CN116498896A - Fuel supply system of hypersonic high-temperature wind tunnel and design method thereof - Google Patents
Fuel supply system of hypersonic high-temperature wind tunnel and design method thereof Download PDFInfo
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- CN116498896A CN116498896A CN202310762352.XA CN202310762352A CN116498896A CN 116498896 A CN116498896 A CN 116498896A CN 202310762352 A CN202310762352 A CN 202310762352A CN 116498896 A CN116498896 A CN 116498896A
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- fuel supply
- pressure
- supply tank
- pressure fuel
- valve
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- 239000000446 fuel Substances 0.000 title claims abstract description 138
- 238000013461 design Methods 0.000 title claims abstract description 26
- 238000000034 method Methods 0.000 title claims abstract description 14
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 45
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 22
- 238000003466 welding Methods 0.000 claims abstract description 14
- 238000012360 testing method Methods 0.000 claims abstract description 13
- 238000002485 combustion reaction Methods 0.000 claims abstract description 10
- 238000007789 sealing Methods 0.000 claims abstract description 9
- 238000009434 installation Methods 0.000 claims description 15
- 238000004519 manufacturing process Methods 0.000 claims description 9
- 239000000178 monomer Substances 0.000 claims description 9
- 239000002360 explosive Substances 0.000 claims description 7
- NNPPMTNAJDCUHE-UHFFFAOYSA-N isobutane Chemical compound CC(C)C NNPPMTNAJDCUHE-UHFFFAOYSA-N 0.000 claims description 6
- 230000000694 effects Effects 0.000 claims description 3
- 239000001282 iso-butane Substances 0.000 claims description 3
- 229910001873 dinitrogen Inorganic materials 0.000 claims 1
- 238000003860 storage Methods 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000010763 heavy fuel oil Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/02—Pipe-line systems for gases or vapours
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D3/00—Arrangements for supervising or controlling working operations
- F17D3/01—Arrangements for supervising or controlling working operations for controlling, signalling, or supervising the conveyance of a product
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D5/00—Protection or supervision of installations
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the technical field of hypersonic high-temperature wind tunnel tests, and discloses a fuel supply system of a hypersonic high-temperature wind tunnel and a design method thereof. The main body of the fuel supply system is a high-pressure fuel supply tank, the top end of the fuel supply system is connected with an input pipeline through a Kalman I, the input pipeline is externally connected with a high-pressure nitrogen source through a high-pressure nitrogen valve, the tail end of the fuel supply system is connected with a supply pipeline through a Kalman II, and the supply pipeline is sequentially connected with a high-pressure fuel supply tank root valve, a Venturi cavitation pipe, a high-pressure fuel supply tank main valve and a combustion heater; the front end and the rear end of the Venturi cavitation tube are fixed through the clamping flanges; the front end and the rear end of the high-pressure nitrogen valve, the high-pressure fuel supply tank root valve and the main valve of the high-pressure fuel supply tank are fixed through welding flanges. The design method comprises the steps of classifying equipment contained in the fuel supply system, selecting a connection mode and installing. The quick and reliable sealing connection of the high-pressure pipeline of the fuel supply system is realized by adopting the flange welding in combination with the flange, and the safety and the reliability of the hypersonic high-temperature wind tunnel are improved.
Description
Technical Field
The invention belongs to the technical field of hypersonic high-temperature wind tunnel tests, and particularly relates to a fuel supply system of a hypersonic high-temperature wind tunnel and a design method thereof.
Background
The hypersonic high-temperature wind tunnel can reproduce the total air flow temperature under the real flight condition of the hypersonic aircraft, and is one of key equipment for developing hypersonic aircraft engine tests, organism propulsion integrated tests and large-area thermal structure tests. When the hypersonic high-temperature wind tunnel runs, a mixture of high-pressure fuel, high-pressure air and liquid oxygen is combusted and heated in a high-power high-pressure combustion heater to form high-temperature high-pressure airflow, the high-temperature high-pressure airflow is expanded and accelerated through a hypersonic jet pipe to form high-speed jet flow, and an aerodynamic test is carried out on an engine, an aircraft or a thermal structural component arranged in a test section.
The hypersonic high-temperature wind tunnel consists of a low-pressure storage system and a high-pressure supply system; the low-pressure storage system stores the fuel required by the test for a long time, and also carries out emergency release and recovers the residual fuel of the test; the high pressure supply system pressurizes fuel in a high pressure fuel supply tank, which supplies fuel of a flow rate and pressure required for the test to the combustion heater, with high pressure nitrogen. The fuel supply system is one of main subsystems of the hypersonic high-temperature wind tunnel and is mainly used for providing fuel necessary for the hypersonic high-temperature wind tunnel to operate.
The hypersonic high-temperature wind tunnel generally adopts flammable and explosive media as fuel, the working pressure of a high-pressure supply system is up to 35MPa, and if high-pressure leakage occurs, serious safety accidents can be caused. Therefore, high demands are placed on the tightness and reliability of the piping connections of the high pressure supply system equipment.
Currently, there is a need to develop a fuel supply system for hypersonic high temperature wind tunnels and a design method thereof.
Disclosure of Invention
The invention aims to solve the technical problem of providing a fuel supply system of a hypersonic high-temperature wind tunnel, and the invention aims to solve the technical problem of a design method of the fuel supply system of the hypersonic high-temperature wind tunnel, which is used for overcoming the defects of the prior art.
The fuel supply system of the hypersonic high-temperature wind tunnel is characterized in that a main body of the fuel supply system is a high-pressure fuel supply tank; the top end of the high-pressure fuel supply tank is connected with an input pipeline through a kalant I, and the input pipeline is externally connected with a high-pressure nitrogen source through a high-pressure nitrogen valve; the tail end of the high-pressure fuel supply tank is connected with a supply pipeline through a Kalan II, and the supply pipeline is sequentially connected with a root valve of the high-pressure fuel supply tank, a Venturi cavitation pipe, a main valve of the high-pressure fuel supply tank and a combustion heater;
the front end and the rear end of the Venturi cavitation tube are fixed through the clamping flanges; the front end and the rear end of the high-pressure nitrogen valve, the high-pressure fuel supply tank root valve and the main valve of the high-pressure fuel supply tank are fixed through welding flanges.
Further, the pressure range of the high pressure is 0.1-35 MPa.
Further, the high-pressure fuel supply tank is used for storing inflammable and explosive media including isobutane; the high pressure fuel supply tank provides fuel to the combustion heater at a design pressure of up to 35MPa.
Further, the design pressure of the root valve of the high-pressure fuel supply tank and the main valve of the high-pressure fuel supply tank is the same as the design pressure of the high-pressure fuel supply tank, and is at most 35MPa; the high-pressure fuel supply tank root valve and the high-pressure fuel supply tank main valve both adopt soft sealing ball valves.
Furthermore, the high-pressure nitrogen valve, the high-pressure fuel supply tank root valve and the main valve of the high-pressure fuel supply tank are installed in a top-mounted mode, and overhaul is not affected.
Further, the venturi cavitation tube utilizes the venturi effect to stabilize the supply flow of the control pipeline; the venturi tubes with different throat diameters are disassembled and replaced, so that different fuel flow supply requirements required by hypersonic high-temperature wind tunnel tests are met.
The design method of the fuel supply system of the hypersonic high-temperature wind tunnel comprises the following steps:
s10, classifying equipment contained in a fuel supply system;
dividing the fuel supply system into equipment to be disassembled, large monomer manufacturing equipment and a high-pressure valve; wherein, the venturi cavitation tube belongs to the equipment which needs to be disassembled; the high-pressure fuel supply tank belongs to large-scale monomer manufacturing equipment; a high-pressure nitrogen valve, a high-pressure fuel supply tank root valve and a high-pressure fuel supply tank main valve belong to a high-pressure valve;
s20, selecting a connection mode;
for equipment to be disassembled, the two ends of the venturi cavitation tube are fixed through the clamping flanges, and the venturi tubes with different throat diameters of the venturi cavitation tube are convenient to disassemble and replace by utilizing the characteristics of small volume and high-pressure self-sealing of the clamping flanges;
for large-scale monomer manufacturing equipment, the characteristics of small volumes of a flange I and a flange II and adaptation to a narrow installation space in a skirt of a high-pressure fuel supply tank are utilized, the top end of the high-pressure fuel supply tank is connected with an input pipeline through the flange I, and the tail end of the high-pressure fuel supply tank is connected with a supply pipeline through the flange II;
for the high-pressure valve, the front and rear ends of the high-pressure nitrogen valve, the high-pressure fuel supply tank root valve and the main valve of the high-pressure fuel supply tank are fixed through welding flanges, so that leakage at the joint is avoided, and meanwhile, top-mounted installation is adopted, so that the overhaul is convenient;
s30, mounting;
and (3) carrying out installation connection according to a design plan, detecting connection quality after the installation is completed, and ensuring that welded welding seams are even and free of leakage, and the flange connection is tight and free of leakage.
The fuel supply system of the hypersonic high-temperature wind tunnel and the design method thereof utilize the characteristics of small volume and high-pressure self-sealing of the kalman, are used in a position with a small installation space and needs quick replacement, and can meet the connection requirement of the fuel supply system.
According to the fuel supply system of the hypersonic high-temperature wind tunnel and the design method thereof, the high-pressure valve is installed by utilizing the characteristic of good sealing performance of flange welding installation, and meanwhile, top-mounted installation is adopted, so that the maintenance is convenient, and the connection requirement of the fuel supply system can be met.
The fuel supply system and the design method of the hypersonic high-temperature wind tunnel adopt a connection mode of welding a flange by adopting a Kalan, so that the quick and reliable sealing connection of a high-pressure pipeline of the fuel supply system is realized, the possibility of high-pressure conveying leakage of the combustible and explosive medium fuel is reduced to the minimum, the safe use of the combustible and explosive medium fuel is ensured to the maximum extent, the safe, reliable and economic transportation of the high-pressure and explosive medium fuel of the hypersonic high-temperature wind tunnel is realized, and the safety and reliability of the hypersonic high-temperature wind tunnel are improved.
Drawings
Fig. 1 is a schematic structural diagram of a fuel supply system of a hypersonic high temperature wind tunnel of the present invention.
In the figure, 1. Kalan I; 2. a high pressure nitrogen valve; 3. a high-pressure fuel supply tank; 4. kalan II; 5. a supply conduit; 6. a high pressure fuel supply tank root valve; 7. welding a flange; 8. a venturi cavitation tube; 9. a high pressure fuel supply tank main valve; 10. a combustion heater.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
Example 1:
the fuel supply system of the hypersonic high-temperature wind tunnel and the design method thereof of the embodiment are successfully applied to a hypersonic high-temperature wind tunnel fuel supply system in the China center for aerodynamic research and development.
As shown in fig. 1, the main body of the fuel supply system of the hypersonic high temperature wind tunnel of the present embodiment is a high pressure fuel supply tank 3; the top end of the high-pressure fuel supply tank 3 is connected with an input pipeline through a kalant I1, and the input pipeline is externally connected with a high-pressure nitrogen source through a high-pressure nitrogen valve 2; at the end of the high-pressure fuel supply tank 3, a supply pipe 5 is connected through a kalan II 4, and a high-pressure fuel supply tank root valve 6, a Venturi cavitation pipe 8, a high-pressure fuel supply tank main valve 9 and a combustion heater 10 are sequentially connected to the supply pipe 5;
the front end and the rear end of the Venturi cavitation tube 8 are fixed through a clamping flange; the front end and the rear end of the high-pressure nitrogen valve 2, the high-pressure fuel supply tank root valve 6 and the high-pressure fuel supply tank main valve 9 are fixed through welding flanges 7.
Further, the pressure range of the high pressure is 0.1-35 MPa.
Further, the high-pressure fuel supply tank 3 is used for storing inflammable and explosive mediums including isobutane; the high-pressure fuel supply tank 3 supplies fuel to the combustion heater 10 at a design pressure of up to 35MPa.
Further, the design pressure of the high-pressure fuel supply tank root valve 6 and the high-pressure fuel supply tank main valve 9 is the same as the design pressure of the high-pressure fuel supply tank 3, and is at most 35MPa; the high-pressure fuel supply tank root valve 6 and the high-pressure fuel supply tank main valve 9 each employ a soft seal ball valve.
Further, the high-pressure nitrogen valve 2, the high-pressure fuel supply tank root valve 6 and the high-pressure fuel supply tank main valve 9 are installed in a top-mounted mode, and overhaul is not affected.
Further, the venturi cavitation tube 8 utilizes the venturi effect to stabilize the supply flow of the control pipeline; the venturi tubes with different throat diameters are disassembled and replaced, so that different fuel flow supply requirements required by hypersonic high-temperature wind tunnel tests are met.
The design method of the fuel supply system of the hypersonic high-temperature wind tunnel of the embodiment comprises the following steps:
s10, classifying equipment contained in a fuel supply system;
dividing the fuel supply system into equipment to be disassembled, large monomer manufacturing equipment and a high-pressure valve; wherein the venturi cavitation tube 8 belongs to equipment which needs to be disassembled; the high-pressure fuel supply tank 3 belongs to a large-sized monomer manufacturing apparatus; the high-pressure nitrogen valve 2, the high-pressure fuel supply tank root valve 6 and the high-pressure fuel supply tank main valve 9 belong to high-pressure valves;
s20, selecting a connection mode;
for equipment to be disassembled, the two ends of the venturi cavitation tube 8 are fixed through the clamping flanges, and the venturi tubes with different throat diameters of the venturi cavitation tube 8 are convenient to disassemble and replace by utilizing the characteristics of small volume and high-pressure self-sealing of the clamping flanges;
for large monomer manufacturing equipment, the top end of the high-pressure fuel supply tank 3 is connected with an input pipeline through the Kalman I1, and the tail end of the high-pressure fuel supply tank 3 is connected with a supply pipeline 5 through the Kalman II 4 by utilizing the characteristics of small volumes of the Kalman I1 and the Kalman II 4 and adapting to a narrow installation space in a skirt seat of the high-pressure fuel supply tank 3;
for the high-pressure valve, the front and rear ends of the high-pressure nitrogen valve 2, the high-pressure fuel supply tank root valve 6 and the high-pressure fuel supply tank main valve 9 are fixed through the welding flange 7, so that the leakage of the joint is avoided, and meanwhile, the top-mounted installation is adopted, so that the overhaul is convenient;
s30, mounting;
and (3) carrying out installation connection according to a design plan, detecting connection quality after the installation is completed, and ensuring that welded welding seams are even and free of leakage, and the flange connection is tight and free of leakage.
The foregoing is only a preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the technical scope of the present invention disclosed in the embodiments of the present invention should be covered by the present invention.
Claims (7)
1. The fuel supply system of the hypersonic high-temperature wind tunnel is characterized in that the main body of the fuel supply system is a high-pressure fuel supply tank (3); the top end of the high-pressure fuel supply tank (3) is connected with an input pipeline through a kalant I (1), and the input pipeline is externally connected with a high-pressure nitrogen source through a high-pressure nitrogen valve (2); at the end of the high-pressure fuel supply tank (3), a supply pipeline (5) is connected through a flange II (4), and a high-pressure fuel supply tank root valve (6), a Venturi cavitation pipe (8), a high-pressure fuel supply tank main valve (9) and a combustion heater (10) are sequentially connected to the supply pipeline (5);
the front end and the rear end of the Venturi cavitation tube (8) are fixed through a clamping flange; the front end and the rear end of the high-pressure nitrogen valve (2), the high-pressure fuel supply tank root valve (6) and the high-pressure fuel supply tank main valve (9) are fixed through welding flanges (7).
2. The fuel supply system of the hypersonic high temperature wind tunnel according to claim 1, wherein the pressure range of the high pressure is 0.1mpa to 35mpa.
3. The fuel supply system of a hypersonic high temperature wind tunnel according to claim 1, characterized in that the high pressure fuel supply tank (3) is used for storing inflammable and explosive media including isobutane; a high-pressure fuel supply tank (3) supplies fuel to the combustion heater (10) at a design pressure of up to 35MPa.
4. The fuel supply system of a hypersonic high temperature wind tunnel according to claim 1 characterized in that the design pressure of the high pressure fuel supply tank root valve (6) and the high pressure fuel supply tank main valve (9) is the same as the design pressure of the high pressure fuel supply tank (3), at most 35MPa; the high-pressure fuel supply tank root valve (6) and the high-pressure fuel supply tank main valve (9) are soft sealing ball valves.
5. The fuel supply system of the hypersonic high temperature wind tunnel according to claim 1, wherein the high pressure nitrogen gas valve (2), the high pressure fuel supply tank root valve (6) and the high pressure fuel supply tank main valve (9) are installed in a top-mounted mode, and overhaul is not affected.
6. The fuel supply system of hypersonic high temperature wind tunnel according to claim 1, characterized in that the venturi cavitation tube (8) uses venturi effect to stabilize the control tube supply flow; the venturi tubes with different throat diameters are disassembled and replaced, so that different fuel flow supply requirements required by hypersonic high-temperature wind tunnel tests are met.
7. A design method of a fuel supply system of a hypersonic high temperature wind tunnel, which is used for designing the fuel supply system of the hypersonic high temperature wind tunnel according to any one of claims 1 to 6, and is characterized by comprising the following steps:
s10, classifying equipment contained in a fuel supply system;
dividing the fuel supply system into equipment to be disassembled, large monomer manufacturing equipment and a high-pressure valve; wherein the venturi cavitation tube (8) belongs to equipment which needs to be disassembled; the high-pressure fuel supply tank (3) belongs to large-scale monomer manufacturing equipment; the high-pressure nitrogen valve (2), the high-pressure fuel supply tank root valve (6) and the high-pressure fuel supply tank main valve (9) are high-pressure valves;
s20, selecting a connection mode;
for equipment to be disassembled, two ends of the venturi cavitation tube (8) are fixed through the kaleidos, and the venturi tubes with different throat diameters of the venturi cavitation tube (8) are convenient to disassemble and replace by utilizing the characteristics of small kaleidos volume and high-pressure self-sealing;
for large monomer manufacturing equipment, the characteristics of small volumes of the Kalman I (1) and the Kalman II (4) and narrow installation space in a skirt seat of a high-pressure fuel supply tank (3) are utilized, the top end of the high-pressure fuel supply tank (3) is connected with an input pipeline through the Kalman I (1), and the tail end of the high-pressure fuel supply tank (3) is connected with a supply pipeline (5) through the Kalman II (4);
for the high-pressure valve, the front and rear ends of the high-pressure nitrogen valve (2), the high-pressure fuel supply tank root valve (6) and the high-pressure fuel supply tank main valve (9) are fixed through welding flanges (7), so that leakage at the joint is avoided, and meanwhile, top-mounted installation is adopted, so that the overhaul is convenient;
s30, mounting;
and (3) carrying out installation connection according to a design plan, detecting connection quality after the installation is completed, and ensuring that welded welding seams are even and free of leakage, and the flange connection is tight and free of leakage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310762352.XA CN116498896A (en) | 2023-06-27 | 2023-06-27 | Fuel supply system of hypersonic high-temperature wind tunnel and design method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310762352.XA CN116498896A (en) | 2023-06-27 | 2023-06-27 | Fuel supply system of hypersonic high-temperature wind tunnel and design method thereof |
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| Publication Number | Publication Date |
|---|---|
| CN116498896A true CN116498896A (en) | 2023-07-28 |
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| CN202310762352.XA Pending CN116498896A (en) | 2023-06-27 | 2023-06-27 | Fuel supply system of hypersonic high-temperature wind tunnel and design method thereof |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116776453A (en) * | 2023-08-25 | 2023-09-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-temperature wind tunnel equipment body layout method |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040129311A1 (en) * | 2002-10-28 | 2004-07-08 | Courtney William L. | Combined connector-pneumatic coupler-locking inflate/deflate valve series |
| CN103672946A (en) * | 2013-11-28 | 2014-03-26 | 北京动力机械研究所 | Device for quantitatively adjusting large-flow fuel for burning under high-pressure environment |
| CN106932153A (en) * | 2017-04-27 | 2017-07-07 | 保定天威电气设备结构有限公司 | A kind of method and device of container part leak detection |
| CN107025817A (en) * | 2017-04-24 | 2017-08-08 | 北京航天试验技术研究所 | A kind of fuel feed system and kidney-yang simulation generator |
| CN108398272A (en) * | 2017-12-14 | 2018-08-14 | 中国航天空气动力技术研究院 | A kind of fuel system and method for the experiment of shock tunnel super burn engine inlets |
| CN111412301A (en) * | 2020-05-11 | 2020-07-14 | 上海一核阀门股份有限公司 | Anti-leakage valve for high-pressure gas medium |
| CN112066749A (en) * | 2020-09-09 | 2020-12-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Double-row blade air inlet distributor for vacuum high-temperature equipment |
| CN212616452U (en) * | 2020-05-29 | 2021-02-26 | 温州加利利阀门制造有限公司 | Top-mounted valve ball |
| CN115575075A (en) * | 2022-09-09 | 2023-01-06 | 中国空气动力研究与发展中心空天技术研究所 | Hydrogen fuel injector applied to high-temperature gas inflow condition |
| CN116046320A (en) * | 2023-03-31 | 2023-05-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic high-temperature wind tunnel pneumatic layout method |
-
2023
- 2023-06-27 CN CN202310762352.XA patent/CN116498896A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040129311A1 (en) * | 2002-10-28 | 2004-07-08 | Courtney William L. | Combined connector-pneumatic coupler-locking inflate/deflate valve series |
| CN103672946A (en) * | 2013-11-28 | 2014-03-26 | 北京动力机械研究所 | Device for quantitatively adjusting large-flow fuel for burning under high-pressure environment |
| CN107025817A (en) * | 2017-04-24 | 2017-08-08 | 北京航天试验技术研究所 | A kind of fuel feed system and kidney-yang simulation generator |
| CN106932153A (en) * | 2017-04-27 | 2017-07-07 | 保定天威电气设备结构有限公司 | A kind of method and device of container part leak detection |
| CN108398272A (en) * | 2017-12-14 | 2018-08-14 | 中国航天空气动力技术研究院 | A kind of fuel system and method for the experiment of shock tunnel super burn engine inlets |
| CN111412301A (en) * | 2020-05-11 | 2020-07-14 | 上海一核阀门股份有限公司 | Anti-leakage valve for high-pressure gas medium |
| CN212616452U (en) * | 2020-05-29 | 2021-02-26 | 温州加利利阀门制造有限公司 | Top-mounted valve ball |
| CN112066749A (en) * | 2020-09-09 | 2020-12-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Double-row blade air inlet distributor for vacuum high-temperature equipment |
| CN115575075A (en) * | 2022-09-09 | 2023-01-06 | 中国空气动力研究与发展中心空天技术研究所 | Hydrogen fuel injector applied to high-temperature gas inflow condition |
| CN116046320A (en) * | 2023-03-31 | 2023-05-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic high-temperature wind tunnel pneumatic layout method |
Non-Patent Citations (2)
| Title |
|---|
| 刘崇智: "高温风洞燃烧加热系统动态响应特性建模及应用研究", 中国优秀硕士学位论文全文数据库工程科技Ⅱ辑, no. 6, pages 031 - 4 * |
| 赵传良: "卡兰的施工技术", 石油化工建设, vol. 36, no. 4, pages 74 - 76 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116776453A (en) * | 2023-08-25 | 2023-09-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-temperature wind tunnel equipment body layout method |
| CN116776453B (en) * | 2023-08-25 | 2023-10-24 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-temperature wind tunnel equipment body layout method |
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