CN103308316A - Variable-length supersonic diffuser - Google Patents
Variable-length supersonic diffuser Download PDFInfo
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- CN103308316A CN103308316A CN2013101438697A CN201310143869A CN103308316A CN 103308316 A CN103308316 A CN 103308316A CN 2013101438697 A CN2013101438697 A CN 2013101438697A CN 201310143869 A CN201310143869 A CN 201310143869A CN 103308316 A CN103308316 A CN 103308316A
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- diffuser
- engine
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- variable
- injection tube
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Abstract
The invention discloses a variable-length supersonic diffuser which comprises a main diffuser, an auxiliary injection tube, a guiderail and a connecting component, wherein the main diffuser and an engine are matched to form engine injection to vacuumize a vacuum cabin, the auxiliary injection tube is arranged on the guiderail and used for changing the length of the diffuser and leads the gas of an engine into the main diffuser, the guiderail is mainly used for stipulating the motion direction and distance of the auxiliary injection tube, and the connecting component is used for fixedly installing the guiderail. The diffuser is simple to assemble, variable in length, and the vacuum degree of the vacuum cabin can be kept stable when the engine is ignited at different axial positions.
Description
Technical field
The present invention relates to a kind of variable-length supersonic diffuser, relate in particular to a kind of spacecraft and dynamically vacuumize technology with the altitude simulation test system, belong to vacuum and obtain technical field.
Background technology
The rail control engine need carry out the motor power vector on ground and demarcate altitude simulation test as satellite platform main transformer rail engine.When this test is carried out, need make engine in four different setting angles and two disalignments to the installation site, amount to and carry out the engine ignition test under eight states.The altitude simulation system of this test is made up of vacuum chamber, supersonic diffuser, induction apparatus etc., and wherein the injection assembling device is used for the acquisition of engine dynamic vacuum, guarantees the vacuum tightness that engine ignition is preceding; Vacuum chamber is used for the installation of engine and measurement mechanism; The effect of supersonic diffuser is to cooperate with engine, when engine ignition, forms engine self injection, thereby further improves vacuum tightness in the vacuum chamber, obtains the vacuum environment under the engine ignition state.During engine ignition, because vacuum tightness need keep constant in the vacuum chamber, the distance between supersonic diffuser entrance and the engine jet pipe outlet just needs to keep constant.And this test engine need particularly need be lighted a fire at two disalignment line positions at eight different conditions down-firings, for vacuum tightness in the vacuum chamber in the assurance engine ignition process is constant, needs the supersonic diffuser of a kind of variable-length of development.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome the deficiencies in the prior art, a kind of variable-length supersonic diffuser is provided, this diffuser is formed simple, variable-length, make engine when axial diverse location igniting in the vacuum chamber vacuum tightness keep stable.
Technical solution of the present invention is: a kind of variable-length supersonic diffuser, comprise main diffuser, auxiliary injection tube, guide rail and link, main diffuser cooperates formation engine self injection that vacuum chamber is vacuumized with engine, auxiliary injection tube is installed on and is used on the guide rail changing diffuser length and engine gas being imported main diffuser, it is the auxiliary injection tube travel direction of regulation and distance that guide rail mainly acts on, and the link effect is the fixed installation of guide rail.
The present invention's advantage compared with prior art is: this diffuser is formed simple, variable-length within the specific limits, make engine when axially diverse location is lighted a fire, the distance between engine and the diffuser keeps constant, and vacuum tightness keeps stablizing in the vacuum chamber thereby make.
Description of drawings
Accompanying drawing is variable-length supersonic diffuser structural representation.
Embodiment
Main diffuser is secondary venturi type diffuser, designs processing according to engine parameter.Diffuser is the flow-guiding channel of combustion gas, utilize simultaneously engine gas from ejector action, vacuum chamber is vacuumized.Diffuser adopts stainless steel material, and interlayer water-cooling structure, its entrance are straight-line segment, and internal diameter is 346mm.After engine ignition was stable, diffuser startup work can guarantee that vacuum tightness is about 80Pa in the vacuum chamber.
Auxiliary injection tube is single-wall structure, and internal diameter is 340mm, length 355mm, and wall thickness 1mm adopts stainless steel material to make, and main effect is that engine gas is imported diffuser.During engine operation, the engine export temperature is lower, and speed is very fast, and high velocity air has certain cooling effect to cylindrical shell, guarantees that auxiliary injection tube is working properly.At auxiliary injection tube entrance coupling arrangement is arranged, link to each other with motor on the thrust frame, guarantee that thrust frame can move with engine.
The guide rail effect is the parts of the auxiliary injection tube direction of motion of regulation, has three groups, and every group is adopted roller structure.
Link is that guide rail is installed on parts on the main diffuser, mainly contains a single wall stainless steel cylinder and constitutes cylinder internal diameter 500mm, length 100mm, thickness 3mm.Three double-screw bolts of uniform welding on cylindrical shell are used for being connected with the diffuser flange, and 3 uniform positions are opened two holes respectively on cylindrical shell simultaneously, are used for mounting guide rail.
The present invention not detailed description is technology as well known to those skilled in the art.
Claims (1)
1. variable-length supersonic diffuser, comprise main diffuser, auxiliary injection tube, guide rail and link, main diffuser cooperates formation engine self injection that vacuum chamber is vacuumized with engine, auxiliary injection tube is installed on and is used on the guide rail changing diffuser length and engine gas being imported main diffuser, it is the auxiliary injection tube travel direction of regulation and distance that guide rail mainly acts on, and the link effect is the fixed installation of guide rail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101438697A CN103308316A (en) | 2013-04-24 | 2013-04-24 | Variable-length supersonic diffuser |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013101438697A CN103308316A (en) | 2013-04-24 | 2013-04-24 | Variable-length supersonic diffuser |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103308316A true CN103308316A (en) | 2013-09-18 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013101438697A Pending CN103308316A (en) | 2013-04-24 | 2013-04-24 | Variable-length supersonic diffuser |
Country Status (1)
| Country | Link |
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| CN (1) | CN103308316A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114166511A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | High-altitude cabin and exhaust diffuser connecting and positioning structure and high-altitude simulation test equipment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5211057A (en) * | 1991-08-08 | 1993-05-18 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Nozzle diffuser for use with an open test section of a wind tunnel |
| RU2028593C1 (en) * | 1990-01-22 | 1995-02-09 | Центральный аэрогидродинамический институт им.проф.Н.Е.Жуковского | Method of actuating the supersonic diffuser and a supersonic diffuser |
| CN201983918U (en) * | 2011-03-22 | 2011-09-21 | 中国人民解放军国防科学技术大学 | Retractable diffuser for supersonic wind tunnel |
| CN201983919U (en) * | 2011-03-23 | 2011-09-21 | 中国人民解放军国防科学技术大学 | Side-cutting diffuser used for ultrasonic speed wind tunnel |
| CN203275094U (en) * | 2013-04-24 | 2013-11-06 | 北京航天试验技术研究所 | Variable-length ultrasonic diffuser |
-
2013
- 2013-04-24 CN CN2013101438697A patent/CN103308316A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2028593C1 (en) * | 1990-01-22 | 1995-02-09 | Центральный аэрогидродинамический институт им.проф.Н.Е.Жуковского | Method of actuating the supersonic diffuser and a supersonic diffuser |
| US5211057A (en) * | 1991-08-08 | 1993-05-18 | The United States Of America As Represented By The United States National Aeronautics And Space Administration | Nozzle diffuser for use with an open test section of a wind tunnel |
| CN201983918U (en) * | 2011-03-22 | 2011-09-21 | 中国人民解放军国防科学技术大学 | Retractable diffuser for supersonic wind tunnel |
| CN201983919U (en) * | 2011-03-23 | 2011-09-21 | 中国人民解放军国防科学技术大学 | Side-cutting diffuser used for ultrasonic speed wind tunnel |
| CN203275094U (en) * | 2013-04-24 | 2013-11-06 | 北京航天试验技术研究所 | Variable-length ultrasonic diffuser |
Non-Patent Citations (1)
| Title |
|---|
| 张奎好: "火箭发动机－超音速扩压器－蒸汽引射泵组合式高空模拟试验系统的性能研究", 《推进技术》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114166511A (en) * | 2021-10-20 | 2022-03-11 | 中国航发四川燃气涡轮研究院 | High-altitude cabin and exhaust diffuser connecting and positioning structure and high-altitude simulation test equipment |
| CN114166511B (en) * | 2021-10-20 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | High altitude cabin and exhaust diffuser connection positioning structure and high altitude simulation test equipment |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130918 |