CN114856731A - Structure for improving laminate cooling performance by utilizing aviation kerosene - Google Patents
Structure for improving laminate cooling performance by utilizing aviation kerosene Download PDFInfo
- Publication number
- CN114856731A CN114856731A CN202210586109.2A CN202210586109A CN114856731A CN 114856731 A CN114856731 A CN 114856731A CN 202210586109 A CN202210586109 A CN 202210586109A CN 114856731 A CN114856731 A CN 114856731A
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- Prior art keywords
- circle
- impact
- air film
- pore plate
- cooling
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- 238000001816 cooling Methods 0.000 title claims abstract description 53
- 239000003350 kerosene Substances 0.000 title claims abstract description 45
- 239000011148 porous material Substances 0.000 claims abstract description 42
- 239000007789 gas Substances 0.000 claims abstract description 15
- 239000002737 fuel gas Substances 0.000 claims abstract description 4
- 238000010521 absorption reaction Methods 0.000 abstract description 3
- 238000007664 blowing Methods 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Images
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
- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a structure for improving the cooling performance of a laminate by utilizing aviation kerosene, which comprises an impact orifice plate, a turbulence column and a gas film orifice plate; aviation kerosene flow channels are processed inside the impact pore plate, the turbulence column and the gas film pore plate; the section of the kerosene channel has a fractal characteristic, the kerosene channel is distributed in a multistage manner around a circle as a center, the main channel is a primary circle, the primary circle forms 4 symmetrical secondary circles, each secondary circle forms 2 tertiary circles, the center of each secondary circle is located on the boundary of the primary circle, and the center of each tertiary circle is located on the boundary of the secondary circle. The cooling airflow can absorb heat transferred by high-temperature fuel gas in the internal cooling runner while carrying out jet impact cooling, turbulence column reinforced cooling and air film cooling. According to the invention, the aviation kerosene cooling flow channel with the fractal characteristic is arranged in the laminate structure, and the heat absorption capacity of the aviation kerosene and the enhanced heat exchange capacity of the fractal channel are utilized to further improve the laminate cooling efficiency.
Description
Technical Field
The invention relates to a high-efficiency cooling technology for hot-end components of an aviation gas turbine engine, in particular to a structure for improving the cooling performance of a laminate by utilizing aviation kerosene.
Technical Field
The continuous increase of the supercharging ratio of the compressor of the aircraft engine and the temperature of the inlet (outlet) of the combustion chamber) of the turbine brings innovation and development requirements of the intensified cooling technology of hot-end components. At present, the boost ratio of an engine compressor with a thrust-weight ratio of 10 grade reaches 30, the temperature of gas at a turbine inlet is close to 2000K, and the temperature resistance limit of a material of a hot end component is far exceeded; the published literature reports that the average turbine inlet temperature of the latest generation of aircraft engines exceeds 2100K. The laminated plate cooling integrates jet impact cooling, turbulent flow column reinforced cooling and air film cooling, cooling airflow forms jet flow after passing through an impact hole and impacts the cold side of an air film pore plate, the impacted cooling airflow enters a hot air channel after passing through the turbulent flow column and the air film hole, and a cooling air film is formed on the hot side of the air film pore plate; is considered to be an effective way for breaking through the technical bottleneck of the heat protection of the high thrust-weight ratio aeroengine.
The aviation kerosene cooling and the laminate cooling are combined, the aviation kerosene cooling channel with fractal characteristics is processed in the laminate (the air film pore plate, the impact pore plate and the turbulence column), and the improvement of the laminate cooling performance is realized by utilizing the heat absorption capacity of the low-temperature aviation kerosene and the strong heat exchange capacity of the fractal channel on the basis of the traditional jet impact cooling, the turbulent column reinforced cooling and the air film cooling.
Disclosure of Invention
The invention discloses a structure for improving the cooling performance of a laminated plate by utilizing aviation kerosene.
In order to achieve the purpose, the technical scheme of the invention is as follows:
a structure for improving the cooling performance of a laminate by utilizing aviation kerosene comprises an impact orifice plate, a turbulence column and an air film orifice plate; the gas film pore plate is positioned at the upper part of the impact pore plate, and a plurality of turbulence columns arranged in an array are arranged between the impact pore plate and the gas film pore plate; the interior of the impact orifice plate, the turbulence column and the gas film orifice plate is provided with a through aviation kerosene flow channel with fractal characteristics;
the impact pore plate and the air film pore plate are respectively provided with a plurality of impact pores and air film pores which are arranged in an array manner, cooling airflow forms jet flow after passing through the impact pores and impacts the cold side of the air film pore plate, the impacted cooling airflow is intensively cooled by the turbulence columns, and a cooling air film is formed at the hot side of the air film pore plate after passing through the air film pores;
meanwhile, the low-temperature aviation kerosene flows in from an aviation kerosene runner on the gas film pore plate and flows out from an aviation kerosene runner on the impact pore plate after passing through the turbulence column, and the low-temperature aviation kerosene is used for further absorbing heat transferred by the high-temperature fuel gas.
Furthermore, the thickness of the air film pore plate and the thickness of the impact pore plate are 0.8-1.5 mm, the diameter of the turbulence column is 0.8-1.5 mm, and the impact height is 1.0-2.0 mm.
Furthermore, the aperture of the air film is 0.5-1.1 mm, the ratio of the pitch to the row spacing of the air film holes is 0.8-2.2, the ratio of the area of the air film holes to the area of the impact holes is 0.25-1, the ratio of the row spacing of the air film holes to the aperture of the air film holes is 4-14, and the blockage ratio of the turbulence column is 0.3-0.7.
Furthermore, the impact holes and the air film holes are arranged in a staggered mode, and the jet impact target point is located in the center of the connecting line of the adjacent air film holes.
Furthermore, the section of the aviation kerosene flow channel has a fractal characteristic, the aviation kerosene flow channel is distributed in a multistage manner around a circle as a center, the main flow channel is a primary circle, the primary circle is divided into 4 symmetrical secondary circles, each secondary circle is divided into 2 tertiary circles, the centers of the secondary circles are located on the boundary of the primary circle, and the centers of the tertiary circles are located on the boundary of the secondary circles.
Furthermore, the diameter of the primary circle is 0.4-0.6 mm, the diameter of the secondary circle is 1/2 of the diameter of the primary circle, and the diameter of the tertiary circle is 1/2 of the diameter of the secondary circle.
Advantageous effects
According to the structure for improving the laminate cooling performance by using the aviation kerosene, the aviation kerosene cooling flow channel with the fractal characteristic is processed in the air film pore plate, the impact pore plate and the turbulence column, the heat absorption capacity of the aviation kerosene and the strong heat exchange capacity of the fractal channel are used for further improving the laminate cooling efficiency, and the laminate cooling performance is improved. The structure has the advantages of simple processing and lower cost, and can improve the working reliability and the service life of the hot end part of the gas turbine.
Drawings
FIG. 1 is a schematic view of a laminate cooling performance enhancement using aviation kerosene according to the present invention;
FIG. 2 is a schematic cross-sectional view of a gas film orifice plate, an impingement orifice plate, and a longitudinal section along the aviation kerosene passage direction;
FIG. 3 is a schematic cross-sectional view of a jet fuel passage;
FIG. 4 illustrates the calculation of regions and boundaries according to one embodiment.
Detailed Description
The embodiment is a structure for improving the laminate cooling performance by using aviation kerosene. The diameter of the air film hole is 0.6mm, the impact height is 2mm, the impact aperture is 0.6mm, the hole array pitch is 5mm, the hole pitch is 6mm, the blocking ratio is 0.45, the thickness of the impact orifice plate is 1mm, the diameter of the turbulence column is 1mm, and the thickness of the air film orifice plate is 1 mm. The diameter of the first-level circle 5, the diameter of the second-level circle 6 and the diameter of the third-level circle 7 of the cross section of the aviation kerosene flow passage are respectively 0.5mm, 0.25mm and 0.125 mm. The inlet mass of the aviation kerosene RP-3 is 0.04kg/s, the inlet temperature is 350K, and the kerosene flows out of the impact orifice plate after passing through the gas film orifice plate and the turbulence column.
The temperature of the fuel gas is 2100K, the pressure is 3.0MPa, the flow rate is 20m/s, and the temperature of the cooling gas is 730K. The blowing ratio is defined as:
in the formula, ρ c 、u c Is the density and velocity of the secondary stream, p ∞ 、u ∞ The density and velocity of the mainstream. In this example, the blowing ratio was 1.0.
The flow field and temperature field were solved by commercial software Ansys Fluent calculations. Defining the comprehensive cooling efficiency as:
in the formula, T g Is the main stream temperature, T w Temperature of the hot side wall, T c Is the cooling gas temperature. Before the aviation kerosene is used for enhanced cooling, the average cooling efficiency of the area of the cooling section is 0.758; after the aviation kerosene is used for cooling, the average cooling efficiency is increased by 11.3 percent and reaches 0.844, and the temperature of an aviation kerosene outlet rises by 23K.
Claims (6)
1. A structure for improving the laminate cooling performance by using aviation kerosene is characterized by comprising an impact orifice plate (1), a turbulence column (2) and a gas film orifice plate (3);
the gas film pore plate (3) is positioned at the upper part of the impact pore plate (1), and a plurality of turbulence columns (2) arranged in an array are arranged between the impact pore plate (1) and the gas film pore plate (3); an aviation kerosene flow channel (4) which is communicated and has fractal characteristics is arranged inside the impact pore plate (1), the turbulence column (2) and the air film pore plate (3);
the impact pore plate (1) and the air film pore plate (3) are respectively provided with a plurality of impact pores and air film pores which are arranged in an array manner, cooling air flow forms jet flow after passing through the impact pores and impacts the cold side of the air film pore plate, the impacted cooling air flow is intensively cooled by the turbulence columns, and a cooling air film is formed on the hot side of the air film pore plate after passing through the air film pores;
meanwhile, low-temperature aviation kerosene flows in from an aviation kerosene flow channel (4) on the gas film pore plate (3), flows out from the aviation kerosene flow channel (4) on the impact pore plate (1) after passing through the turbulence column, and is used for further absorbing heat transferred by high-temperature fuel gas.
2. The structure for improving the laminate cooling performance using kerosene for aviation according to claim 1, wherein: the thickness of the air film pore plate (3) and the thickness of the impact pore plate (1) are 0.8-1.5 mm, the diameter of the turbulence column (2) is 0.8-1.5 mm, and the impact height is 1.0-2.0 mm.
3. The structure for improving the laminate cooling performance using kerosene for aviation according to claim 1, wherein: the diameter of the air film is 0.5-1.1 mm, the ratio of the pitch to the row spacing of the air film holes is 0.8-2.2, the ratio of the area of the air film holes to the area of the impact holes is 0.25-1, the ratio of the row spacing of the air film holes to the diameter of the air film holes is 4-14, and the blockage ratio of the turbulent flow columns is 0.3-0.7.
4. The structure for improving the laminate cooling performance using kerosene for aviation according to claim 1, wherein: the impact holes and the air film holes are arranged in a staggered mode, and the jet impact target point is located in the center of a connecting line of the adjacent air film holes.
5. The structure for improving the laminate cooling performance using kerosene for aviation according to claim 1, wherein: the section of the aviation kerosene flow passage (4) has a fractal characteristic, the aviation kerosene flow passage is in multi-stage distribution around a circle, the main flow passage is a primary circle (5), the primary circle (5) forms 4 symmetrical secondary circles (6), each secondary circle (6) forms 2 tertiary circles (7), the circle center of each secondary circle (6) is located on the boundary of the corresponding primary circle (5), and the circle center of each tertiary circle (7) is located on the boundary of the corresponding secondary circle (6).
6. A structure for improving the cooling performance of laminated plates by using aviation kerosene as claimed in claim 5, wherein the diameter of said primary circle (5) is 0.4-0.6 mm, the diameter of said secondary circle (6) is 1/2 of the diameter of said primary circle (5), and the diameter of said tertiary circle (7) is 1/2 of the diameter of said secondary circle (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210586109.2A CN114856731A (en) | 2022-05-26 | 2022-05-26 | Structure for improving laminate cooling performance by utilizing aviation kerosene |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210586109.2A CN114856731A (en) | 2022-05-26 | 2022-05-26 | Structure for improving laminate cooling performance by utilizing aviation kerosene |
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| Publication Number | Publication Date |
|---|---|
| CN114856731A true CN114856731A (en) | 2022-08-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210586109.2A Pending CN114856731A (en) | 2022-05-26 | 2022-05-26 | Structure for improving laminate cooling performance by utilizing aviation kerosene |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114856731A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130209233A1 (en) * | 2012-02-15 | 2013-08-15 | United Technologies Corporation | Cooling hole with enhanced flow attachment |
| CN103968418A (en) * | 2014-05-26 | 2014-08-06 | 西北工业大学 | Double-layer-wall heat insulation screen used for afterburner |
| CN110344886A (en) * | 2019-05-30 | 2019-10-18 | 南京航空航天大学 | It is a kind of with the impact-air film compound cooling structure for dividing shape groove |
-
2022
- 2022-05-26 CN CN202210586109.2A patent/CN114856731A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130209233A1 (en) * | 2012-02-15 | 2013-08-15 | United Technologies Corporation | Cooling hole with enhanced flow attachment |
| CN103968418A (en) * | 2014-05-26 | 2014-08-06 | 西北工业大学 | Double-layer-wall heat insulation screen used for afterburner |
| CN110344886A (en) * | 2019-05-30 | 2019-10-18 | 南京航空航天大学 | It is a kind of with the impact-air film compound cooling structure for dividing shape groove |
Non-Patent Citations (2)
| Title |
|---|
| 叶程: "新型空气/煤油双层壁冷却结构流动换热特性研究", 《CNKI硕士学位论文全文库》 * |
| 吴青: "高温壁面的空气-燃油组合冷却方式研究", 《CNKI硕士学位论文全文库》 * |
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Application publication date: 20220805 |
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