outer wall.
  • the invention further pursues the approach of increasing the temperature of the inner wall in order to reduce the temperature gradient of the entire component wall even from the lower material temperature and thus to approach the temperatures of the inner wall and outer wall to such an extent that life-shortening stresses from thermal expansion are reduced.
  • the invention turns away from the idea of avoiding the heating of the inner wall.
  • the temperature gradient between the inner wall and the outer wall can be further reduced if elements for intensifying the heat transfer are provided on an inner surface of the inner wall delimiting the outlet cavity.
  • the component wall comprises not only a single inlet cavity and a single outlet cavity, but a plurality of inlet cavities and a plurality of outlet cavities and a plurality of dividing the interior accordingly dividing partitions and also a plurality of inlet openings and a plurality of outlet openings, such that along a transverse extent the inlet wall cavities and outlet cavities are always arranged alternately, wherein at least every second partition dividing the interior accordingly each having at least one through hole, preferably a plurality of through holes for conveying coolant from the respective inlet cavity into the immediately adjacent outlet cavity ,
  • This embodiment serves for a large-scale approximation of the temperatures of the inner wall and outer wall while simultaneously achieving a sufficiently cooled outer wall.
  • the outlet cavity is by two partitions of two on both sides limited adjacent inlet cavities and arranged in only one of the two respective partitions through holes. In this way, a combination of coolant flows from two inlet cavities flanking a respective outlet cavity can be avoided, if appropriate. Thus, for each pairing of an outlet cavity with an inlet cavity, there is a dedicated coolant flow path.
  • each of the inlet cavities each having a plurality of inlet openings and each of the outlet cavities, each having a plurality Outlet openings directly connected and arranged in the respective partitions in between a plurality of through holes.
  • the inlet openings and the outlet openings are preferably arranged along this longitudinal extent of the component wall offset from the passage openings located in the flow path.
  • the alternately arranged inlet cavities and outlet cavities are each designed triangular to form a plurality of flow paths and at the same time are arranged overlapping each other.
  • the inlet cavities abut with a corner of their triangular contour on the inner wall, whereas their corner opposite this edge is part of the outer wall.
  • the outlet cavity or cavities are inversely oriented: one corner of the triangular outlet cavities abuts the outside wall, whereas an edge of the triangular one opposite this corner designed outlet cavity then form part of the inner wall.
  • the inner wall largely limits the outlet cavities
  • the outer wall largely limits the inlet cavities so that the inlet cavities are more likely to be punctiformly adjacent the inner wall and the outlet cavities are closer to the outer wall.
  • This arrangement in particular if it is provided repetitively, has the advantage that the outer wall can be largely impact-cooled by the inlet cavities.
  • the inner wall can be tempered by the preferably impact radiation of the inner wall due to the arranged in the partition through holes with an already heated due to the impingement cooling of the outer wall coolant such that the temperature of the inner wall approaches the temperature of the outer wall. This extends the life of the component wall of a hot gas component for a gas turbine.
  • this geometry increases the rigidity of the component wall.
  • a hot gas component has a corresponding component wall.
  • the hot gas component may, for example, be a turbine blade, designed as a guide blade or as a moving blade.
  • the component wall may be part of the blade and / or part of the platform.
  • the hot gas component can also be designed as a ring segment or as a heat shield of a combustion chamber. Other applications are also conceivable.
  • the component wall is monolithic.
  • Such a component wall can be manufactured by additive manufacturing methods, and in particular by selective laser melting. In contrast to previous impact-cooled component walls, outer wall and impingement cooling wall are produced simultaneously.
  • FIG. 1 shows a perspective view of a section through a component wall 10 of the invention.
  • the component wall 10 is part of a hot gas component, not shown, which can be used in a gas turbine in the hot gas path or to the limitation.
  • the component wall 10 is designed double-walled and has a hotter during operation outer wall 12 and a colder inner wall 14 during operation.
  • the terms "hotter” and “colder” refer to the other wall: the outer wall is higher in operation Temperature than the inner wall and is thus hotter, whereas in operation, the inner wall has a lower temperature than the outer wall. Consequently, the inner wall is the colder.
  • an interior space is arranged, which is basically divided by itself between the inner wall 14 and the outer wall 12 extending partitions 16.
  • the component wall 10 is designed in sandwich construction.
  • the partition walls 16 disposed in the interior are arranged obliquely, so that sets a zigzag-like course. This results in cross-sectionally triangular cavities 22, 24.
  • the cavities 22 directly connected to the inlet openings 18 are referred to as inlet cavities, whereas the cavities 24 connected directly to the outlet openings 20 are referred to as outlet cavities.
  • the inlet cavities 22 are in direct fluid communication only with the inlet ports 18 and the passageways 26.
  • the outlet cavities 24 communicate directly only with the outlet openings 20 and the passage openings 26.
  • the term "direct" means immediately adjacent to each other.
  • the shape of the inlet cavities 22 and outlet cavities 24 are in the shape of an isosceles triangle so that they can be arranged complementarily.
  • a hot working medium AM flows along the outwardly facing surface 13 of the outer wall 12.
  • a coolant KM stands on a surface 15 of the inner wall 14 facing away from the interior of the component wall 10.
  • this flows the surface 15 pending coolant KM via the inlet openings 18 with formation of individual coolant jets in the inlet cavity 22.
  • the outer wall 12 is then crimped, which lowers the temperature level of the outer wall 12 over a large area and heats the coolant KM.
  • the coolant KM flows to the staggered passage openings 26 and flows through them into one of the immediately adjacent outlet cavities 24.
  • FIG. 2 shows the section through the hot gas component according to the first embodiment along the section line II-II.
  • elements 28 for intensifying the heat transfer are provided on the inner surfaces 17, delimiting the outlet cavities 24, of the inner wall 14. These elements 28 may, for example, be in the form of turbulators, rib-shaped elevations or also of pedestals. The application of these elements further contributes to the reduction of the temperature gradient between inside and outside.
  • FIG. 3 shows one too FIG. 1 Analog representation of a component wall 10 according to a second embodiment. Not each of the inlet cavities 22 dividing the inlet cavities 22 from the outlet cavities 24 extends obliquely from the inner wall 14 to the outer wall 12. According to the embodiment shown here, each second partition wall 16 is perpendicular to the inner walls 14 and outer walls 12, while the rest are arranged at an angle. In contrast to the first embodiment with isosceles Triangular shapes according to the second embodiment in FIG. 3 the pairs summarized inlet cavities 22 and outlet cavities 24 each have a substantially rectangular triangular shape, the paired form a rectangular shape.
  • Both embodiments have in common that the inlet openings 18 and the outlet openings 20 are arranged in a corner region of the triangles, whereas the bulging surfaces of the inlet cavities 22 then parts of the outer wall 12 and the bulging surfaces of the outlet cavities 22 then parts of the inner wall 14 are. In this way, in each case the greatest possible area for impact radiation from outer wall 12 or inner wall 14 can be brought about and as far as possible avoid temperature gradients along inner wall 14 or along outer wall 12.
  • FIG. 4 shows the arrangement of rib-shaped turbulators 28 on the outlet cavity 24 defining inner surfaces 17 of the inner wall 14th
  • FIGS. 5 and 6 show a portion of an aerodynamically curved airfoil 30 of a turbine blade 32 in a perspective view with a section through the blade profile. Shown is on the one hand, the pressure side wall 34 of the blade 30 and the front edge 36.
  • the blade 30 further includes a suction side wall and a trailing edge (both not shown).
  • the inlet cavities 22 and the outlet cavities 24 extend along a profile centerline (not shown).
  • the pressure side wall 34 and the suction side wall enclose a supply cavity 38 arranged in the interior of the blade 30, to which the coolant KM is supplied via a blade root, not shown.
  • This can, as already described above, via inlet openings 18 bounce in the interior of the component wall 10 and the pressure side wall 34.
  • the coolant KM leaves the component wall 10 or the turbine blade and then mixes with the working medium AM flowing around the blade 30.
  • a comparatively thin component wall 10 can be provided by means of the additive method of selective laser melting.
  • Wall thicknesses in the order of 0.5 mm are conceivable.
  • the walls configured in such a hollow manner allow a surface impingement cooling of the outer wall 12, without at the same time the life shortening thermo-mechanical stresses due to an inadmissibly high temperature gradient occur. It can thus be realized wall thicknesses of the order of about 2.5 mm for the component wall 10 according to the invention.
  • the invention relates to a component wall 10 of a hot gas component for a gas turbine, which configured double-walled in operation a hotter outer wall 12 and a colder during operation inner wall 14 and its interposed interior divided by itself between the inner wall and the outer wall extending partitions 16 is, can be flowed through by arranged in the inner wall 14 inlet openings 18, a coolant KM in the interior and can flow out of the interior through arranged in the outer wall 12 outlet openings 20.
  • inlet cavity 22 is directly connected to at least one of the inlet openings 18 without being directly connected to outlet openings 20 and immediately adjacent to the at least one inlet cavity 22 at least one second cavity is provided, which is directly connected as an outlet cavity 24 only with at least one of the outlet openings 20 without being directly connected to inlet openings 18, and that the respective inlet cavity and the adjacent outlet cavity 24 dividing partition wall 16 has at least one passage opening 26 for the passage of the coolant KM from the respective inlet cavity 22 into the outlet cavity 24.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP18170851.2A 2018-05-04 2018-05-04 Paroi de composant d'un composant à gaz chaud Withdrawn EP3564484A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP18170851.2A EP3564484A1 (fr) 2018-05-04 2018-05-04 Paroi de composant d'un composant à gaz chaud
US17/048,584 US11220915B2 (en) 2018-05-04 2019-04-12 Component wall of a hot gas component
EP19720433.2A EP3762586B1 (fr) 2018-05-04 2019-04-12 Paroi de composant à gaz chaud
PCT/EP2019/059392 WO2019211082A1 (fr) 2018-05-04 2019-04-12 Paroi de composant d'un gaz chaud

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18170851.2A EP3564484A1 (fr) 2018-05-04 2018-05-04 Paroi de composant d'un composant à gaz chaud

Publications (1)

Publication Number Publication Date
EP3564484A1 true EP3564484A1 (fr) 2019-11-06

Family

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP18170851.2A Withdrawn EP3564484A1 (fr) 2018-05-04 2018-05-04 Paroi de composant d'un composant à gaz chaud
EP19720433.2A Active EP3762586B1 (fr) 2018-05-04 2019-04-12 Paroi de composant à gaz chaud

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP19720433.2A Active EP3762586B1 (fr) 2018-05-04 2019-04-12 Paroi de composant à gaz chaud

Country Status (3)

Country Link
US (1) US11220915B2 (fr)
EP (2) EP3564484A1 (fr)
WO (1) WO2019211082A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11572801B2 (en) * 2019-09-12 2023-02-07 General Electric Company Turbine engine component with baffle
US11371702B2 (en) * 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine

Citations (5)

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Publication number Priority date Publication date Assignee Title
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
EP0954680B1 (fr) 1996-12-02 2002-02-06 Siemens Aktiengesellschaft Aube de turbine et son utilisation dans un systeme de turbine a gaz
US20050150632A1 (en) * 2004-01-09 2005-07-14 Mayer Robert R. Extended impingement cooling device and method
EP1990507A1 (fr) * 2006-03-02 2008-11-12 IHI Corporation Structure de refroidissement par contact
US9683444B1 (en) * 2013-11-18 2017-06-20 Florida Turbine Technologies, Inc. Multiple wall impingement plate for sequential impingement cooling of a turbine hot part

Family Cites Families (3)

* Cited by examiner, † Cited by third party
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US11220915B2 (en) 2022-01-11
EP3762586A1 (fr) 2021-01-13
US20210156262A1 (en) 2021-05-27
EP3762586B1 (fr) 2022-03-30

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