EP3658751A1 - Schaufelblatt für eine turbinenschaufel - Google Patents
Schaufelblatt für eine turbinenschaufelInfo
- Publication number
- EP3658751A1 EP3658751A1 EP18779293.2A EP18779293A EP3658751A1 EP 3658751 A1 EP3658751 A1 EP 3658751A1 EP 18779293 A EP18779293 A EP 18779293A EP 3658751 A1 EP3658751 A1 EP 3658751A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cooling
- airfoil
- wall
- impingement cooling
- impingement
- 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
- 238000001816 cooling Methods 0.000 claims abstract description 128
- 238000000034 method Methods 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 239000000654 additive Substances 0.000 claims description 3
- 230000000996 additive effect Effects 0.000 claims description 3
- 239000012530 fluid Substances 0.000 claims 1
- 239000002826 coolant Substances 0.000 description 19
- 230000004888 barrier function Effects 0.000 description 5
- 230000001419 dependent effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000265 homogenisation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000005495 investment casting Methods 0.000 description 1
- 230000005923 long-lasting effect Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000000930 thermomechanical effect Effects 0.000 description 1
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
- 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
- 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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
-
- 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
-
- 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
- F05D2240/303—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the leading edge of a rotor blade
-
- 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
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/185—Two-dimensional patterned serpentine-like
-
- 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
-
- 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
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
-
- 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
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
Definitions
- the invention relates to an airfoil for a turbine blade according to the preamble of claim 1.
- a blade according to the preamble of claim 1 has long been known from the extensive existing state of the art.
- the airfoil and in particular the entire gas turbine blade are usually produced in a precision casting process, so that cavities are present in the interior of the airfoil. These cavities can be flowed through by a coolant, usually cooling air, so that the metallic material of the blade and the turbine blade can permanently withstand the high temperatures occurring during operation.
- a coolant usually cooling air
- impingement cooling For cooling long-known different cooling concepts are used, one of which is referred to as impingement cooling. In this cooling air jets meet at a nearly vertical angle to the inner surfaces of the metallic blade wall to take up the heat energy contained therein and then transported with him.
- the impact cooling walls required for the formation of the impingement cooling can on the one hand be cast or on the other hand can be provided by the installation of metal sheet inserts.
- molded impingement cooling requires a minimum distance between the wall surface to be cooled and the impingement cooling wall having the impingement cooling openings, since the casting cores required for this purpose themselves require a minimum wall thickness for sufficient strength. If the perforated impingement cooling wall is mounted as an insert in an airfoil, further production and assembly steps are required for this, which increase the expense for producing the turbine blade.
- leaks at the interface between the used Impact cooling insert and cast component and on the other wear phenomena occur, which can affect the cooling efficiency or the service life.
- the object of the invention is therefore to provide a long-lasting blade for a turbine blade, which allows a particularly efficient cooling of the side walls of the blade.
- the present invention contemplates that in a turbine blade airfoil comprising a suction side sidewall and a pressure side sidewall extending along a tread centerline from a common leading edge to a common trailing edge and in a spanwise direction from a root end to a head end extending at least partially enclose a cavity, wherein along the span inside a first perforated impingement cooling wall for impingement cooling of the leading edge and at least one further perforated impingement cooling wall for impingement cooling a portion of the suction side and / or pressure side side wall is provided, the impingement cooling openings of the first impingement cooling wall and the impingement cooling openings of at least one further impingement cooling wall are fluidly connected in series.
- a cascaded impingement cooling is proposed in the interior of the airfoil, wherein starting from a first impingement cooling at the leading edge on the suction side and / or pressure side, at least one further impingement cooling section, preferably two further impingement cooling sections, is connected in cascading manner per side wall.
- the invention is based on the finding that a series-connected impingement cooling (cascaded impingement cooling) makes it possible to use the cooling air several times and thus provide a uniformity of the temperature distribution along the cross section to achieve.
- the region of the airfoil which is subjected to the highest thermal load, ie the region around the front edge, is fed and cooled down in a first baffle cooling section with the coolest cooling air.
- the cooling air heats up for the first time and the blade temperature in the vicinity of the leading edge is reduced to a tolerable level.
- the heated cooling air is then guided in a downstream section of the blade and used there again for impingement cooling of the side wall, whereby the local side wall is also lowered in its temperature and the cooling air is heated in turn.
- an efficient use of cooling air is achieved, so that - compared to conventional airfoils - the saved cooling air can be used to increase the efficiency of the gas turbine.
- the thermal constraint across the blade cross-section can be reduced. This can reduce the thermo-mechanical stress of the metallic blade, which can lead to an increased blade life. Due to the fact that the series-connected impingement cooling has small transverse flow components in spanwise direction, this is comparatively efficient.
- an impingement cooling space is provided between the respective impingement cooling wall and the inside of the associated side wall, wherein downstream of the respective impingement cooling space a collecting space is provided, which immediately adjacent to the upstream further impingement cooling wall.
- the relative terms “upstream” and “downstream” refer to the flow direction of the cooling air inside the airfoil, unless otherwise stated.
- the collecting chambers serve as cavities in which the coolant that is further heated after an impingement cooling can be collected on the one hand and off on the other hand can pass through the baffle cooling openings of the subsequent impact cooling wall for further impingement cooling.
- the collecting chambers extend in spanwise direction preferably over the entire length of the airfoil. Consequently, a homogenization of the pressure in the collecting space can take place.
- a supply channel for supplying coolant for cooling the leading edge is provided between the first collecting space and the first impact cooling space.
- This supply channel preferably extends over the entire span of the airfoil. He may, more preferably be tapered tapering from its foot-side end to the head end, so that on the assumption that the supply of coolant into the supply channel at the foot end, he has a larger flow area at the foot end than at his head end. This takes into account the fact that the coolant quantity present in the supply channel decreases as a result of the presence of baffle cooling openings in the baffle cooling wall with increasing distance from the foot-side end. The conical shape of the supply channel therefore leads to a homogenization of the flow velocity of the coolant along the Spannweiteraum.
- the collection space is partially bounded by a projection which is impact-cooled.
- side wall near outlet openings are arranged in the rib.
- At least one further impact cooling device is provided on at least one side wall of the airfoil, preferably on both side walls. wall provided. Consequently, the first impingement cooling (the leading edge of the blade) in each case is followed by the suction-side impingement cooling and the impingement-side impingement cooling, whereby, however, the two further impingement cooling systems arranged on both sides of the profile center line are connected in parallel.
- one of the two further impingement cooling chambers is arranged on the suction side and the other of the two further impingement cooling chambers is arranged on the pressure side and a separate collection space is arranged upstream of each of these two impingement cooling spaces.
- These can preferably be provided by providing a first barrier rib.
- the pressures of the coolant required in the respective collecting chambers can be adjusted in accordance with the local thermal loading of the suction-side and pressure-side side walls in such a way that efficient and locally adapted use of coolants takes place.
- a further cavity is provided between two collecting chambers arranged on both sides of the profile center line.
- this further cavity is separated from the collecting spaces by two second separating ribs.
- the said cavity can on the one hand be used to reduce the size of the collecting spaces to a desired level, if a certain flow rate is to be achieved in the collecting spaces.
- the further cavity can also be used to guide a further coolant from a head end to a foot end of the airfoil when this coolant is to be passed through the airfoil if possible without receiving heat energy.
- Such blades can be produced in particular by means of an additive process.
- An additive process is understood in particular to be the so-called SLM technique known as “selective laser melting.”
- SLM technique known as "selective laser melting.”
- This technology also known as 3D printing technology, makes it possible for metallic components to be comparatively small in comparison with conventionally cast turbine blades
- Figure 2 shows the cross section according to the section line II-II
- FIG. 3 shows a second exemplary embodiment of an airfoil according to the invention of a turbine blade.
- a turbine blade 10 relating to the invention is shown in perspective in FIG.
- the turbine blade 10 is designed according to FIG. 1 as a rotor blade.
- the invention can also be used in a guide vane, not shown, of a vane.
- the turbine blade 10 comprises a blade root 12 of a fir-tree-shaped cross-section and a platform 14 arranged thereon.
- the platform 14 is adjoined by an airfoil 16 which is aerodynamically curved. Whether the blade 16 is covered by a thermal protection layer or not, is irrelevant to the invention.
- the airfoil 16 includes a suction side wall 22 and a pressure side wall 24, which, relative to a hot gas flowing around the airfoil 16, extend from a front edge 18 to a rear edge 20. Along the trailing edge 20 a plurality of openings 28 are provided for blowing out coolant, which are separated from one another by webs 30 arranged therebetween.
- the airfoil 16 extends along a spanwise direction from a foot-side end 26 to a head-side end 27. When using the shown turbine blade 10 in an axial flow gas turbine, the spanwise direction coincides with the radial direction of the gas turbine.
- Figure 2 shows a sectional view through the airfoil 16 according to the section line II-II as a first exemplary embodiment of a blade according to the invention 16, whereas Figure 3 shows a second embodiment thereof.
- Figure 3 shows a second embodiment thereof.
- the blade 16 and the pressure-side side wall 24 and suction-side side wall 22 extend - as already explained - from the front edge 18, starting along a profile center line 32 to Trailing edge.
- baffle cooling wall 34 is arranged at a distance from the inner surface of the front edge 18, so that a first baffle cooling space 36 is formed therebetween.
- a supply channel 38 is provided on the first impingement cooling chamber 36 opposite side of the first impact cooling wall 34. This is separated by a first rib 40 from the remaining cavity of the airfoil 16. According to the cross-sectional plane, the first rib 40 extends from a suction-side rib end 37 to a pressure-side rib end 37 and has outlet openings 39 close to the side wall for the first impingement cooling chamber 36.
- first impact cooling wall 34 for surface cooling of the front edge 18 and the suction side and pressure side regions of the side walls 22, 24 contiguous thereto.
- first rib 40 Viewing along the profile center line 32 in the direction of the trailing edge , the first rib 40 is followed by a first collecting space 44, which is separated from a second collecting space 48 by a second rib 46. The latter is also limited by a third rib 50, so that further in the direction of the trailing edge, a third collecting space 52 connects.
- the first plenum 44 is bounded on both the suction side and on the pressure side by two further impingement cooling walls 54.
- baffle cooling openings 42 are arranged, so that first further baffle cooling chambers 56 are provided, with which corresponding sections of the suction-side and pressure-side side walls 22 and 24 are bounce-coolable.
- Second additional impingement cooling chambers 59 are separated from the second collection space 48 by impact cooling walls 55. According to the embodiment shown, all others are
- Impact cooling chambers 56, 59 laterally delimited by extending from the side walls 22, 24 inwardly extending projections 57.
- Analogous to the first rib 40 go the second and third ribs 46, 50 at their rib ends 37 into the suction-side or pressure-side side wall 22, 24 and have side wall near outlet openings 39 there.
- impingement cooling openings 42 outlet openings 39 are present, but that in the corresponding walls more of them at the corresponding position, preferably lying in a row, are distributed along the span.
- a coolant is supplied to the supply channel 38 during operation through an opening, not shown, of the turbine blade 10. There, it spreads over the span of the blade and flows through the air jets forming the individual baffle cooling openings 42 of the first baffle cooling wall 34. The air jets bounce in a known manner on the inner surface of the leading edge and cool it as intended. Subsequently, the coolant flows through the outlet openings 39 of the first rib 40, after which it impinges on the projections 57 and is deflected by these into the first collecting space 44. From there it flows through the first and second further impact cooling walls 54, 55 for cooling the associated side wall sections. From the first and second impingement cooling chambers 56, 59, it passes through the outlet openings of the fins 46, 50 into the subsequent collection spaces 48, 52. After the coolant has cascaded the previously described cascading
- the coolant in a known manner for cooling other sections of the airfoil 16 are used. It is conceivable that it is diverted on the one hand into a kind of meander cooling and finally blown out through the trailing edge openings 28. It is also possible that the coolant from the interior of the airfoil 16 is passed to the outside through film cooling openings (64, FIG. 3) arranged in the side walls 22, 24. The combination of both variants can make sense technically.
- FIG. 3 shows an alternative embodiment of the turbine blade 10 according to the invention as a second exemplary embodiment.
- the identical features are provided with the same reference symbols in FIG. 3, so that only the differences from the first exemplary embodiment are discussed below.
- separating ribs 58, 60 are provided in the interior of the blade 16.
- a first barrier rib 58 extends between the rib 40 and the further rib 46 along the profile centerline 32.
- the barrier rib 58 divides the plenum 44 into two plenums 44a and 44b, the first of which is on the suction side and the second on the pressure side.
- Two second separating ribs 60 extend along the and thus quasi-parallel to the profile center line 32 between the rib 46 and the rib 50, wherein, however, one of each suction side and one of which is arranged on the pressure side.
- the plenum 48 of FIG. 2 is now split into two plenums 48a and 48b, however, due to the use of two second barrier ribs 60, another cavity 62 can be provided.
- the further cavity 62 can be used for different purposes. For example, it is suitable for passing a part of the coolant from the foot-side end 26 of the blade 16 to a head-side end 27 of the blade 16, without this coming into contact with the comparatively hot side walls 22, 24. Thus, at the head end 27 of the airfoil be provided comparatively cool cooling air, which is particularly advantageous for vanes.
- the cavity 62 is hermetically closed in order to guide the cooling air guided in the partial collecting spaces 48a, 48b closer to the impingement cooling walls 54 and the impingement cooling openings 42 arranged therein.
- the invention thus relates to an airfoil 16 for a turbine blade 10, comprising a suction side Be tenwand 22 and a pressure-side side wall 24 extending along a profile center line 32 from a common leading edge 18 to a common trailing edge 20 and in a Spannweitecardi of a foot-side end 26th extending to a head end 27 at least partially enclosing a cavity, wherein along the span inside a first perforated impingement baffle 34 for impingement cooling of the leading edge 18 and at least one further perforated impingement cooling wall 54 for impingement cooling of a portion of the suction side and / or pressure side vane wall 22nd , 24 is provided.
- the baffle cooling openings 42 of the first baffle cooling wall 34 and the at least one second baffle cooling wall 54 be fluidly connected in series.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102017216926 | 2017-09-25 | ||
PCT/EP2018/075288 WO2019057743A1 (de) | 2017-09-25 | 2018-09-19 | Schaufelblatt für eine turbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3658751A1 true EP3658751A1 (de) | 2020-06-03 |
EP3658751B1 EP3658751B1 (de) | 2021-07-07 |
Family
ID=63708332
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18779293.2A Active EP3658751B1 (de) | 2017-09-25 | 2018-09-19 | Schaufelblatt für eine turbinenschaufel |
Country Status (3)
Country | Link |
---|---|
US (1) | US11203937B2 (de) |
EP (1) | EP3658751B1 (de) |
WO (1) | WO2019057743A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3650644B1 (de) * | 2018-11-09 | 2023-12-27 | RTX Corporation | Schaufel mit benachbart angeordnetem kühlkanalnetz mit hohlraum |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3564484A1 (de) * | 2018-05-04 | 2019-11-06 | Siemens Aktiengesellschaft | Bauteilwand eines heissgasbauteils |
US11286793B2 (en) * | 2019-08-20 | 2022-03-29 | Raytheon Technologies Corporation | Airfoil with ribs having connector arms and apertures defining a cooling circuit |
CN111927564A (zh) * | 2020-07-31 | 2020-11-13 | 中国航发贵阳发动机设计研究所 | 一种采用高效冷却结构的涡轮导向器叶片 |
US11767766B1 (en) * | 2022-07-29 | 2023-09-26 | General Electric Company | Turbomachine airfoil having impingement cooling passages |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6036441A (en) * | 1998-11-16 | 2000-03-14 | General Electric Company | Series impingement cooled airfoil |
JP2002242607A (ja) | 2001-02-20 | 2002-08-28 | Mitsubishi Heavy Ind Ltd | ガスタービン冷却翼 |
US7097426B2 (en) * | 2004-04-08 | 2006-08-29 | General Electric Company | Cascade impingement cooled airfoil |
US7497655B1 (en) | 2006-08-21 | 2009-03-03 | Florida Turbine Technologies, Inc. | Turbine airfoil with near-wall impingement and vortex cooling |
US8070442B1 (en) * | 2008-10-01 | 2011-12-06 | Florida Turbine Technologies, Inc. | Turbine airfoil with near wall cooling |
JP5675081B2 (ja) | 2009-11-25 | 2015-02-25 | 三菱重工業株式会社 | 翼体及びこの翼体を備えたガスタービン |
US10024171B2 (en) | 2015-12-09 | 2018-07-17 | General Electric Company | Article and method of cooling an article |
-
2018
- 2018-09-19 US US16/647,139 patent/US11203937B2/en active Active
- 2018-09-19 EP EP18779293.2A patent/EP3658751B1/de active Active
- 2018-09-19 WO PCT/EP2018/075288 patent/WO2019057743A1/de unknown
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3650644B1 (de) * | 2018-11-09 | 2023-12-27 | RTX Corporation | Schaufel mit benachbart angeordnetem kühlkanalnetz mit hohlraum |
Also Published As
Publication number | Publication date |
---|---|
US20200277860A1 (en) | 2020-09-03 |
US11203937B2 (en) | 2021-12-21 |
WO2019057743A1 (de) | 2019-03-28 |
EP3658751B1 (de) | 2021-07-07 |
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