CN116499690B - Fuel system anti-gas clamping device for large combustion wind tunnel and use method - Google Patents
Fuel system anti-gas clamping device for large combustion wind tunnel and use method Download PDFInfo
- Publication number
- CN116499690B CN116499690B CN202310753810.3A CN202310753810A CN116499690B CN 116499690 B CN116499690 B CN 116499690B CN 202310753810 A CN202310753810 A CN 202310753810A CN 116499690 B CN116499690 B CN 116499690B
- Authority
- CN
- China
- Prior art keywords
- fuel supply
- pressure
- branch
- valve
- backflow
- 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.)
- Active
Links
- 239000000446 fuel Substances 0.000 title claims abstract description 165
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 27
- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000007599 discharging Methods 0.000 claims abstract description 9
- 238000005086 pumping Methods 0.000 claims abstract description 3
- 238000002955 isolation Methods 0.000 claims description 60
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 28
- 238000010992 reflux Methods 0.000 claims description 26
- 239000007789 gas Substances 0.000 claims description 19
- 229910052757 nitrogen Inorganic materials 0.000 claims description 14
- 238000011049 filling Methods 0.000 claims description 9
- 238000011144 upstream manufacturing Methods 0.000 claims description 9
- 238000000605 extraction Methods 0.000 claims description 4
- 239000007788 liquid Substances 0.000 description 4
- NNPPMTNAJDCUHE-UHFFFAOYSA-N isobutane Chemical compound CC(C)C NNPPMTNAJDCUHE-UHFFFAOYSA-N 0.000 description 2
- 239000007800 oxidant agent Substances 0.000 description 2
- 230000001590 oxidative effect Effects 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000000889 atomisation Methods 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000001282 iso-butane Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Abstract
The invention belongs to the technical field of hypersonic high-temperature wind tunnel tests, and discloses a fuel system anti-gas clamping device for a large combustion wind tunnel and a use method thereof. The fuel system anti-gas clamping device comprises a high-pressure fuel supply tank, a high-pressure supply pipeline isolating valve, a high-point gas discharging branch and a tail end backflow branch; the high-pressure fuel supply tank supplies high-pressure fuel to the heater through the fuel supply pipe; a high-point bleed branch is provided at a high point of the fuel supply line and a terminal return branch is provided at a low point of the fuel supply line. The method of use includes a vacuum pumping workflow, a fueling workflow, a high point bleed and a reflow workflow that are sequentially developed. According to the anti-gas clamping device of the fuel system and the use method, by adding the branch on the fuel system, insoluble gas mixed in the fuel supply pipeline is discharged to the maximum extent, so that the stability and the reliability of the fuel system are enhanced, the accurate supply of the flow of the fuel system is realized, and the use safety of the high-power high-pressure combustion heater is ensured.
Description
Technical Field
The invention belongs to the technical field of hypersonic high-temperature wind tunnel tests, and particularly relates to a fuel system anti-gas clamping device for a large combustion wind tunnel and a use method thereof.
Background
The total air flow temperature of the real flight condition of the hypersonic aircraft is reproduced, the hypersonic aircraft engine test, the engine propulsion integrated test and the large-area thermal structure test are developed, a hypersonic high-temperature wind tunnel is needed, and the hypersonic high-temperature wind tunnel usually adopts a high-power high-pressure combustion heater and belongs to a combustion type wind tunnel. 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 air flow, the high-speed jet flow is formed by expansion and acceleration of a hypersonic jet pipe, and the high-speed jet flow carries out aerodynamic test on an engine, an aircraft or a thermal structural component arranged in a test section.
The fuel 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 fuel system consists of a low-pressure storage system and a high-pressure supply system, the high-pressure supply system pressurizes fuel in a high-pressure storage tank through high-pressure nitrogen, the high-pressure storage tank supplies isobutane fuel with flow and pressure required by a test to the combustion heater, and the working pressure of the high-pressure storage tank is up to 35MPa.
The high-power high-pressure combustion heater adopts a gas-liquid combustion principle, wherein an oxidant is in a gaseous state, and a fuel is in a liquid state. The liquid fuel is atomized and then reacts with the oxidant for combustion, and the continuous transportation of the fuel in the pipeline and the atomization mechanism of the nozzle determine that the liquid fuel in the pipeline cannot have the insoluble gas, otherwise, the insoluble gas can influence the stable supply of the fuel in the pipeline and the performance of the combustion heater, and even the phenomenon of non-ignition or deflagration of the heater occurs. Therefore, the prevention of the air inclusion of the fuel system is the basis for ensuring the normal operation of the hypersonic high-temperature wind tunnel and is also a preceding technical condition for ensuring the safe operation of the hypersonic high-temperature wind tunnel.
Currently, there is a need to develop a fuel system anti-pinch device for large combustion wind tunnels and a method of use.
Disclosure of Invention
The invention aims to provide a fuel system anti-trapping device for a large combustion wind tunnel, and the other technical problem to be solved is to provide a use method of the fuel system anti-trapping device for the large combustion wind tunnel, which is used for eliminating the harm of fuel trapping of a fuel system in a hypersonic high-temperature wind tunnel.
The invention relates to a fuel system anti-clamping device for a large combustion wind tunnel, which is characterized by comprising a high-pressure fuel supply tank, a high-pressure supply pipeline isolating valve, a high-point air release branch and a tail end backflow branch; the high-pressure fuel supply tank supplies high-pressure fuel to the heater through the fuel supply pipe; a high-point bleed branch is provided at a high point of the fuel supply line and a terminal return branch is provided at a low point of the fuel supply line.
Further, the high-pressure fuel supply tank supplies fuel to the heater; the upstream of the high-pressure fuel supply tank is connected with a high-pressure nitrogen system through a high-pressure nitrogen valve, and the downstream of the high-pressure fuel supply tank is connected with a heater through a fuel supply pipeline; the operating pressure of the high-pressure fuel supply tank is at most 35MPa.
Further, the high-pressure supply pipeline isolation valve comprises a high-pressure fuel supply tank root valve positioned at the upstream of the fuel supply pipeline, and the high-pressure fuel supply tank root valve is arranged at the outlet end of the high-pressure fuel supply tank; the fuel supply pipe main valve is arranged at the inlet end of the heater.
Further, the high-point air release branch is higher than the elbow and the reducing equipment of the fuel supply pipeline and comprises a plurality of high-point air release branches connected in parallel; the upper ends of the high-point air release branches are combined into outlet ends, and the outlet ends are connected with the downstream of the tail-end backflow branches;
the pressure level of the high-point deflation branch circuit is the same as that of the high-point deflation isolation valve; the gas flow direction in the high-point gas release branch is upward; the high-point air release isolation valve adopts a high-pressure ball valve.
Further, the tail end backflow branch is connected to the upstream of the main valve of the fuel supply pipeline through a backflow branch isolation valve, the downstream of the tail end backflow branch is connected with the outlet end of the high-point air release branch, and the outlet end of the tail end backflow branch is provided with a backflow isolation valve;
the reflux isolation valve, the tail end reflux branch and the reflux branch isolation valve are the same as the pressure level of the fuel supply pipeline; the gas flow direction in the tail end reflux branch is downward; the reflux branch isolation valve adopts a high-pressure ball valve.
The invention relates to a method for using a fuel system anti-air-clamping device for a large combustion wind tunnel,
the method comprises a vacuum pumping work flow, a fuel filling work flow, a high-point air discharging work flow and a reflux work flow which are sequentially developed;
s10, vacuum air extraction working flow;
s11, closing all valves of an anti-air clamping device of the fuel system;
s12, vacuumizing the heater;
s13, closing a root valve of the high-pressure fuel supply tank, opening a main valve of the fuel supply pipeline, and vacuumizing a fuel supply pipeline between the root valve of the high-pressure fuel supply tank and the main valve of the fuel supply pipeline for at least 2 times;
s14, closing a main valve of a fuel supply pipeline;
s20, a fuel filling flow;
s21, opening a high-pressure nitrogen valve, and pressurizing the high-pressure fuel supply tank by 0.8MPa;
s22, opening a root valve of the high-pressure fuel supply tank, and filling the high-pressure fuel into a fuel supply pipeline for 30s;
s23, opening a backflow branch isolation valve and a backflow isolation valve, performing backflow overflow operation, discharging redundant gas at the tail end of a fuel supply pipeline in a backflow discharge mode, and closing the backflow branch isolation valve after the discharge is finished;
s30, high-point air release and backflow processes;
s31, opening a high-pressure nitrogen valve, pressurizing 1MPa in a high-pressure fuel supply tank, simultaneously opening a high-point deflation isolation valve, a backflow branch isolation valve and a backflow isolation valve, and discharging gas deposited at corners, dead zones and high points through the backflow isolation valve in an overflow mode;
s32, closing each high-point air release isolation valve, each reflux branch isolation valve and each reflux isolation valve;
s33, repeating S31 and S32 at least 5 times.
The invention provides an anti-gas-clamping device of a fuel system for a large combustion wind tunnel and a use method thereof, which are based on the basic principle of the combustion wind tunnel and the characteristic analysis of the fuel system, and by adding a branch on the fuel system, insoluble gas mixed in a fuel supply pipeline is discharged to the maximum extent, so that the stability and the reliability of the fuel system are enhanced, the accurate supply of the flow of the fuel system is realized, the use safety of a high-power high-pressure combustion heater is ensured, and a safe, economical and high-performance anti-gas-clamping solution of the fuel system is provided for the fuel system of the hypersonic high-temperature wind tunnel.
Drawings
FIG. 1 is a schematic diagram of a fuel system anti-pinch device for a large combustion wind tunnel according to the present invention.
In the figure, 1. A high pressure nitrogen valve; 2. a high-pressure fuel supply tank; 3. a high pressure fuel supply tank root valve; 4. a fuel supply pipe; 5. a high-point deflation isolating valve I; 6. a high-point air release isolation valve II; 7. a high point bleed branch; 8. a fuel supply line main valve; 9. a heater; 10. a return branch isolation valve; 11. a terminal reflow branch; 12. a backflow isolation valve.
Detailed Description
The invention is described in detail below with reference to the drawings and examples.
Example 1:
as shown in fig. 1, the fuel system anti-pinch device for a large combustion wind tunnel of the present embodiment includes a high-pressure fuel supply tank 2, a high-pressure supply line isolation valve, a high-point bleed branch 7, and a terminal return branch 11; the high-pressure fuel supply tank 2 supplies high-pressure fuel to the heater 9 through the fuel supply pipe 4; a high-point bleed branch 7 is provided at the high point of the fuel supply line 4 and a terminal return branch 11 is provided at the low point of the fuel supply line 4.
Further, the high-pressure fuel supply tank 2 supplies fuel to the heater 9; the upstream of the high-pressure fuel supply tank 2 is connected with a high-pressure nitrogen system through a high-pressure nitrogen valve 1, and the downstream is connected with a heater 9 through a fuel supply pipeline 4; the operating pressure of the high-pressure fuel supply tank 2 is at most 35MPa.
Further, the high-pressure supply pipeline isolation valve comprises a high-pressure fuel supply tank root valve 3 positioned upstream of the fuel supply pipeline 4, and the high-pressure fuel supply tank root valve 3 is arranged at the outlet end of the high-pressure fuel supply tank 2; also included is a fuel supply line main valve 8 downstream of the fuel supply line 4, the fuel supply line main valve 8 being disposed at the inlet end of the heater 9.
Further, the high-point air release branch 7 is higher than the elbow and diameter-changing equipment of the fuel supply pipeline 4 and comprises a plurality of high-point air release branches 7 which are connected in parallel; the high-point air release branches 7 are provided with independent high-point air release isolation valves, the lower ends of the high-point air release branches 7 are respectively connected with the fuel supply pipeline 4, the upper ends of the high-point air release branches 7 are combined into outlet ends, and the outlet ends are connected with the downstream of the tail end reflux branch 11;
the pressure level of the high-point deflation branch circuit 7 is the same as that of the high-point deflation isolation valve; the gas flow direction in the high-point gas release branch 7 is upward; the high-point air release isolation valve adopts a high-pressure ball valve.
Further, the tail end backflow branch 11 is connected to the upstream of the main valve 8 of the fuel supply pipeline through a backflow branch isolation valve 10, the downstream of the tail end backflow branch 11 is connected with the outlet end of the high-point deflation branch 7, and the outlet end of the tail end backflow branch 11 is provided with a backflow isolation valve 12;
the pressure level of the return isolation valve 12, the end return branch 11, the return branch isolation valve 10 and the fuel supply pipe 4 is the same; the gas flow direction inside the end return branch 11 is downward; the return branch isolation valve 10 is a high pressure ball valve.
The application method of the fuel system anti-air clamping device for the large combustion wind tunnel comprises a vacuum air extraction work flow, a fuel filling work flow, a high-point air discharge work flow and a backflow work flow which are sequentially developed;
s10, vacuum air extraction working flow;
s11, closing all valves of an anti-air clamping device of the fuel system;
s12, vacuumizing the heater 9;
s13, closing the high-pressure fuel supply tank root valve 3, opening the fuel supply pipeline main valve 8, and vacuumizing the fuel supply pipeline 4 between the high-pressure fuel supply tank root valve 3 and the fuel supply pipeline main valve 8 for at least 2 times;
s14, closing a main valve 8 of a fuel supply pipeline;
s20, a fuel filling flow;
s21, opening a high-pressure nitrogen valve 1, and pressurizing the high-pressure fuel supply tank 2 by 0.8MPa;
s22, opening a high-pressure fuel supply tank root valve 3, and filling high-pressure fuel 30s into a fuel supply pipeline 4;
s23, opening the reflux branch isolation valve 10 and the reflux isolation valve 12, performing reflux overflow operation, discharging redundant gas at the tail end of the fuel supply pipeline 4 in a reflux discharge mode, and closing the reflux branch isolation valve 10 after the discharge is finished;
s30, high-point air release and backflow processes;
s31, opening the high-pressure nitrogen valve 1, pressurizing 1MPa in the high-pressure fuel supply tank 2, simultaneously opening each high-point deflation isolating valve, each reflux branch isolating valve 10 and each reflux isolating valve 12, and discharging gas deposited at corners, dead areas and high points through the reflux isolating valves 12 in an overflow mode;
s32, closing each high-point air release isolation valve, each reflux branch isolation valve 10 and each reflux isolation valve 12;
s33, repeating S31 and S32 at least 5 times.
In this embodiment, there are 2 parallel high-point air release branches 7, and the corresponding high-point air release isolation valves are respectively a high-point air release isolation valve i 5 and a high-point air release isolation valve ii 6. The high-pressure fuel supply tank 2 is a key device for stably supplying fuel to the heater 9. The purpose of opening the return branch isolation valve 10 in S31 of the high point bleed and return flow path is to increase the fluidity of the fuel supply pipe 4, improving the exhaust efficiency.
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 (2)
1. The fuel system anti-clamping device for the large combustion wind tunnel is characterized by comprising a high-pressure fuel supply tank (2), a high-pressure supply pipeline isolating valve, a high-point air release branch (7) and a tail end backflow branch (11); the high-pressure fuel supply tank (2) supplies high-pressure fuel to the heater (9) through the fuel supply pipe (4); a high-point air release branch (7) is arranged at the high point of the fuel supply pipeline (4), and an end reflux branch (11) is arranged at the low point of the fuel supply pipeline (4);
the high-pressure fuel supply tank (2) supplies fuel to the heater (9); the upstream of the high-pressure fuel supply tank (2) is connected with a high-pressure nitrogen system through a high-pressure nitrogen valve (1), and the downstream is connected with a heater (9) through a fuel supply pipeline (4); the working pressure of the high-pressure fuel supply tank (2) is at most 35MPa;
the high-pressure supply pipeline isolation valve comprises a high-pressure fuel supply tank root valve (3) which is positioned at the upstream of the fuel supply pipeline (4), and the high-pressure fuel supply tank root valve (3) is arranged at the outlet end of the high-pressure fuel supply tank (2); the fuel supply pipeline main valve (8) is positioned at the downstream of the fuel supply pipeline (4), and the fuel supply pipeline main valve (8) is arranged at the inlet end of the heater (9);
the high-point air release branch (7) is higher than the elbow and diameter-changing equipment of the fuel supply pipeline (4) and comprises a plurality of high-point air release branches (7) which are connected in parallel; the high-point air release branches (7) are provided with independent high-point air release isolation valves, the lower ends of the high-point air release branches (7) are respectively connected with a fuel supply pipeline (4), the upper ends of the high-point air release branches (7) are combined into outlet ends, and the outlet ends are connected with the downstream of the tail end reflux branch (11);
the pressure level of the high-point deflation branch circuit (7) is the same as that of the high-point deflation isolation valve; the gas flow direction in the high-point deflation branch (7) is upward; the high-point air release isolation valve adopts a high-pressure ball valve;
the tail end backflow branch (11) is connected to the upstream of the main valve (8) of the fuel supply pipeline through a backflow branch isolation valve (10), the downstream of the tail end backflow branch (11) is connected with the outlet end of the high-point air release branch (7), and the outlet end of the tail end backflow branch (11) is provided with a backflow isolation valve (12);
the pressure level of the reflux isolation valve (12), the tail end reflux branch (11) and the reflux branch isolation valve (10) is the same as that of the fuel supply pipeline (4); the gas flow direction in the tail end reflux branch (11) is downward; the reflux branch isolation valve (10) adopts a high-pressure ball valve.
2. A method for using the fuel system anti-pinch device for a large combustion wind tunnel, which is used for the fuel system anti-pinch device for a large combustion wind tunnel as claimed in claim 1, and is characterized in that the method comprises a vacuum pumping work flow, a fuel filling work flow, a high-point air discharging work flow and a back flow work flow which are sequentially developed;
s10, vacuum air extraction working flow;
s11, closing all valves of an anti-air clamping device of the fuel system;
s12, vacuumizing the heater (9);
s13, closing a high-pressure fuel supply tank root valve (3), opening a fuel supply pipeline main valve (8), and vacuumizing a fuel supply pipeline (4) between the high-pressure fuel supply tank root valve (3) and the fuel supply pipeline main valve (8) at least 2 times;
s14, closing a main valve (8) of a fuel supply pipeline;
s20, a fuel filling flow;
s21, opening a high-pressure nitrogen valve (1) and pressurizing the high-pressure fuel supply tank (2) by 0.8MPa;
s22, opening a high-pressure fuel supply tank root valve (3) and filling the fuel supply pipeline (4) with high-pressure fuel 30s;
s23, opening a backflow branch isolation valve (10) and a backflow isolation valve (12), performing backflow overflow operation, discharging redundant gas at the tail end of a fuel supply pipeline (4) in a backflow discharge mode, and closing the backflow branch isolation valve (10) after the discharge is finished;
s30, high-point air release and backflow processes;
s31, opening a high-pressure nitrogen valve (1), pressurizing 1MPa in a high-pressure fuel supply tank (2), opening a high-point deflation isolation valve, a backflow branch isolation valve (10) and a backflow isolation valve (12), and discharging gas deposited at corners, dead areas and high points through the backflow isolation valve (12) in an overflow mode;
s32, closing each high-point air release isolation valve, a backflow branch isolation valve (10) and a backflow isolation valve (12);
s33, repeating S31 and S32 at least 5 times.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310753810.3A CN116499690B (en) | 2023-06-26 | 2023-06-26 | Fuel system anti-gas clamping device for large combustion wind tunnel and use method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310753810.3A CN116499690B (en) | 2023-06-26 | 2023-06-26 | Fuel system anti-gas clamping device for large combustion wind tunnel and use method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116499690A CN116499690A (en) | 2023-07-28 |
| CN116499690B true CN116499690B (en) | 2023-09-01 |
Family
ID=87320504
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310753810.3A Active CN116499690B (en) | 2023-06-26 | 2023-06-26 | Fuel system anti-gas clamping device for large combustion wind tunnel and use method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116499690B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05340312A (en) * | 1992-06-08 | 1993-12-21 | Unisia Jecs Corp | Trouble diagnostic device of exhaust gas reflux device |
| CN102216573A (en) * | 2010-01-28 | 2011-10-12 | 丰田自动车株式会社 | Controller of internal combustion engine, and device for measuring mass flow of nox refluxed back to intake passage along with blow-by gas |
| CN104995393A (en) * | 2012-12-17 | 2015-10-21 | 西港能源有限公司 | Air-enriched gaseous fuel direct injection for an internal combustion engine |
| CN105518430A (en) * | 2013-07-12 | 2016-04-20 | Avl里斯脱有限公司 | Device and method for continuously measuring the dynamic fuel consumption of an internal combustion engine |
| CN110182044A (en) * | 2018-02-23 | 2019-08-30 | 福特全球技术公司 | Filling entrance with fluid separation |
| CN113864645A (en) * | 2021-08-25 | 2021-12-31 | 上海空间推进研究所 | Blowing system for rail-controlled engine ground test |
| CN114264447A (en) * | 2021-12-31 | 2022-04-01 | 西安交通大学 | Injection type shock tube and method |
| CN116044613A (en) * | 2022-07-29 | 2023-05-02 | 西安航天动力研究所 | Extrusion test run system and method for liquid oxygen kerosene gas generator |
| CN116067606A (en) * | 2023-03-31 | 2023-05-05 | 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 overall layout method |
-
2023
- 2023-06-26 CN CN202310753810.3A patent/CN116499690B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05340312A (en) * | 1992-06-08 | 1993-12-21 | Unisia Jecs Corp | Trouble diagnostic device of exhaust gas reflux device |
| CN102216573A (en) * | 2010-01-28 | 2011-10-12 | 丰田自动车株式会社 | Controller of internal combustion engine, and device for measuring mass flow of nox refluxed back to intake passage along with blow-by gas |
| CN104995393A (en) * | 2012-12-17 | 2015-10-21 | 西港能源有限公司 | Air-enriched gaseous fuel direct injection for an internal combustion engine |
| CN105518430A (en) * | 2013-07-12 | 2016-04-20 | Avl里斯脱有限公司 | Device and method for continuously measuring the dynamic fuel consumption of an internal combustion engine |
| CN110182044A (en) * | 2018-02-23 | 2019-08-30 | 福特全球技术公司 | Filling entrance with fluid separation |
| CN113864645A (en) * | 2021-08-25 | 2021-12-31 | 上海空间推进研究所 | Blowing system for rail-controlled engine ground test |
| CN114264447A (en) * | 2021-12-31 | 2022-04-01 | 西安交通大学 | Injection type shock tube and method |
| CN116044613A (en) * | 2022-07-29 | 2023-05-02 | 西安航天动力研究所 | Extrusion test run system and method for liquid oxygen kerosene gas generator |
| CN116067606A (en) * | 2023-03-31 | 2023-05-05 | 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 overall layout method |
Non-Patent Citations (1)
| Title |
|---|
| 注油方式对超燃冲压发动机燃烧性能的影响;邓维鑫 等;航空动力学报;第28卷(第07期);第1449-1457页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116499690A (en) | 2023-07-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN116499690B (en) | Fuel system anti-gas clamping device for large combustion wind tunnel and use method | |
| CN116046320B (en) | Hypersonic high-temperature wind tunnel pneumatic layout method | |
| CN107587954A (en) | Gas oxygen kerosene Rocket Engines pressurizing transmission system and small rocket motor propellant-feed system | |
| CN109538379B (en) | Device and method for testing thrust chamber of high-thrust liquid rocket engine | |
| US20070095068A1 (en) | Methods and apparatus for operating gas turbine engines | |
| CN113446130B (en) | Final-stage passivation method for liquid oxygen kerosene of carrier rocket | |
| CN102913752B (en) | Unloading and liquid adding device for skid-type liquid adding station and unloading and liquid adding method | |
| CN204344305U (en) | Shutdown pilot system before a kind of one push start turbopump-fed liquid rocket engine pump | |
| CN108045587B (en) | Waste heat recovery system of oxygen consumption type inerting fuel tank based on thermoelectric generation technology | |
| CN112460635B (en) | Air-entraining purging method for dual-fuel gas turbine | |
| CN106917685A (en) | Entrance heat extraction control system | |
| CN103711610A (en) | RBCC fuel gas generator integrated supplying and adjusting system based on liquid oxygen | |
| CN112727604A (en) | Liquid/gas dual fuel supply system for gas turbine | |
| CN114810350B (en) | Methane precooling turbine-based combined cycle engine system with interstage combustion chamber | |
| CN1779225B (en) | Methods and systems for operating oxidizer systems | |
| CN110907123B (en) | High-enthalpy propulsion wind tunnel air heating method and device | |
| CN110963059A (en) | Cabin pressurization and oxygenation device and method based on hollow fiber membrane airborne nitrogen production technology | |
| CN114427975A (en) | Tandem type combined power mode conversion verification method | |
| EP3147484A1 (en) | Method and system for reliable gas to liquid transfer | |
| CN211711102U (en) | Cabin pressurization and oxygenation device based on hollow fiber membrane airborne nitrogen production technology | |
| CN111305978A (en) | Gas engine gas supply device with step gas supply pressure and control method thereof | |
| CN113588233B (en) | Exhaust back pressure adjusting system and method suitable for turbine test bed | |
| CN214145700U (en) | Double-machine circulation precooling system based on asymmetric backflow | |
| CN214198146U (en) | Hydrogen recycling system diffuses in hydrogenation station | |
| CN116044613A (en) | Extrusion test run system and method for liquid oxygen kerosene gas generator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |