CN113958426B - Thrust chamber scale test device - Google Patents
Thrust chamber scale test device Download PDFInfo
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- CN113958426B CN113958426B CN202111257616.3A CN202111257616A CN113958426B CN 113958426 B CN113958426 B CN 113958426B CN 202111257616 A CN202111257616 A CN 202111257616A CN 113958426 B CN113958426 B CN 113958426B
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- igniter
- body part
- adapter
- mounting channel
- cooling liquid
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Measuring Fluid Pressure (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention discloses a thrust chamber reduced scale test device, which solves the problems that an igniter fails to ignite or the end part is burnt and the connection between the body part of the reduced scale test device and the igniter or a sensor fails in the prior art, and comprises a body part, the igniter and an igniter adapter; the body part is of a cylindrical structure, and a plurality of axial cooling channels are uniformly arranged in the cylinder wall of the body part along the circumferential direction and are used for accommodating a coolant; two annular cooling liquid collecting cavities are arranged at two ends in the cylinder wall and communicate the plurality of axial cooling channels; a cooling liquid inlet and a cooling liquid outlet are correspondingly arranged at the positions of the two cooling liquid collecting cavities respectively; the inner chamber of body portion is the burning chamber, is equipped with first installation passageway on the lateral wall of body portion along radial, first installation passageway and burning chamber intercommunication, and some firearm adapter socket and first installation passageway threaded connection, some firearm are installed at some firearm adapter socket.
Description
Technical Field
The invention relates to the technical field of propulsion of liquid rocket engines, in particular to a scale test device for a thrust chamber.
Background
The large-thrust liquid rocket engine has the advantages of large flow of the thrust chamber, high pressure, large heat flux density and complex combustion characteristics, the performance is evaluated by independently carrying out a thermal test on the thrust chamber, the risk is high, the period is long, the cost is huge, and a reduced scale test device is generally adopted to replace the evaluation.
The commonly used scale test device for the thrust chamber comprises a head part, a body part and a heat sink throat, the test device with the structure usually utilizes a copper material to conduct heat rapidly, and the hot test time is very short (about 1 s); during hot test, an igniter and a sensor are required to be arranged on the body part, the igniter and the sensor are generally made of steel materials, the body part is made of copper materials, and the igniter and the sensor are connected through threads; frequent disassembly of the igniter and the sensor for inspection in the test process easily causes deformation and failure of the copper material threads, thereby leading to body scrapping.
In recent years, for the purpose of realizing long-range thermal test, the body part and the throat of the scale test device adopt an interlayer cooling structure, and a cavity between interlayers is supplied with coolant; the body part adopting the structure needs to penetrate through the cooling interlayer when the igniter and the sensor are installed, and in order to prevent cooling liquid from leaking into the combustion chamber from the installation hole, a sleeve needs to be additionally arranged and two ends of the sleeve are respectively welded with the inner wall and the outer wall of the body part. The igniter penetrates through the ignition sleeve and extends into the cavity for ignition, and the structure has the following two main problems: firstly, the space is narrow when the bottom end of the ignition sleeve is welded with the inner wall, and the welding difficulty is high; secondly, the welding seam is easy to crack after long-time and multiple hot tests. Meanwhile, in the existing thrust chamber scale test device, one end of the igniter extending into the fuel chamber is basically flush with the inner wall of the chamber, so that the end part of the igniter is prevented from being burnt after ignition; however, in practice there is still ablation or the end of the igniter that extends into the chamber is not long enough to cause misfire.
Disclosure of Invention
The invention provides a reduced scale test device of a thrust chamber, aiming at solving the problems that an igniter fails to ignite or burns at the end part and the connection between the body part of the reduced scale test device and the igniter or a sensor fails in the prior art.
A thrust chamber scale test device is characterized in that: comprises a body part, an igniter and an igniter adapter;
the body part is of a cylindrical structure, and a plurality of axial cooling channels are uniformly formed in the wall of the body part along the circumferential direction and are used for accommodating a coolant; two annular cooling liquid collecting cavities are arranged at two ends in the cylinder wall and communicate the plurality of axial cooling channels; a cooling liquid inlet and a cooling liquid outlet are correspondingly arranged at the positions of the two cooling liquid collecting cavities respectively;
the inner chamber of body portion is the combustion chamber, radially be equipped with first installation passageway on the lateral wall of body portion, first installation passageway with the combustion chamber intercommunication, some firearm adapter socket with first installation passageway threaded connection, some firearm are installed on some firearm adapter socket, the ignition end of some firearm stretches into in the combustion chamber.
Furthermore, the device also comprises a plurality of sensors and a plurality of sensor adapter seats which correspond to the sensors one by one;
the lateral wall of the body part is provided with a plurality of second mounting channels which are in one-to-one correspondence with the sensor adapter along the radial direction, each second mounting channel is communicated with the combustion chamber, each sensor adapter is in threaded connection with the corresponding second mounting channel, and the detection end of the sensor mounted on the sensor adapter extends into the combustion chamber and is used for measuring the pressure in the combustion chamber.
Further, the body part is integrally manufactured by adopting a 3D printing technology.
Further, the first mounting channel is a step through hole;
the igniter adapter comprises a first connecting part and a first flange part which are fixedly connected, and the first connecting part is connected with the large-diameter hole wall of the first mounting channel through threads; an annular gasket is disposed between the first flange portion and the body portion.
Further, the second mounting channel is a step through hole;
the sensor adapter comprises a second connecting part and a second flange part which are fixedly connected, and the second connecting part is in threaded connection with the large-diameter hole wall of the second mounting channel; an annular gasket is disposed between the second flange portion and the body portion.
Compared with the prior art, the invention has the following beneficial effects:
the body part integrally manufactured by adopting a 3D printing technology is provided with a plurality of axial cooling channels on the wall of a combustion chamber, and the inner wall of the combustion chamber is cooled and protected by cooling media in the cooling channels; the ignition adapter is installed in a first installation channel of the first adapter cylinder through threads, and the length of an igniter installed on the igniter adapter extending into the combustion cavity can be adjusted by adjusting the screwing length of the igniter adapter and the first installation channel; therefore, in the hot test process, the igniter is extended into the combustion chamber for a sufficient length to ensure smooth ignition, the end part of the igniter is prevented from being ablated, and the service life of the igniter is prolonged;
according to the invention, the igniter adapter and the sensor adapter are adopted, so that the igniter and the sensor are prevented from being directly in threaded connection with the body, the failure of threads of the body due to frequent disassembly and inspection in the hot test process of the igniter and the sensor can be effectively prevented, and the reliable connection of the igniter, the sensor and the body is ensured.
Drawings
Fig. 1 is a schematic structural diagram of a body of a thrust chamber scale test device provided in an embodiment of the present invention;
FIG. 2 is a schematic cross-sectional structure view of a body of a reduced-scale testing device of a thrust chamber according to an embodiment of the present invention;
FIG. 3 is a schematic structural view of a body portion (omitting an igniter adapter, an igniter, and a sensor adapter) according to an embodiment of the invention;
FIG. 4 is a schematic diagram of an igniter adapter according to an embodiment of the invention;
FIG. 5 is a schematic structural diagram of a sensor adapter according to an embodiment of the present invention;
in the figure: 1-igniter, 2-body, 21-combustion chamber, 24-first mounting channel, 26-second mounting channel, 27-cooling channel, 271-coolant inlet, 272-coolant outlet, 3-igniter adapter, 31-first center hole, 32-first connection, 33-first flange, 5-sensor adapter, 51-second center hole, 52-second connection, 53-second flange, 6-cooling header chamber.
Detailed Description
The following detailed description of the present invention is provided in conjunction with the accompanying drawings, but it should be understood that the scope of the present invention is not limited to the specific embodiments.
As shown in fig. 1, the thrust chamber scale test device comprises a body 2, an igniter 1, an igniter adapter 3, two sensors and two sensor adapters 5;
as shown in fig. 2, the body 2 is integrally manufactured by 3D printing technology, the body 2 is a cylindrical structure, and a plurality of axial cooling channels 27 are uniformly formed in the wall of the cylindrical structure along the circumferential direction for accommodating a coolant; two annular cooling liquid collecting cavities 6 are arranged at two ends in the cylinder wall, and the two cooling liquid collecting cavities 6 are communicated with a plurality of axial cooling channels 27; a cooling liquid inlet 271 and a cooling liquid outlet 272 are correspondingly arranged at the positions of the two cooling liquid collecting cavities 6 respectively;
as shown in fig. 3, the inner cavity of the body 2 is a combustion chamber 21, a first mounting channel 24 is radially arranged on the side wall of the body 2, the first mounting channel 24 is a step through hole, and the first mounting channel 24 is communicated with the combustion chamber 21 and is not communicated with a cooling channel 27; as shown in fig. 4, the igniter adaptor 3 includes a first connecting portion 32 and a first flange portion 33 fixedly connected, and the first connecting portion 32 is screwed with the large-diameter hole wall of the first mounting passage 24; an annular sealing gasket is arranged between the first flange part 33 and the body part 2, the igniter adapter 3 is provided with a first central through hole 31, the igniter 1 is arranged on the igniter adapter 3 through the first central through hole 31, and the ignition end of the igniter 1 extends into the combustion cavity 21.
Two second mounting channels 26 are radially arranged on the side wall of the body part 2, the second mounting channels 26 are step through holes, and each second mounting channel 26 is communicated with the combustion cavity 21 and is not communicated with the cooling channel 27; as shown in fig. 5, each sensor adapter 5 includes a second connecting portion 52 and a second flange portion 53 fixedly connected to each other, the second connecting portion 52 is connected to the large-diameter hole wall of the second mounting channel 24 through a screw thread, an annular sealing gasket is disposed between the second flange portion 53 and the body portion 2, the sensor adapter 5 is provided with a second central through hole 51, the sensor can be mounted on the sensor adapter 5 through the second central pupil 51, and the detection end of the sensor adapter extends into the combustion chamber 21 for measuring the pressure in the combustion chamber 21.
When the thrust chamber scale test device needs to ignite in a combustion cavity of a body part, the igniter adapter 3 is rotated, and the first connecting part 52 is screwed inwards relative to the first mounting channel 24, so that the igniter 1 can be ignited successfully; after ignition, the first connecting part 52 is screwed outwards relative to the first mounting channel 24, so that the ignition end of the igniter 1 is prevented from being ablated, and the detachment and replacement of the igniter are reduced; the sensing end of the sensor 1 extends into the combustion chamber 21 to measure the pressure in the chamber.
The above disclosure is only for the specific embodiments of the present invention, but the embodiments of the present invention are not limited thereto, and any variations that can be considered by those skilled in the art should fall within the scope of the present invention.
Claims (5)
1. The utility model provides a thrust room reduced scale testing device which characterized in that: comprises a body part (2), an igniter (1) and an igniter adapter (3);
the body part (2) is of a cylindrical structure, and a plurality of axial cooling channels (27) are uniformly formed in the wall of the body part along the circumferential direction and are used for containing a coolant; two annular cooling liquid collecting cavities (6) are arranged at two ends in the cylinder wall, and the two cooling liquid collecting cavities (6) are used for communicating the plurality of axial cooling channels (27); a cooling liquid inlet (271) and a cooling liquid outlet (272) are correspondingly arranged at the positions of the two cooling liquid collecting cavities (6) respectively;
the inner cavity of the body part (2) is a combustion cavity (21), a first mounting channel (24) is arranged on the side wall of the body part (2) along the radial direction, the first mounting channel (24) is communicated with the combustion cavity (21), the igniter adapter (3) is in threaded connection with the first mounting channel (24), and the igniter (1) is mounted on the igniter adapter (3);
the body part (2) comprises a flange arranged on the lateral surface of the outer side of the combustion chamber (21), and a first mounting channel (24) is arranged on the side wall of the flange along the radial direction.
2. The thrust cell scale test apparatus of claim 1, wherein: the sensor adapter also comprises a plurality of sensors and a plurality of sensor adapters (5) which are in one-to-one correspondence with the sensors;
the lateral wall of the body part (2) is radially provided with a plurality of second mounting channels (26) which are in one-to-one correspondence with the sensor adapter (5), each second mounting channel (26) is communicated with the combustion cavity (21), each sensor adapter (5) is in threaded connection with the corresponding second mounting channel (26), and the sensor is mounted on the sensor adapter (5).
3. The thrust cell scale test apparatus of claim 2, wherein: the body part (2) is integrally manufactured by adopting a 3D printing technology.
4. A thrust cell scale test apparatus as defined in claim 3, wherein: the first mounting channel (24) is a step through hole;
the igniter adapter (3) comprises a first connecting part (32) and a first flange part (33) which are fixedly connected, and the first connecting part (32) is connected with the large-diameter hole wall of the first mounting channel (24) through threads; an annular sealing gasket is arranged between the first flange part (33) and the flange.
5. The thrust cell scale testing apparatus of claim 4, wherein: the second mounting channel (26) is a stepped through hole;
the sensor adapter (5) comprises a second connecting part (52) and a second flange part (53) which are fixedly connected, and the second connecting part (52) is in threaded connection with the large-diameter hole wall of the second mounting channel (26); an annular gasket is arranged between the second flange part (53) and the body part (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111257616.3A CN113958426B (en) | 2021-10-27 | 2021-10-27 | Thrust chamber scale test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111257616.3A CN113958426B (en) | 2021-10-27 | 2021-10-27 | Thrust chamber scale test device |
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| Publication Number | Publication Date |
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| CN113958426A CN113958426A (en) | 2022-01-21 |
| CN113958426B true CN113958426B (en) | 2023-03-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111257616.3A Active CN113958426B (en) | 2021-10-27 | 2021-10-27 | Thrust chamber scale test device |
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Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102022225B (en) * | 2010-12-30 | 2013-03-27 | 北京航空航天大学 | Test device for hydrogen-rich/oxygen-rich gas multinozzle gas-gas injector |
| CN201983931U (en) * | 2011-03-10 | 2011-09-21 | 北京航天动力研究所 | Reduced scale thrust chamber for high-pressure and large-heat-flux heat transfer test |
| CN103644044B (en) * | 2013-11-26 | 2015-10-28 | 北京航空航天大学 | Be applied to polychormism simulated engine and the ignition schemes thereof of the research of Vacuum Plume effect experiment |
| CN103743571B (en) * | 2013-12-16 | 2016-01-13 | 中国科学院力学研究所 | For the air heating apparatus of long-time supersonic combustion |
| CN104806381B (en) * | 2015-04-03 | 2017-01-04 | 北京航空航天大学 | Solid-liquid rocket lighter and head outlet method thereof |
| CN106050476B (en) * | 2016-07-11 | 2018-06-05 | 湖北三江航天江河化工科技有限公司 | A kind of liquid-propellant rocket engine igniter and its ignition method |
| CN108639391B (en) * | 2018-07-06 | 2021-12-07 | 湖北三江航天红林探控有限公司 | Gas generator for rapid actuation |
| CN110646211B (en) * | 2019-10-09 | 2024-07-26 | 中国人民解放军32181部队 | Rocket engine pressure testing device and method |
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