CN117052479A - Microchannel cooled turbine guide vane blade utilizing carbon dioxide working medium - Google Patents
Microchannel cooled turbine guide vane blade utilizing carbon dioxide working medium Download PDFInfo
- Publication number
- CN117052479A CN117052479A CN202311252272.6A CN202311252272A CN117052479A CN 117052479 A CN117052479 A CN 117052479A CN 202311252272 A CN202311252272 A CN 202311252272A CN 117052479 A CN117052479 A CN 117052479A
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- China
- Prior art keywords
- carbon dioxide
- impact
- cavity
- chamber
- front edge
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- Pending
Links
- CURLTUGMZLYLDI-UHFFFAOYSA-N Carbon dioxide Chemical compound O=C=O CURLTUGMZLYLDI-UHFFFAOYSA-N 0.000 title claims abstract description 230
- 229910002092 carbon dioxide Inorganic materials 0.000 title claims abstract description 115
- 239000001569 carbon dioxide Substances 0.000 title claims abstract description 115
- 238000001816 cooling Methods 0.000 claims description 36
- 239000012530 fluid Substances 0.000 claims description 7
- 239000003921 oil Substances 0.000 description 9
- 239000000446 fuel Substances 0.000 description 5
- 239000000295 fuel oil Substances 0.000 description 5
- 238000004939 coking Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 230000008929 regeneration Effects 0.000 description 2
- 238000011069 regeneration method Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000012546 transfer Methods 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a micro-channel cooled turbine guide vane blade utilizing carbon dioxide working media, which comprises a vane main body, wherein a carbon dioxide inlet cavity and a carbon dioxide outlet cavity are arranged in the vane main body in the high direction of the vane, a guide vane front edge impact area is arranged at the inner side of the carbon dioxide inlet cavity, the guide vane front edge impact area comprises a carbon dioxide impact hole, a carbon dioxide front edge impact cavity and a turbulent column, the carbon dioxide impact hole is communicated with the carbon dioxide inlet cavity, and the carbon dioxide front edge impact cavity is positioned in the vane main body, and is communicated with the carbon dioxide front edge impact cavity.
Description
Technical Field
The invention belongs to the technical field of heat protection of aeroengines, and particularly relates to a micro-channel cooled turbine guide vane using a carbon dioxide working medium.
Background
With the progress of the aviation industry, modern aircrafts take high altitude and high speed as main development directions, and under the high altitude and high speed flight condition, the total temperature of incoming air is extremely high, and the traditional air-cooled turbine cannot meet the heat protection requirement of turbine blades. The oil-cooled turbine based on the fuel oil heat sink is a new development thought in the field of the aviation industry nowadays, can improve the fuel oil temperature while cooling high-temperature parts of the engine, and can complete the recovery and regeneration of the heat energy of the engine, and is a new road widely explored in the aviation industry nowadays.
Oil-cooled turbines based on fuel-oil heat sinks can be classified into direct oil cooling and indirect oil cooling according to their cooling medium. The oil cooling mode of directly cooling turbine blades by adopting fuel working media is called direct oil cooling, and is a main direction in the current oil cooling turbine research, and the main problem is that the internal thermal environment of an aeroengine is complicated along with the change of working conditions, the turbine thermal load is extremely large, the fuel is easy to cause over-temperature coking, and the running stability and the safety of the whole engine system are threatened. The cooling means of introducing the intermediate circulation working medium to cool the turbine based on the fuel heat sink and then releasing heat to the fuel in the heat exchanger is called indirect oil cooling, the problem of coking of the fuel in a turbine cooling channel can be avoided when the indirect oil cooling finishes heat transfer, the method is a promising research direction in the field of oil cooling turbines, the supercritical working medium has the advantages of gas and liquid, is the intermediate working medium meeting the requirements of aeroengines, and in the common supercritical working medium, carbon dioxide has a lower critical point and excellent heat exchange performance, and is the intermediate working medium meeting the application requirements of aeroengines.
At present, an impact-air film composite structure is often adopted in the design of a turbine based on air cooling, and cooling air flows out of a blade after impact cooling is carried out on a front edge hot spot of a turbine guide vane, so that an air film is formed on the surface of the blade. For an oil-cooled turbine, the cooling working medium needs to be recovered and cannot flow out from the surfaces of blades, and meanwhile, in order to fully cope with the heat exchange working environment of the turbine with high heat flux density and small size, a cooling structure in the indirect oil-cooled turbine needs to be designed so as to finish turbine cooling under the condition of small size and high heat flux density.
Disclosure of Invention
The invention aims to provide a micro-channel cooled turbine guide vane by utilizing a carbon dioxide working medium so as to solve the problems in the background art.
In order to achieve the above purpose, the present invention provides the following technical solutions: the utility model provides an utilize carbon dioxide working medium's microchannel refrigerated turbine stator blade, includes the blade main part, the inside leaf height direction of blade main part is provided with carbon dioxide inlet chamber and carbon dioxide outlet chamber, the inboard in carbon dioxide inlet chamber is provided with the leading edge impact zone of stator, the leading edge impact zone of stator includes carbon dioxide impact hole, carbon dioxide leading edge impact chamber and vortex post, carbon dioxide impact hole and carbon dioxide inlet chamber intercommunication, the carbon dioxide leading edge impact chamber is located the inside of blade main part, and carbon dioxide impact hole and carbon dioxide leading edge impact chamber intercommunication each other, the inside in carbon dioxide leading edge impact chamber is provided with a plurality of vortex posts, be provided with carbon dioxide wall cooling microchannel between carbon dioxide leading edge impact chamber and the carbon dioxide outlet chamber.
Preferably, the carbon dioxide wall cooling micro-channel is a rectangular channel and is parallel to the blade shape of the blade body, and fluid in the channel flows along the chord length direction and finally merges into the carbon dioxide outlet cavity.
Preferably, the area of the carbon dioxide impact hole is:
wherein,for carbon dioxide mass flow, v 1 Inlet velocity, v, of carbon dioxide impingement holes 2 Let p be the carbon dioxide density and n be the total number of impingement holes.
Preferably, the carbon dioxide inlet cavity is a special-shaped channel, and the channel shape of the carbon dioxide inlet cavity is the same as and parallel to the leading edge molded line of the blade main body.
Preferably, the carbon dioxide front edge impact cavity molded line is the same as and parallel to the blade main body molded line, each carbon dioxide impact hole is perpendicular to the carbon dioxide front edge impact cavity wall, and each turbulence column is perpendicular to the carbon dioxide front edge impact cavity wall.
Compared with the prior art, the invention has the beneficial effects that: according to the invention, the carbon dioxide indirect oil cooling mode based on the fuel oil heat sink is utilized, so that the consumption of high-pressure cold air and air entraining is reduced, the efficiency of the engine is improved, the heat contained in the high temperature of the turbine is transferred to the fuel oil, the regeneration of energy is completed, the energy utilization rate of the system is improved, and meanwhile, the impact-micro-channel composite cooling structure can efficiently complete the cooling task of the turbine guide vane.
Drawings
FIG. 1 is a top view of a turbine vane blade of the present invention and a schematic cross-sectional view thereof in the blade height direction.
FIG. 2 is a schematic isometric view of a turbine vane blade of the present invention.
FIG. 3 is a schematic block diagram of the internal cooling passages of the turbine of the present invention.
1. A blade body; 2. a carbon dioxide inlet chamber; 3. a carbon dioxide outlet chamber; 4. a guide vane leading edge impingement zone; 5. carbon dioxide wall cooling micro-channels; 41. a carbon dioxide impingement hole; 42. a carbon dioxide front impingement cavity; 43. a turbulent flow column.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1 to 3, the present invention provides a technical solution: the turbine guide vane blade cooled by utilizing the micro-channel of the carbon dioxide working medium comprises a blade main body 1, wherein a carbon dioxide inlet cavity 2 and a carbon dioxide outlet cavity 3 are arranged in the blade main body 1 in the blade height direction, the carbon dioxide cooling working medium flows into the carbon dioxide inlet cavity 2 from a turbine disk, a guide vane front edge impact area 4 is arranged on the inner side of the carbon dioxide inlet cavity 2, the carbon dioxide cooling working medium passes through the guide vane front edge impact area 4, the guide vane front edge impact area 4 comprises a carbon dioxide impact hole 41, a carbon dioxide front edge impact cavity 42 and a vortex column 43, the carbon dioxide impact hole 41 is communicated with the carbon dioxide inlet cavity 2, the carbon dioxide front edge impact cavity 42 is positioned in the blade main body 1, the carbon dioxide impact hole 41 is mutually communicated with the carbon dioxide front edge impact cavity 42, a plurality of vortex columns 43 are arranged in the carbon dioxide front edge impact cavity 42 and the carbon dioxide outlet cavity 3, and a carbon dioxide wall surface cooling micro-channel 5 is arranged between the carbon dioxide front edge impact cavity 42 and the carbon dioxide outlet cavity 3; the carbon dioxide is flushed into the carbon dioxide front edge impact cavity 42 through the carbon dioxide impact holes 41, fully exchanges heat with the front edge wall surface under the action of the turbulence post 43, flows into the carbon dioxide wall surface cooling micro-channel 55, further exchanges heat with the vane back and the vane basin of the turbine vane, and is converged in the carbon dioxide outlet cavity 3.
In this embodiment, the carbon dioxide wall cooling micro-channel 5 is preferably a rectangular channel and is parallel to the blade shape of the blade body 1, and the fluid in the channel flows along the chord length direction and finally merges into the carbon dioxide outlet chamber 3; in order to ensure the strength of the turbine blade, the impingement cavity and the cooling micro-channel are kept at a certain distance from the wall surface of the turbine, and a certain thickness is reserved.
In the present embodiment, the area of the carbon dioxide impingement holes 41 is preferably:
wherein,for carbon dioxide mass flow, v 1 Inlet velocity, v, of carbon dioxide impingement holes 2 Let p be the carbon dioxide density and n be the total number of impingement holes.
In this embodiment, the carbon dioxide inlet chamber 2 is preferably a profiled channel having the same shape and parallel to the leading edge profile of the blade body 1.
In this embodiment, preferably, the profile of the carbon dioxide front edge impact cavity 42 is the same as and parallel to the profile of the blade body 1, and each carbon dioxide impact hole 41 is perpendicular to the cavity wall of the carbon dioxide front edge impact cavity 42 and is used for providing jet flow for carbon dioxide cooling working medium; each spoiler column 43 is perpendicular to the cavity wall of the carbon dioxide front impingement cavity 42; in order to increase the heat exchange coefficient of the near wall facing flow of the carbon dioxide cooling working medium in the impact cavity, the heat exchange of the front edge of the turbine is enhanced.
Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. The utility model provides a turbine stator blade of microchannel cooling with carbon dioxide working medium, includes blade main part (1), its characterized in that: the inside leaf height direction of blade main part (1) is provided with carbon dioxide inlet chamber (2) and carbon dioxide outlet chamber (3), the inboard of carbon dioxide inlet chamber (2) is provided with stator leading edge impact zone (4), stator leading edge impact zone (4) are including carbon dioxide impact hole (41), carbon dioxide leading edge impact chamber (42) and vortex post (43), carbon dioxide impact hole (41) and carbon dioxide inlet chamber (2) intercommunication, carbon dioxide leading edge impact chamber (42) are located the inside of blade main part (1), and carbon dioxide impact hole (41) and carbon dioxide leading edge impact chamber (42) communicate each other, the inside of carbon dioxide leading edge impact chamber (42) is provided with a plurality of vortex posts (43), be provided with carbon dioxide wall cooling microchannel (5) between carbon dioxide leading edge impact chamber (42) and carbon dioxide outlet chamber (3).
2. A microchannel cooled turbine vane utilizing carbon dioxide working fluid as defined in claim 1, wherein: the carbon dioxide wall cooling micro-channel (5) is a rectangular channel and is parallel to the blade shape of the blade body (1), and fluid in the channel flows along the chord length direction and finally flows into the carbon dioxide outlet cavity (3).
3. A microchannel cooled turbine vane utilizing carbon dioxide working fluid as defined in claim 1, wherein: the area of the carbon dioxide impact hole (41) is as follows:
wherein,for carbon dioxide mass flow, v 1 Inlet velocity, v, of carbon dioxide impingement holes 2 Let p be the carbon dioxide density and n be the total number of impingement holes.
4. A microchannel cooled turbine vane utilizing carbon dioxide working fluid as defined in claim 1, wherein: the carbon dioxide inlet cavity (2) is a special-shaped channel, and the shape of the channel is the same as and parallel to the front edge molded line of the blade main body (1).
5. A microchannel cooled turbine vane utilizing carbon dioxide working fluid as defined in claim 1, wherein: the molded line of the carbon dioxide front edge impact cavity (42) is the same as and parallel to the molded line of the blade main body (1), each carbon dioxide impact hole (41) is perpendicular to the cavity wall of the carbon dioxide front edge impact cavity (42), and each turbulence column (43) is perpendicular to the cavity wall of the carbon dioxide front edge impact cavity (42).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311252272.6A CN117052479A (en) | 2023-09-26 | 2023-09-26 | Microchannel cooled turbine guide vane blade utilizing carbon dioxide working medium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311252272.6A CN117052479A (en) | 2023-09-26 | 2023-09-26 | Microchannel cooled turbine guide vane blade utilizing carbon dioxide working medium |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117052479A true CN117052479A (en) | 2023-11-14 |
Family
ID=88666562
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311252272.6A Pending CN117052479A (en) | 2023-09-26 | 2023-09-26 | Microchannel cooled turbine guide vane blade utilizing carbon dioxide working medium |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117052479A (en) |
-
2023
- 2023-09-26 CN CN202311252272.6A patent/CN117052479A/en active Pending
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