EP3762586A1 - Component wall of a hot gas component - Google Patents
Component wall of a hot gas componentInfo
- Publication number
- EP3762586A1 EP3762586A1 EP19720433.2A EP19720433A EP3762586A1 EP 3762586 A1 EP3762586 A1 EP 3762586A1 EP 19720433 A EP19720433 A EP 19720433A EP 3762586 A1 EP3762586 A1 EP 3762586A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- cavity
- inlet
- outlet
- 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.)
- Granted
Links
- 238000005192 partition Methods 0.000 claims abstract description 27
- 239000002826 coolant Substances 0.000 claims abstract description 25
- 238000001816 cooling Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 6
- 238000012546 transfer Methods 0.000 claims description 6
- 239000000654 additive Substances 0.000 claims description 3
- 230000000996 additive effect Effects 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 2
- 230000008901 benefit Effects 0.000 description 6
- 238000013459 approach Methods 0.000 description 4
- 238000010276 construction Methods 0.000 description 4
- 230000005855 radiation Effects 0.000 description 4
- 230000035882 stress Effects 0.000 description 4
- 108090000623 proteins and genes Proteins 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 238000004904 shortening Methods 0.000 description 2
- 230000000930 thermomechanical effect Effects 0.000 description 2
- 241000272517 Anseriformes Species 0.000 description 1
- 241001282736 Oriens Species 0.000 description 1
- 238000005267 amalgamation Methods 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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
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- 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 configured a double-walled in operation hotter outer wall and a colder inner wall during operation and whose inner space arranged therebetween is divided by dividing walls occidental hereinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinskyinsky, a coolant in the interior can be flowed in and out of the interior can be flowed through outlet openings arranged in the outer wall.
- Such a component wall is used, for example, according to EP 0 954 680 B1 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.
- a cascaded impingement cooling in a heat shield is also disclosed in US Pat. No. 4,573,865.
- the object of the invention is to provide a component wall of a hot gas component for a gas turbine, which has a higher
- the object is achieved by such a component wall, which has at least one 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 which is adjacent to the at least one inlet opening.
- At least one second cavity is provided in the cavity, which as outlet cavity is directly connected to at least one of the outlet openings without being directly connected to inlet openings, so as to form a flow path that separates the relevant inlet cavity from the adjacent outlet cavity.
- Cavity dividing partition has at least one through-opening for the passage of the coolant from the Subject Author fenden inlet cavity in the outlet cavity, and that at least one means is provided which in be proper use of the component wall, an increase in the material temperature of réellewa nd purposefully brought about.
- 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 certain openings are arranged: only one adjoin the inlet cavity Nozzle openings, but no outlet openings on and at the outlet cavity, only limit outlet openings, but no inlet openings.
- the inlet opening is preferably configured for impingement cooling of the hotter in Be outer wall, whereby a particularly effective reduction of the temperature of the outer wall isassigeru fen.
- the at least one fürgangsöff tion having partition for impact irradiation of Be in operation cooler inner wall in the region of the outlet cavity configured with heated in operation coolant.
- the partition arranged in the partition fürgangsöffnun conditions are not towards the outer wall, but towards the inner wall towards orien benefits, so they radiate as baffles the heateddemit tel lead to the inner wall and thus increase the temperature Tem, especially compared with a component wall without such Activities.
- the invention pursues the approach not only the temperature of the outer wall Tem as far as possible to reduce the temperature gradient between inner wall and outer wall to re ducieren.
- 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 also from the ge ringeren material temperature and thus approach the overall temperature of the inner wall and outer wall so far that life shortening stresses from thermal Deh voltages reduced become.
- the invention turns away from the idea of avoiding the heating of the inner wall. Consequently, the invention proposes to increase the temperature of the inner wall with at least one designated means targeted.
- the component wall is monolithic, ie inner wall, outer wall and partitions are in one piece.
- Such a component wall can be manufactured by additive manufacturing methods, and in particular by selective laser melting.
- the inventive component wall outer wall, partitions and impact cooling wall thus produced simultaneously.
- the temperature-related material voltages can occur in an undesirably high degree, so that the life of particular monolithic components can be significantly increased with the invention.
- the temperature gradient between the inner wall and the outer wall and thus the resulting thermo-mechanical conditions Spannun in the component wall can be further reduced if provided as a means to an outlet cavity limiting inner surface of the inner wall elements for amplifying the heat transfer. These, too, can then serve for targeted heating of the comparatively colder inner wall, which leads to the said result.
- the means for increasing the material temperature of the inner wall, i. the impact irradiation of the inner wall with heated coolant or the elements for adjusting the heat transfer can be used alternatively or in addition to each other.
- 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 partition walls dividing the interior 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, wherein at least every second the interior accordingly dividing partition each at least one passage opening, preferably, several passage openings for forwarding coolant from the respective inlet cavity in the has immediacy bar adjacent outlet cavity.
- This Ausgestal device serves a large-scale approximation of temperatures of inner wall and outer wall while simultaneously achieving a sufficiently cooled outer wall.
- the outlet cavity is bounded by two partitions of two beidsei term adjacent inlet cavities and disposed in only one of the two respective partitions through holes.
- each of the inlet cavities, each with a plurality of inlet openings and each of the outlet cavities each with a plurality of outlet openings directly connected and in the respective partition walls between each multiple passage openings is arranged.
- the inlet openings and the outlet openings are offset relative to the lying in the flow path fürgangsöffnun gene along this longitudinal extent of the component wall.
- 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 this corner temporarilylie ing edge is part of the outer wall.
- the or the outlet cavities are reversely oriented: one corner of the triangular outlet cavities abuts against the outer wall, whereas an edge of the three angularly shaped outlet cavity facing this corner then forms 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 punctually adjacent to the inner wall and the outlet cavities are more selectively adjacent 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 arranged in the partition through holes with a treatment already heated due to the Prallküh development of the outer wall coolant such that the temperature of the inner wall to the temperature Tempe the outer wall approaches.
- this geometry increases the rigidity of the component wall.
- a hot gas component has a component wall corresponding to it.
- the hot gas component may be, for example, a turbine blade configured as a guide blade or as a rotor blade.
- the component wall may be part of the blade and / or part of the platform.
- the hot gas component may also be configured as a ring segment or as a heat shield of a Brennkam mer. Other applications are also conceivable.
- FIG. 1 is a perspective view of a section through an inventive component wall of a hot gas component for a gas turbine according to a first embodiment
- FIG. 3 is a perspective view of the section through a component wall according to a second embodiment example
- FIG. 4 is a perspective view of a cross section through a component wall according to the second exemplary embodiment
- Fig. 5 shows a cross section through the blade of a
- Turbine blade as a third embodiment of a component wall, wherein the cut is longitudinally through the inlet cavity and
- Fig. 6 shows the turbine blade according to FIG. 5 as the third one
- Embodiment of a component wall with a arranged through the outlet cavity section.
- 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, which can be used in a gas turbine in its hot gas path or to the boundary.
- 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 in each case: the outer wall has a higher temperature during operation than the inner wall and is thus hotter, where against 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 divided by itself between the inner wall 14 and the outer wall 12 extending partitions 16 in principle.
- partitions 16 in principle, it is meant that in some or all partitions in each case at least one passage opening 26, preferably a plurality of passage openings 26 are provided.
- a plurality of inlet openings 18 are provided in the inner wall 14 and a plurality of outlet openings 20 are provided in the outer wall 12.
- 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-section triangular cavities 22, 24.
- the directly to the A lassö réelleen 18 directly connected cavities 22 are referred to as inlet cavities, whereas the directly connected to the outlet openings 20 cavities 24 are referred to as outlet cavities.
- the inlet cavities 22 are directly only with the inlet openings 18 and the openings 26 fürgangsöff in flow communication.
- the outlet cavities 24 communicate directly with only 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.
- the coolant KM impinging on the surface 15 flows over the inlet Openings 18 with the formation of individual coolant jets in the inlet cavity 22.
- the outer wall 12 is then cooled tightly, which lowers the temperature level of the outer wall 12settingflä Chig and heats the coolant KM.
- the coolant KM flows to the staggered through openings 26 and flows through them in one of the immedi applicable adjacent outlet cavities 24 a.
- Figure 2 shows the section through the hot gas component according to the first embodiment along the section line II-II.
- elements 28 vorgese to increase the heat transfer hene.
- 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 reducing the temperature gradient between inside and outside. Whether the amplification of the heat transfer due to the magnification ßerten surface and / or due to the more turbulent flow is basically irrelevant. Both variants are in turn advantages.
- Figure 3 shows an analogous to Figure 1 representation of a construction part wall 10 according to a second embodiment. Not each of the inlet cavities 22 of the outlet cavities 24 dividing partitions 16 extends in an oblique direction from the inner wall 14 to the outer wall 12. According to the embodiment shown here, each second separating wall 16 is perpendicular from the inner walls 14 and outer walls 12th while the remaining are arranged obliquely.
- the pairable inlet cavities 22 and outlet cavities 24 each have a union in wesent rectangular triangular shape, the paired together form a rectangular shape.
- Both embodiments are common in 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 the inner wall 14 are. In this way, a maximum possible area for impact radiation from the outer wall 12 or inner wall 14 can be brought about in each case, thus largely avoiding temperature gradients along the inner wall 14 or along the outer wall 12.
- FIG. 4 shows the arrangement of rib-shaped turbulators 28 on the inner surfaces 17 of the inner wall 14 delimiting the outlet cavity 24.
- Figures 5 and 6 show a portion of an aerodynamically curved GE blade 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 airfoil 30 and the front edge 36th
- the airfoil 30 further includes a suction sidewall 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 disposed inside the airfoil 30 supply cavity 38, which is supplied via a not presented Darge blade foot, the coolant KM.
- the coolant KM flows to the passage openings 26 and then enters the outlet cavity 24, from where it flows to the outlet openings 20.
- the tel KM the component wall 10 and the turbine blade and then mixes with the the blade blade 30 umströ coming working medium AM.
- 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 so hollow can allow a planar impingement cooling of the outer wall 12, without at the same time the Le bensdauer 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.
- monolithic sandwich construction component wall 10 In contrast to conventionally manufactured impact-cooled turbine components, in which a mostly made by casting forth outer wall and a separately manufactured baffle chill be paired with each other, executed in monolithic sandwich construction component wall 10 leads in addition to a lower total metal average temperature to a more homogenous temperature distribution over the complete structure and thus to lower thermal stresses. In addition, 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 has a double-walled design of a hotter outer wall 12 during operation and a colder inner wall 14 during operation, and the interposed therebetween arranged interior by dividing walls 16 extending between the inner wall and the outer wall is basically divided, with a coolant KM in the interior einström- by arranged in the inner wall 14 A laßö réelleen 18 and arranged in the outer wall 12 Auslassöffnun gene 20 from the interior can be flowed out.
- openings are directly connected as an inlet cavity 22 with at least one of the inlet openings 18 without being directly connected to outlet openings 20 and that immediately adjacent to the at least one Inlet cavity 22 is provided at least a second cavity, which is connected as an outlet cavity 24 le diglich with at least one of the outlet openings 20 directly without being connected to inlet ports 18, and that the respective inlet cavity and the adjacent thereto outlet Cavity 24 dividing
- Partition 16 at least one passage opening 26 for the passage of the coolant KM from the respective inlet cavity 22 in the outlet cavity 24 has.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP18170851.2A EP3564484A1 (en) | 2018-05-04 | 2018-05-04 | Hot gas component wall |
PCT/EP2019/059392 WO2019211082A1 (en) | 2018-05-04 | 2019-04-12 | Component wall of a hot gas component |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3762586A1 true EP3762586A1 (en) | 2021-01-13 |
EP3762586B1 EP3762586B1 (en) | 2022-03-30 |
Family
ID=62116733
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18170851.2A Withdrawn EP3564484A1 (en) | 2018-05-04 | 2018-05-04 | Hot gas component wall |
EP19720433.2A Active EP3762586B1 (en) | 2018-05-04 | 2019-04-12 | Hot gas component wall |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18170851.2A Withdrawn EP3564484A1 (en) | 2018-05-04 | 2018-05-04 | Hot gas component wall |
Country Status (3)
Country | Link |
---|---|
US (1) | US11220915B2 (en) |
EP (2) | EP3564484A1 (en) |
WO (1) | WO2019211082A1 (en) |
Families Citing this family (2)
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4573865A (en) * | 1981-08-31 | 1986-03-04 | General Electric Company | Multiple-impingement cooled structure |
WO1998025009A1 (en) | 1996-12-02 | 1998-06-11 | Siemens Aktiengesellschaft | Turbine blade and its use in a gas turbine system |
US7270175B2 (en) * | 2004-01-09 | 2007-09-18 | United Technologies Corporation | Extended impingement cooling device and method |
JP4845957B2 (en) * | 2006-03-02 | 2011-12-28 | 株式会社Ihi | Impingement cooling structure |
US20160222796A1 (en) * | 2013-09-18 | 2016-08-04 | United Technologies Corporation | Manufacturing method for a baffle-containing blade |
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 (en) * | 2015-07-13 | 2017-01-19 | Siemens Aktiengesellschaft | Blade for a turbomachine and method for its production |
WO2019057743A1 (en) * | 2017-09-25 | 2019-03-28 | Siemens Aktiengesellschaft | Blade for a turbine blade |
-
2018
- 2018-05-04 EP EP18170851.2A patent/EP3564484A1/en not_active Withdrawn
-
2019
- 2019-04-12 WO PCT/EP2019/059392 patent/WO2019211082A1/en active Search and Examination
- 2019-04-12 US US17/048,584 patent/US11220915B2/en active Active
- 2019-04-12 EP EP19720433.2A patent/EP3762586B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
WO2019211082A1 (en) | 2019-11-07 |
EP3762586B1 (en) | 2022-03-30 |
EP3564484A1 (en) | 2019-11-06 |
US20210156262A1 (en) | 2021-05-27 |
US11220915B2 (en) | 2022-01-11 |
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