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EP3762586B1 - Paroi de composant à gaz chaud - Google Patents

Paroi de composant à gaz chaud Download PDF

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Publication number
EP3762586B1
EP3762586B1 EP19720433.2A EP19720433A EP3762586B1 EP 3762586 B1 EP3762586 B1 EP 3762586B1 EP 19720433 A EP19720433 A EP 19720433A EP 3762586 B1 EP3762586 B1 EP 3762586B1
Authority
EP
European Patent Office
Prior art keywords
wall
inlet
outlet
cavity
component
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.)
Active
Application number
EP19720433.2A
Other languages
German (de)
English (en)
Other versions
EP3762586A1 (fr
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 Energy Global GmbH and Co KG
Original Assignee
Siemens Energy Global GmbH and Co KG
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
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Publication of EP3762586A1 publication Critical patent/EP3762586A1/fr
Application granted granted Critical
Publication of EP3762586B1 publication Critical patent/EP3762586B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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 double-walled and comprises an outer wall that is hotter during operation and an inner wall that is colder during operation and the interior space of which is arranged between them and is fundamentally divided by partition walls extending between the inner wall and the outer wall, with the inner wall being divided by the inner wall arranged inlet openings, a coolant can flow into the interior and can flow out of the interior through outlet openings arranged in the outer wall.
  • Such a component wall comes, for example, according to EP 0 954 680 B1 used in a turbine blade.
  • the component wall is that of a blade, which is provided in an aerodynamically curved manner for deflecting a hot gas flowing in a gas turbine.
  • heat transfer elements are provided, with which the outer wall, which is heated during operation, can be cooled due to the cooling air flowing through the hollow component wall.
  • a cascaded impingement cooling in a heat shield also reveals the U.S. 4,573,865 .
  • the object of the invention is to specify a component wall of a hot-gas component for a gas turbine that has a longer service life.
  • the object is achieved by such a component wall that has at least one first cavity in the interior, which as an inlet cavity is only directly connected to at least one of the inlet openings without being directly connected to outlet openings and that is directly next to the at least one inlet cavity at least one second cavity is provided, which as an outlet cavity is only directly connected to at least one of the outlet openings without being directly connected to inlet openings, so that the dividing wall dividing the relevant inlet cavity from the outlet cavity adjacent thereto at least has a passage opening for conducting the coolant from the relevant inlet cavity into the outlet cavity, and that at least one means is provided which, when the component wall is used as intended, causes a targeted increase in the material temperature of the inner wall rt.
  • the interior is therefore divided into at least one inlet cavity, preferably several inlet cavities, and at least one outlet cavity, preferably several outlet cavities, to which specific openings are assigned: only inlet openings adjoin the inlet cavity, but no outlet openings on and at the outlet cavity only outlet openings but no inlet openings border.
  • the inlet opening is preferably designed for impact cooling of the outer wall, which is hotter during operation, resulting in a particularly effective reduction in the temperature of the outer wall.
  • the partition wall having at least one through-opening is designed for impact irradiation of the inner wall, which is cooler during operation, in the area of the outlet cavity with coolant heated during operation.
  • the through openings arranged in the partition wall are not oriented towards the outer wall but towards the inner wall, so that as impingement openings they direct the heated coolant to the inner wall in the form of jets and can thus increase its temperature, in particular compared to a component wall without such measures.
  • the invention therefore pursues the approach of not only reducing the temperature of the outer wall as far as possible in order to reduce the temperature gradient between the inner wall and the outer wall.
  • the invention also pursues the approach of increasing the temperature of the inner wall in order to reduce the temperature gradient of the entire component wall from the lower material temperature and thus approximate the temperatures of the inner wall and outer wall to such an extent that life-shortening stresses from thermal expansion are reduced. Consequently, the invention turns away from the idea of avoiding the heating of the inner wall. Consequently, the invention proposes increasing the temperature of the inner wall in a targeted manner using at least one means provided for this purpose.
  • the component wall is monolithic, ie the inner wall, outer wall and partition walls are in one piece.
  • a component wall can be manufactured by additive manufacturing methods, and in particular by selective laser melting.
  • the outer wall, partition walls and impingement cooling wall are thus produced simultaneously.
  • the temperature-related material stresses can occur to an undesirably high degree, so that the service life, in particular of monolithic components, can be significantly increased with the invention.
  • thermomechanical stresses in the component wall can be further reduced if elements for stimulating the heat transfer are provided as means on an inner surface of the inner wall delimiting the outlet cavity. These can then also be used for targeted heating of the comparatively colder inner wall, which leads to the result mentioned.
  • the means for increasing the material temperature of the inner wall i.e. the impingement of the inner wall with heated coolant or the elements for adapting the heat transfer can be used alternatively or in addition to one another.
  • the component wall does not just include a single inlet cavity and a single outlet cavity, but rather a plurality of inlet cavities and a plurality of outlet cavities as well as a plurality of partitions dividing the interior space accordingly and also a plurality of inlet openings and a plurality of outlet openings such that along a transverse extension of the component wall, inlet cavities and outlet cavities are always arranged alternately, with at least every second partition wall dividing the interior space accordingly having at least one through-opening, preferably several through-openings for passing on coolant from the relevant inlet cavity into the immediately adjacent outlet cavity .
  • This configuration serves to equalize the temperatures over a large area of the inner wall and outer wall while at the same time achieving a sufficiently cooled outer wall.
  • the outlet cavity is delimited by two dividing walls of two inlet cavities adjacent on both sides and through-openings are arranged in only one of the two relevant dividing walls. In this way, a merging of coolant flows from two inlet cavities flanking a relevant outlet cavity can be avoided, if expedient. A dedicated flow path for coolant thus results for each pairing of an outlet cavity with an inlet cavity.
  • each of the inlet cavities has a plurality of inlet openings and each of the outlet cavities has a plurality of them Outlet openings connected directly and arranged in between each several passage openings in the relevant partitions.
  • the inlet openings or the outlet openings are preferably arranged offset to the through-openings lying in the flow path along this longitudinal extent of the component wall.
  • the configuration in which the alternately arranged inlet cavities and outlet cavities are each designed in a triangular manner to form a plurality of flow paths and are at the same time arranged to overlap one another is particularly preferred.
  • the or the outlet cavities are oriented the other way round: one corner of the triangular outlet cavities rests against the outer wall, whereas an edge of the triangular outlet cavity that is opposite this corner then represents part of the inner wall.
  • the inner wall largely delimits the outlet cavities and the outer wall largely delimits the inlet cavities, so that the inlet cavities tend to adjoin the inner wall at points and the outlet cavities adjoin the outer wall at points.
  • This arrangement in particular if it is provided repeatedly, has the advantage that the outer wall can be impingement-cooled over a large area through the inlet cavities.
  • the inner wall can be tempered by the preferably impingement irradiation of the inner wall due to the passage openings arranged in the partition wall with a coolant already heated due to the impingement cooling of the outer wall in such a way that the temperature of the inner wall approaches the temperature of the outer wall. This extends the service 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 particularly preferably has a corresponding component wall.
  • the hot-gas component can be, for example, a turbine blade designed as a guide blade or as a moving blade.
  • the component wall can be part of the airfoil and/or also 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.
  • FIG 1 shows a perspective view of a section through a component wall 10 according to the invention.
  • the component wall 10 is part of a hot gas component, not shown in any more detail, which can be used in a gas turbine in its hot gas path or to limit it.
  • the component wall 10 is double-walled and has an outer wall 12 that is hotter during operation and an inner wall 14 that is colder during operation.
  • the terms "hot” and “colder” each refer to the other wall: the outer wall has a higher temperature than the inner wall during operation and is therefore hotter, whereas during operation, the inner wall has a lower temperature than the outer wall. Consequently, the inner wall is the colder.
  • An interior space is arranged between the outer wall 12 and the inner wall 14 and is basically subdivided by partition walls 16 extending between the inner wall 14 and the outer wall 12 .
  • partition walls 16 extending between the inner wall 14 and the outer wall 12 .
  • a multiplicity of inlet openings 18 are provided in the inner wall 14 and a multiplicity of outlet openings 20 are provided in the outer wall 12 .
  • the component wall 10 is designed in a sandwich construction.
  • the partition walls 16 arranged in the interior are arranged at an angle, so that a zigzag-like progression is established.
  • the cavities 22 directly connected to the inlet openings 18 are referred to as inlet cavities, whereas the cavities 24 directly connected 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 through ports 26 .
  • the outlet cavities 24 communicate directly only with the outlet openings 20 and the through-openings 26 .
  • the term "directly" means immediately adjacent to one another.
  • the shape of the inlet cavities 22 and outlet cavities 24 correspond to the shape of an isosceles triangle, so that they can be arranged in a complementary manner.
  • a hot working medium AM flows along the outward-facing surface 13 of the outer wall 12 .
  • a coolant KM is present on a surface 15 of the inner wall 14 facing away from the interior of the component wall 10 .
  • the coolant KM present on the surface 15 flows through the inlet openings 18 with the formation of individual coolant jets in the inlet cavity 22.
  • the outer wall 12 is then impact-cooled, which lowers the temperature level of the outer wall 12 over a large area and heats up the coolant KM.
  • the coolant KM then flows to the passage openings 26 which are arranged offset and flows through them into one of the immediately adjacent outlet cavities 24 .
  • figure 2 shows the section through the hot gas component according to the first embodiment along the section line II-II.
  • elements 28 for facilitating the heat transfer are provided on the inner surfaces 17 of the inner wall 14 delimiting the outlet cavities 24 .
  • These elements 28 can be present, for example, in the form of turbulators, rib-shaped elevations or also bases. The application of these elements further contributes to reducing the temperature gradient between inside and outside. Whether the amplification of the heat transfer occurs due to the enlarged surface and/or due to the more turbulent flow is basically irrelevant. Both variants have their own advantages.
  • figure 3 shows one to figure 1 analog representation of a component wall 10 according to a second embodiment.
  • each of the partitions 16 dividing the inlet cavities 22 from the outlet cavities 24 extends in an oblique direction from the inner wall 14 to the outer wall 12.
  • every second partition 16 is perpendicular to the inner walls 14 and outer walls 12 down, while the rest are arranged obliquely.
  • the inlet cavities 22 and outlet cavities 24 which can be combined in pairs each have a substantially right-angled triangular shape which, when combined in pairs, form a rectangular shape.
  • Both exemplary 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 impact-blasted surfaces of the inlet cavities 22 are then parts of the outer wall 12 and the impact-blasted surfaces of the outlet cavities 22 are then parts of the inner wall 14 are.
  • the largest possible area can be brought about for impact irradiation of the outer wall 12 or inner wall 14 and thus temperature gradients along the inner wall 14 or along the outer wall 12 can be largely avoided.
  • figure 4 shows the arrangement of rib-shaped turbulators 28 on the inner surface 17 of the inner wall 14 delimiting the outlet cavity 24.
  • the figures 5 and 6 12 show a part of an aerodynamically curved airfoil 30 of a turbine blade 32 in a perspective view with a section through the blade profile.
  • the pressure side wall 34 of the airfoil 30 and its leading edge 36 are shown.
  • the airfoil 30 also 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 center line (not shown).
  • the pressure side wall 34 and the suction side wall enclose a supply cavity 38 which is arranged in the interior of the blade leaf 30 and to which the coolant KM is supplied via a blade root (not shown).
  • this can be done via inlet openings 18 flow into the interior of the component wall 10 or the pressure side wall 34 with impact cooling.
  • the coolant KM then flows to the through openings 26 and then passes into the outlet cavity 24 from where it flows to the outlet openings 20 . Through this, the coolant KM leaves the component wall 10 or the turbine blade and then mixes with the working medium AM flowing around the blade leaf 30 .
  • a comparatively thin component wall 10 can be provided with the aid of the additive method of selective laser melting.
  • Wall thicknesses in the order of 0.5 mm are conceivable.
  • the walls can be designed so that they are hollow, allowing surface impingement cooling of the outer wall 12 without the occurrence of thermo-mechanical stresses that shorten the service life at the same time due to an impermissibly high temperature gradient. Wall thicknesses in the order of about 2.5 mm can thus be realized for the component wall 10 according to the invention.
  • the component wall 10 which is designed in a monolithic sandwich construction, leads to a more homogeneous temperature distribution over the entire structure in addition to a lower overall metal average temperature and thus to lower thermal stresses.
  • the sandwich geometry effectively stiffens the component and reduces its weight.
  • the invention relates to a component wall 10 of a hot gas component for a gas turbine, which is double-walled and comprises an outer wall 12 that is hotter during operation and an inner wall 14 that is colder during operation and the latter in between arranged interior is fundamentally subdivided by partition walls 16 extending between the inner wall and the outer wall, wherein a coolant KM can flow into the interior through inlet openings 18 arranged in the inner wall 14 and out of the interior through outlet openings 20 arranged in the outer wall 12.
  • the inlet cavity 22 is only directly connected to at least one of the inlet openings 18 without being directly connected to outlet openings 20, and that directly next to the at least one inlet cavity 22 at least one second cavity is provided, which as outlet cavity 24 is only directly connected to at least one of the outlet openings 20 without being directly connected to inlet openings 18, and that the partition wall dividing the relevant inlet cavity and the outlet cavity 24 adjacent thereto 16 has at least one through-opening 26 for conducting the coolant KM out of the relevant 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)

Claims (10)

  1. Paroi (10) d'un élément pour gaz chaud d'une turbine à gaz, qui, conformée en double paroi, comprend une paroi (12) extérieure plus chaude en fonctionnement et une paroi (14) intérieure plus froide en fonctionnement et dont l'espace intérieur disposé entre elles est subdivisé fondamentalement par des cloisons (16) s'étendant entre la paroi intérieure et la paroi extérieure,
    dans laquelle un fluide (KM) de refroidissement peut entrer dans l'espace intérieur par des ouvertures (18) d'entrée de la paroi (14) intérieure et peut sortir de l'espace intérieur par des ouvertures (20) de sortie de la paroi (12) extérieure, dans laquelle il est prévu dans l'espace intérieur au moins une première cavité, qui communique directement, en tant que cavité (22) d'entrée, seulement avec au moins l'une des ouvertures (18) d'entrée, sans communiquer directement avec des ouvertures (20) de sortie et
    dans laquelle juste à côté de la au moins une cavité (22) d'entrée est prévue au moins une deuxième cavité, qui, en tant que cavité (24) de sortie, communique directement seulement avec au moins l'une des ouvertures (20) de sortie sans communiquer directement avec des ouvertures (18) d'entrée, et dans laquelle la cloison (16) subdivisant la cavité d'entrée concernée de la cavité (24) de sortie qui en est voisine a au moins une ouverture (26) de passage pour le passage du fluide (KM) de refroidissement de la cavité (22) d'entrée concernée à la cavité (24) de sortie, caractérisée en ce qu'il est prévu au moins un moyen d'élévation de la température du matériau de la paroi intérieure et en ce que la paroi de l'élément à double paroi est conformée de manière monolithique.
  2. Paroi (10) d'élément suivant la revendication 1,
    qui comprend plusieurs cavités (22) d'entrée et plusieurs cavités (24) de sortie ainsi que plusieurs cloisons (16) subdivisant l'espace intérieur ainsi qu'également plusieurs ouvertures (18) d'entrée et plusieurs ouvertures (20) de sortie, de manière à ce que
    suivant une étendue transversale de la paroi de l'élément, des cavités (22) d'entrée et des cavités (24) de sortie soient disposées en alternance les unes avec les autres et au moins une cloison (16) sur deux subdivisant l'espace intérieur a respectivement au moins une ouverture (26) de passage pour l'acheminement du fluide (KM) de refroidissement de la cavité (22) d'entrée concernée à la cavité (24) de sortie immédiatement voisine.
  3. Paroi (10) suivant la revendication 1 ou 2,
    dans laquelle la cavité (22) concernée et la au moins une ouverture (18) d'entrée qui lui est associée sont conformées pour le refroidissement par rebondissement de la paroi (12) extérieure plus chaude en fonctionnement.
  4. Paroi (10) suivant la revendication 1, 2 ou 3,
    dans laquelle comme moyen la cloison (16) ayant au moins une ouverture (26) de passage est conformée pour la projection par rebondissement sur la paroi (14) intérieure plus froide en fonctionnement dans la région de la cavité (24) de sortie du fluide (KM) de refroidissement chauffé en fonctionnement.
  5. Paroi (10) suivant l'une des revendications précédentes, dans laquelle il est prévu comme moyen sur une surface intérieure, délimitant la cavité (24) de sortie, de la paroi (14) intérieure des éléments (28) pour amorcer le transfert de chaleur.
  6. Paroi (10) suivant l'une des revendications précédentes, dans laquelle la cavité (24) de sortie est séparée par deux cloisons (16) de deux cavités d'entrée voisines des deux côtés et en ce que des ouvertures (26) de passage sont disposées seulement dans l'une des deux cloisons (16) concernée.
  7. Paroi (10) suivant l'une des revendications précédentes, dans laquelle chacune des cavités (22) d'entrée communique directement avec respectivement plusieurs ouvertures (18) d'entrée et chacune des cavités (22) de sortie avec respectivement plusieurs ouvertures (20) de sortie et dans laquelle respectivement plusieurs ouvertures (26) de passage sont ménagées dans les cloisons (16) concernées.
  8. Paroi (10) suivant l'une des revendications précédentes, dans laquelle les cavités (22) d'entrée et les cavités (24) de sortie disposées en alternance sont conformées triangulairement en coupe de paroi en formant plusieurs trajets d'écoulement et sont disposées au moins en partie à chevauchement les unes avec les autres.
  9. Paroi (10) suivant l'une des revendications précédentes,
    qui est fabriquée par un procédé additif.
  10. Elément pour gaz chaud comprenant une paroi (10),
    qui est conformé suivant l'une des revendications précédentes.
EP19720433.2A 2018-05-04 2019-04-12 Paroi de composant à gaz chaud Active EP3762586B1 (fr)

Applications Claiming Priority (2)

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
PCT/EP2019/059392 WO2019211082A1 (fr) 2018-05-04 2019-04-12 Paroi de composant d'un gaz chaud

Publications (2)

Publication Number Publication Date
EP3762586A1 EP3762586A1 (fr) 2021-01-13
EP3762586B1 true EP3762586B1 (fr) 2022-03-30

Family

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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 Before (1)

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

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

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* 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

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
JP4027430B2 (ja) 1996-12-02 2007-12-26 シーメンス アクチエンゲゼルシヤフト タービン翼並びにガスタービン設備におけるその使用
US7270175B2 (en) * 2004-01-09 2007-09-18 United Technologies Corporation Extended impingement cooling device and method
CA2644099C (fr) * 2006-03-02 2013-12-31 Ihi Corporation Structure de refroidissement par contact
EP3049625A4 (fr) * 2013-09-18 2017-07-19 United Technologies Corporation Procédé de fabrication pour une pale contenant un déflecteur
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
DE102015213090A1 (de) * 2015-07-13 2017-01-19 Siemens Aktiengesellschaft Schaufel für eine Strömungskraftmaschine und Verfahren zu deren Herstellung
WO2019057743A1 (fr) * 2017-09-25 2019-03-28 Siemens Aktiengesellschaft Aubage d'aube de turbine

Also Published As

Publication number Publication date
US20210156262A1 (en) 2021-05-27
US11220915B2 (en) 2022-01-11
EP3762586A1 (fr) 2021-01-13
EP3564484A1 (fr) 2019-11-06
WO2019211082A1 (fr) 2019-11-07

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