CN112945305A - Double-duct spray pipe thrust measuring platform with thrust interference elimination structure - Google Patents
Double-duct spray pipe thrust measuring platform with thrust interference elimination structure Download PDFInfo
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- CN112945305A CN112945305A CN202110163189.6A CN202110163189A CN112945305A CN 112945305 A CN112945305 A CN 112945305A CN 202110163189 A CN202110163189 A CN 202110163189A CN 112945305 A CN112945305 A CN 112945305A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- 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
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
Abstract
The application belongs to the field of jet pipes of aircraft engines, and particularly relates to a double-duct jet pipe thrust measurement platform with a thrust interference elimination structure. The method comprises the following steps: the device comprises a pressure stabilizing cabin (3), an interference elimination structural part (1), an air inlet pipeline (8), a double-duct spray pipe, a secondary flow pipeline (4) and a thrust measuring balance (2). The utility model provides a two duct spray tube thrust measurement platform with thrust interference elimination structure, through horizontal symmetry admit air, the critical slot hole of non-contact annular labyrinth seal structure and radial axisymmetric elimination air current thrust interference, adopt the thrust balance to measure two duct spray tube thrust, adopt the critical flow nozzle of many throats of axisymmetric to measure total flow, little flow meter measurement secondary flow pipeline in the gas flow. This application can eliminate the pneumatic interference power of admitting air and tube coupling interference power, can carry out spray tube air flow and thrust simultaneously and measure, is applicable to big bypass and separately exhausts spray tube and little bypass and mixes exhaust spray tube thrust measurement, and the range of application is wide.
Description
Technical Field
The application belongs to the field of jet pipes of aircraft engines, and particularly relates to a double-duct jet pipe thrust measurement platform with a thrust interference elimination structure.
Background
At present aeroengine exhaust apparatus for civil aviation is mostly big bypass ratio and divides the exhaust spray pipe, and for military use aeroengine exhaust apparatus is mostly little bypass ratio and mixes the exhaust spray pipe. In order to evaluate the thrust characteristics of the whole engine, the thrust of the spray pipe and the flow of gas flowing through the inner culvert and the outer culvert need to be accurately measured. In order to accurately measure the thrust of the spray pipe, the spray pipe and a main pipeline need to be separated and not contacted, and how to measure the thrust of the large-size double-duct spray pipe and simultaneously complete the measurement of the gas flow of the inner and outer ducts is a technical problem.
The existing nozzle force-measuring test bed mainly has three types: 1) a sealing structure is not adopted, such as a flexible expansion joint connection mode; 2) the two flows of inlet air of the inner culvert and the outer culvert adopt sealing structures, but the thrust measurement and the flow measurement need to be respectively measured, and then approximate fitting is carried out; 3) the test piece does not need to be aerated and can generate gas by itself, such as rockets, missiles and the like. However, the prior art has the following disadvantages: in the first form, the flexible structure and the semi-sealing structure have force measurement interference which is difficult to quantitatively calculate and cannot be eliminated, and the force measurement precision is influenced; in the second form, in order to reduce interference, the states of the force measuring system in the static calibration and dynamic test processes need to be as close as possible, so that the adjustment workload is increased invisibly, the test cost is increased, the efficiency is reduced, and the fitted data is not a true value; in the third form, the nozzle of the engine needs a two-flow air inlet structure, and the structure is complex.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The utility model aims at providing a two duct spray tube thrust measurement platform with thrust interference elimination structure to solve at least one problem that prior art exists.
The technical scheme of the application is as follows:
a dual ducted nozzle thrust measurement platform with thrust disturbance cancellation structure, comprising:
the device comprises a pressure stabilizing cabin, wherein a plurality of throat critical flow nozzles are arranged on a wall plate of the pressure stabilizing cabin;
the interference elimination structure comprises an inner cylinder and an outer cylinder which are sleeved, annular labyrinth seal structures are arranged at two axial ends of the inner cylinder, the interference elimination structure is sleeved on the ballast stabilizing chamber through the annular labyrinth seal structures and is not in contact with the ballast stabilizing chamber, a first annular airflow channel is arranged between the outer cylinder and the inner cylinder, a second annular airflow channel is arranged between the inner cylinder and the ballast stabilizing chamber, a through hole for communicating the first annular airflow channel with the second annular airflow channel is formed in the inner cylinder, and the second annular airflow channel is communicated with the throat critical flow nozzle;
the two air inlet pipelines are horizontally and symmetrically arranged on the outer cylinder of the interference elimination structural part;
the double-duct spray pipe comprises a main flow spray pipe and a secondary flow spray pipe, and the main flow spray pipe is connected with the pressure stabilizing cabin;
one end of the secondary flow pipeline is arranged on the wall plate of the pressure stabilizing cabin and is positioned at the downstream of the interference elimination structural part, and the other end of the secondary flow pipeline is connected with the secondary flow spray pipe;
and one end of the thrust measuring balance is fixedly arranged on the ground of the foundation, and the other end of the thrust measuring balance is fixedly connected with the pressure stabilizing cabin.
Optionally, the throat critical flow nozzles on the wall plate of the ballast are uniformly arranged in 6 in the circumferential direction and in 3 rows in the axial direction.
Optionally, 16 through holes are uniformly arranged on the inner barrel in the circumferential direction, and 7 rows are arranged in the axial direction.
Optionally, the ratio of the length to the diameter of the through hole on the inner cylinder is greater than 10.
Optionally, flow meters are disposed in both the throat critical flow nozzle and the secondary flow pipeline.
Optionally, the dual-duct nozzle is a large-duct-ratio separated exhaust nozzle, a secondary flow nozzle of the large-duct-ratio separated exhaust nozzle is sleeved on the inner side of the ballast stabilizing chamber, one end of the secondary flow pipeline is arranged on a wall plate of the ballast stabilizing chamber, and the other end of the secondary flow pipeline penetrates through the wall plate of the ballast stabilizing chamber and is connected with the secondary flow nozzle.
Optionally, an expansion section is arranged at one end of the secondary flow pipeline connected with the secondary flow spray pipe.
Optionally, the double-duct nozzle is a mixed exhaust nozzle with a small duct ratio, a secondary flow nozzle of the mixed exhaust nozzle with the small duct ratio is sleeved outside the ballast stabilizing chamber, one end of the secondary flow pipeline is arranged on a wall plate of the ballast stabilizing chamber, and the other end of the secondary flow pipeline is connected with the secondary flow nozzle.
Optionally, the system further comprises a main flow rectifying grating and a secondary flow rectifying grating, wherein the main flow rectifying grating is arranged at the connection position of the main flow nozzle and the pressure stabilizing cabin, and the secondary flow rectifying grating is arranged at the connection position of the secondary flow nozzle and the secondary flow pipeline.
Optionally, the primary flow rectification grid and the secondary flow rectification grid are of a honeycomb wire mesh structure.
The invention has at least the following beneficial technical effects:
the utility model provides a two duct spray tube thrust measurement platform with thrust interference elimination structure can be used for measuring the thrust measurement of big duct ratio division exhaust spray tube and little duct ratio mixed exhaust spray tube, can reduce the interference of admitting air to thrust measurement by a wide margin.
Drawings
FIG. 1 is a front view of a high bypass ratio split exhaust nozzle thrust measurement platform with a thrust disturbance rejection structure according to an embodiment of the present application;
FIG. 2 is a cross-sectional view of a disturbance elimination structure of a high bypass ratio split exhaust nozzle thrust measurement platform having a thrust disturbance elimination structure according to one embodiment of the present application;
FIG. 3 is a cross-sectional view of a high bypass ratio split exhaust nozzle thrust measurement platform having a thrust disturbance rejection feature according to an embodiment of the present application;
FIG. 4 is a top view of a high bypass ratio split exhaust nozzle thrust measurement platform having a thrust disturbance rejection structure according to an embodiment of the present application;
FIG. 5 is a cross-sectional view of a low bypass ratio hybrid exhaust nozzle thrust measurement platform having a thrust disturbance rejection feature in accordance with an embodiment of the present application.
Wherein:
1-an interference cancellation structure; 2-a thrust measuring balance; 3-ballast cabin; 4-secondary flow line; 5-a main flow rectification grid; 6-a secondary flow rectification grid; 7-large bypass ratio divided exhaust nozzle; 8-an air inlet pipeline; 9-annular labyrinth seal structure; 10-small bypass ratio mixed exhaust nozzle.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 5.
The application provides a two duct spray tube thrust measurement platform with thrust interference cancellation structure includes: the device comprises a ballast cabin 3, an interference elimination structural part 1, an air inlet pipeline 8, a double-duct spray pipe, a secondary flow pipeline 4 and a thrust measuring balance 2.
Specifically, as shown in fig. 1, a surge chamber 3 is provided inside, and a plurality of throat critical flow nozzles are provided on a wall plate of the surge chamber 3. In a preferred embodiment of the application, 6 throat critical flow nozzles are uniformly arranged along the circumferential direction, 3 rows are arranged along the axial direction, a flowmeter is arranged in each throat critical flow nozzle, the total airflow flowing through the axisymmetric multi-throat critical flow nozzle can be accurately measured, a smooth curve is adopted at the inlet of each nozzle to reduce the flow resistance, and the flow measurement can be simultaneously completed during thrust measurement.
The utility model provides a two duct spray tube thrust measurement platform with thrust interference elimination structure, interference elimination structure 1 is including inner tube and the urceolus that the cover was established, inner tube axial both ends are provided with annular labyrinth seal structure 9, interference elimination structure 1 overlaps through annular labyrinth seal structure 9 and establishes on steady voltage cabin 3, and with steady voltage cabin 3 contactless, first annular air current passageway has between urceolus and the inner tube, second annular air current passageway has between inner tube and the steady voltage cabin 3, and set up the through-hole of intercommunication first annular air current passageway and second annular air current passageway on the inner tube, second annular air current passageway and the critical flow nozzle intercommunication of throat. The air inlet pipelines 8 comprise two air inlet pipelines 8, and the two air inlet pipelines 8 are horizontally and symmetrically arranged on the outer cylinder of the interference elimination structural part 1 to realize air supply. In a preferred embodiment of the present application, 16 through holes are uniformly arranged in the circumferential direction on the inner cylinder of the interference elimination structural member 1, and 7 rows are arranged in the axial direction, in this embodiment, the inner cylinder has a predetermined thickness, the ratio of the length to the diameter of the through holes on the inner cylinder is greater than 10, after the airflow passes through the radial axisymmetric critical through hole, the airflow becomes uniform and radial, no axial airflow exists, no aerodynamic interference exists, and the annular labyrinth seal structures 9 installed at the two axial ends of the interference elimination structural member 1 are in non-contact with the surge tank 3, so that the interference of the pipeline contact force is avoided.
The utility model provides a two duct spray tube thrust measurement platform with thrust interference elimination structure, two duct spray tubes can be big duct ratio and separately exhausts spray tube 7, big duct ratio separately exhausts spray tube 7 and includes mainstream spray tube and secondary flow spray tube, its mainstream spray tube can pass through welded connection with surge tank 3, the inboard at surge tank 3 is established to the secondary flow spray tube cover, the one end setting of secondary flow pipeline 4 is on surge tank 3's wallboard, and be located the low reaches that the interference elimination structure spare 1 was eliminated, the wallboard that the other end passed surge tank 3 is connected with the secondary flow spray tube, secondary flow pipeline 4 is used for big duct ratio to separately exhausts 7 connotations air supplies of spray tube. It can be understood that the end of the secondary flow pipeline 4 connected with the secondary flow nozzle is provided with an expansion section, and the secondary flow pipeline 4 is provided with a small flow meter, so that the flow of the small flow secondary flow can be measured.
Further, two ducted spray pipes can also be little ducted and than mixing exhaust nozzle 10, little ducted is than mixing exhaust nozzle 10 and is including mainstream spray pipe and secondary flow spray pipe, its mainstream spray pipe and surge tank 3 can be through welded connection, the secondary flow spray pipe box is established in the outside of surge tank 3, the one end setting of secondary flow pipeline 4 is on the wallboard of surge tank 3, and be located the low reaches of interference elimination structure 1, the other end flows the spray pipe with the secondary and is connected, secondary flow pipeline 4 is used for little ducted and than mixing exhaust nozzle 10 outer culvert air feed. It is understood that the secondary flow pipe 4 is provided with a small flow meter, and the flow of the small flow secondary flow can be measured.
In a preferred embodiment of the application, the device further comprises a main flow rectifying grating 5 and a secondary flow rectifying grating 6, wherein the main flow rectifying grating 5 is arranged at the joint of a main flow spray pipe of the double-duct spray pipe and the surge tank 3, and the secondary flow rectifying grating 6 is arranged at the joint of a secondary flow spray pipe of the double-duct spray pipe and the secondary flow pipeline 4. Advantageously, the main flow rectification grids 5 and the secondary flow rectification grids 6 both adopt honeycomb wire mesh structures, so that the uniform air inlet flow field of the large bypass ratio separated exhaust nozzle 7 and the small bypass ratio mixed exhaust nozzle 10 is ensured.
The utility model provides a two duct spray tube thrust measurement platform with thrust interference elimination structure still includes thrust measurement balance 2, and thrust measurement balance 2's one end fixed mounting is subaerial on the basis, and the other end and the steady voltage cabin 3 fixed connection who has the many throat critical flow nozzles of axial symmetry for measure the vector thrust of two duct spray tubes.
The utility model provides a two duct spray tube thrust measurement platform with thrust interference elimination structure, through horizontal symmetry admit air, the critical slot hole of non-contact annular labyrinth seal structure and radial axisymmetric elimination air current thrust interference, adopt the thrust balance to measure two duct spray tube thrust, adopt the critical flow nozzle of many throats of axisymmetric to measure total flow, little flow meter measurement secondary flow pipeline in the gas flow. This application can eliminate the pneumatic interference power of admitting air and tube coupling interference power, can carry out spray tube air flow and thrust simultaneously and measure, is applicable to big bypass and separately exhausts spray tube and little bypass and mixes exhaust spray tube thrust measurement, and the range of application is wide.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A dual ducted nozzle thrust measurement platform with thrust disturbance cancellation structure, comprising:
the device comprises a pressure stabilizing cabin (3), wherein a plurality of throat critical flow nozzles are arranged on a wall plate of the pressure stabilizing cabin (3);
the structure comprises an interference elimination structure (1), wherein the interference elimination structure (1) comprises an inner cylinder and an outer cylinder which are sleeved, annular labyrinth seal structures (9) are arranged at two axial ends of the inner cylinder, the interference elimination structure (1) is sleeved on a ballast stabilizing chamber (3) through the annular labyrinth seal structures (9) and is not in contact with the ballast stabilizing chamber (3), a first annular airflow channel is arranged between the outer cylinder and the inner cylinder, a second annular airflow channel is arranged between the inner cylinder and the ballast stabilizing chamber (3), a through hole for communicating the first annular airflow channel with the second annular airflow channel is formed in the inner cylinder, and the second annular airflow channel is communicated with the critical flow nozzle of the throat channel;
the two air inlet pipelines (8) are horizontally and symmetrically arranged on the outer cylinder of the interference elimination structural part (1);
the double-duct spray pipe comprises a main flow spray pipe and a secondary flow spray pipe, and the main flow spray pipe is connected with the pressure stabilizing cabin (3);
one end of the secondary flow pipeline (4) is arranged on the wall plate of the pressure stabilizing cabin (3) and is positioned at the downstream of the interference elimination structural part (1), and the other end of the secondary flow pipeline (4) is connected with the secondary flow spray pipe;
the device comprises a thrust measuring balance (2), wherein one end of the thrust measuring balance (2) is fixedly arranged on the ground of a foundation, and the other end of the thrust measuring balance is fixedly connected with a pressure stabilizing cabin (3).
2. The dual ducted nozzle thrust measurement platform with thrust disturbance cancellation structure in accordance with claim 1, wherein throat critical flow nozzles on the wall of the ballast chamber (3) are uniformly arranged 6 in circumferential direction and 3 rows in axial direction.
3. The dual-ducted nozzle thrust measurement platform having a thrust interference cancellation structure in accordance with claim 2, wherein 16 through holes are uniformly arranged in a circumferential direction on the inner cylinder, and 7 rows are arranged in an axial direction.
4. The dual-ducted nozzle thrust measurement platform having a thrust disturbance cancellation structure in accordance with claim 3, wherein a ratio of a length to a diameter of the through-hole on the inner barrel is greater than 10.
5. The dual-ducted nozzle thrust measurement platform with thrust disturbance cancellation structure in accordance with claim 1, wherein flow meters are provided in both the throat critical flow nozzle and the secondary flow pipe (4).
6. The dual-duct nozzle thrust measurement platform with the thrust interference elimination structure according to claim 1, wherein the dual-duct nozzle is a large-duct-ratio split exhaust nozzle (7), a secondary flow nozzle sleeve of the large-duct-ratio split exhaust nozzle (7) is sleeved on the inner side of the pressure stabilization chamber (3), one end of the secondary flow pipeline (4) is arranged on a wall plate of the pressure stabilization chamber (3), and the other end of the secondary flow pipeline penetrates through the wall plate of the pressure stabilization chamber (3) to be connected with the secondary flow nozzle.
7. The dual-duct nozzle thrust measurement platform with the thrust interference elimination structure according to claim 6, wherein an end of the secondary flow pipeline (4) connected with the secondary flow nozzle is provided with an expansion section.
8. The dual-duct nozzle thrust measurement platform with the thrust interference elimination structure according to claim 1, wherein the dual-duct nozzle is a small-duct-ratio mixed exhaust nozzle (10), a secondary flow nozzle of the small-duct-ratio mixed exhaust nozzle (10) is sleeved outside the ballast stabilizing chamber (3), one end of the secondary flow pipeline (4) is arranged on a wall plate of the ballast stabilizing chamber (3), and the other end of the secondary flow pipeline is connected with the secondary flow nozzle.
9. The dual-duct nozzle thrust measurement platform with the thrust interference elimination structure according to claim 6 or 8, characterized by further comprising a main flow rectification grid (5) and a secondary flow rectification grid (6), wherein the main flow rectification grid (5) is arranged at the connection of the main flow nozzle and the ballast tank (3), and the secondary flow rectification grid (6) is arranged at the connection of the secondary flow nozzle and the secondary flow pipeline (4).
10. The dual ducted nozzle thrust measurement platform with thrust disturbance cancellation structure in accordance with claim 9, wherein the primary flow straightener grid (5) and the secondary flow straightener grid (6) are honeycomb wire mesh structures.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110163189.6A CN112945305B (en) | 2021-02-05 | 2021-02-05 | Double-duct spray pipe thrust measuring platform with thrust interference elimination structure |
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| CN202110163189.6A CN112945305B (en) | 2021-02-05 | 2021-02-05 | Double-duct spray pipe thrust measuring platform with thrust interference elimination structure |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114018583A (en) * | 2021-10-28 | 2022-02-08 | 中国航发沈阳发动机研究所 | Ducted spray pipe thrust and flow synchronous measurement air inlet structure capable of uniformly feeding air |
| CN114739458A (en) * | 2022-04-18 | 2022-07-12 | 中国航发沈阳发动机研究所 | Double-channel high-temperature measurement structure for simulating afterburner inlet flow field |
| CN116183234A (en) * | 2023-04-27 | 2023-05-30 | 中国航发四川燃气涡轮研究院 | Double-deck steady voltage room that admits air of high altitude platform |
| CN117848729A (en) * | 2024-03-08 | 2024-04-09 | 中国航空工业集团公司沈阳空气动力研究所 | Double culvert air suction type negative pressure test device |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040079072A1 (en) * | 2002-10-28 | 2004-04-29 | James Shumate | Method and apparatus for thrust augmentation for rocket nozzles |
| CN101372926A (en) * | 2007-08-23 | 2009-02-25 | 斯奈克玛 | Dual-flow turbomachine with jet noise reduction |
| CN101968013A (en) * | 2010-11-03 | 2011-02-09 | 南京航空航天大学 | Single-tube rotary valve type double-bypass pulse detonation engine |
| WO2017152565A1 (en) * | 2016-03-07 | 2017-09-14 | 合肥通用机械研究院 | Centrifugal compressor stability enhancement device |
| CN110454574A (en) * | 2019-07-31 | 2019-11-15 | 中国航发沈阳发动机研究所 | A kind of inside and outside culvert coaxial air intake sealing device for thrust device measurement |
| CN110864903A (en) * | 2019-11-15 | 2020-03-06 | 西北工业大学 | Double-flow-path spray pipe experiment pipeline with circumferential air inlet function |
| CN210950322U (en) * | 2019-07-31 | 2020-07-07 | 中国航发沈阳发动机研究所 | Double-layer pipeline switching section |
-
2021
- 2021-02-05 CN CN202110163189.6A patent/CN112945305B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040079072A1 (en) * | 2002-10-28 | 2004-04-29 | James Shumate | Method and apparatus for thrust augmentation for rocket nozzles |
| CN101372926A (en) * | 2007-08-23 | 2009-02-25 | 斯奈克玛 | Dual-flow turbomachine with jet noise reduction |
| CN101968013A (en) * | 2010-11-03 | 2011-02-09 | 南京航空航天大学 | Single-tube rotary valve type double-bypass pulse detonation engine |
| WO2017152565A1 (en) * | 2016-03-07 | 2017-09-14 | 合肥通用机械研究院 | Centrifugal compressor stability enhancement device |
| CN110454574A (en) * | 2019-07-31 | 2019-11-15 | 中国航发沈阳发动机研究所 | A kind of inside and outside culvert coaxial air intake sealing device for thrust device measurement |
| CN210950322U (en) * | 2019-07-31 | 2020-07-07 | 中国航发沈阳发动机研究所 | Double-layer pipeline switching section |
| CN110864903A (en) * | 2019-11-15 | 2020-03-06 | 西北工业大学 | Double-flow-path spray pipe experiment pipeline with circumferential air inlet function |
Non-Patent Citations (2)
| Title |
|---|
| 何敬玉等: "双喉道推力矢量喷管的气动性能数值模拟", 《南京航空航天大学学报》, 15 September 2017 (2017-09-15), pages 16 - 23 * |
| 解亮等: "反推力装置模型试验台的研制及验证", 《航空发动机》, no. 03, 15 June 2020 (2020-06-15), pages 77 - 83 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114018583A (en) * | 2021-10-28 | 2022-02-08 | 中国航发沈阳发动机研究所 | Ducted spray pipe thrust and flow synchronous measurement air inlet structure capable of uniformly feeding air |
| CN114018583B (en) * | 2021-10-28 | 2024-03-19 | 中国航发沈阳发动机研究所 | Duct spray tube thrust and flow synchronous measurement air inlet structure of evenly admitting air |
| CN114739458A (en) * | 2022-04-18 | 2022-07-12 | 中国航发沈阳发动机研究所 | Double-channel high-temperature measurement structure for simulating afterburner inlet flow field |
| CN114739458B (en) * | 2022-04-18 | 2023-11-03 | 中国航发沈阳发动机研究所 | Dual-channel high-temperature measurement structure for simulating afterburner inlet flow field |
| CN116183234A (en) * | 2023-04-27 | 2023-05-30 | 中国航发四川燃气涡轮研究院 | Double-deck steady voltage room that admits air of high altitude platform |
| CN116183234B (en) * | 2023-04-27 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Double-deck steady voltage room that admits air of high altitude platform |
| CN117848729A (en) * | 2024-03-08 | 2024-04-09 | 中国航空工业集团公司沈阳空气动力研究所 | Double culvert air suction type negative pressure test device |
| CN117848729B (en) * | 2024-03-08 | 2024-05-03 | 中国航空工业集团公司沈阳空气动力研究所 | Double culvert air suction type negative pressure test device |
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| CN112945305B (en) | 2022-06-03 |
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