CN111120107A - Engine gas collecting and distributing device - Google Patents
Engine gas collecting and distributing device Download PDFInfo
- Publication number
- CN111120107A CN111120107A CN201911285954.0A CN201911285954A CN111120107A CN 111120107 A CN111120107 A CN 111120107A CN 201911285954 A CN201911285954 A CN 201911285954A CN 111120107 A CN111120107 A CN 111120107A
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- Prior art keywords
- wall
- gas collecting
- collecting pipe
- gas
- engine
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Exhaust Silencers (AREA)
Abstract
The invention relates to the technical field of liquid engines, and discloses an engine gas collecting and shunting device which comprises a shell, a gas inlet collecting pipe, a gas outlet collecting pipe, a partition plate, a support plate and a blocking cover, wherein the shell is provided with a gas inlet pipe and a gas outlet pipe; the shell comprises an inner wall and an outer wall, the inner wall and the outer wall are coaxially arranged, and a space between the inner wall and the outer wall forms an airflow channel; support plates are circumferentially arranged on the outer surface of the inner wall at equal intervals; the inner surface of the inner wall is radially provided with a partition plate which divides the inner wall into a closed front cavity and a closed rear cavity; the outer surface of the outer wall is provided with an air inlet gas collecting pipe and an air exhaust gas collecting pipe, the air inlet gas collecting pipe is communicated with the rear cavity, the air exhaust gas collecting pipe is communicated with the front cavity, the outer end of the air inlet gas collecting pipe is provided with an air inlet interface, the outer end of the air exhaust gas collecting pipe is provided with an air exhaust interface, two different media are separated, fuel introduced into the combustion chamber is controlled, the phenomenon that the combustion chamber is not ignited due to the fact that the fuel introduced into the combustion chamber is too much to cause a rich combustion environment of the combustion chamber is avoided, the media for driving the turbine are collected and then discharged or redistributed, and meanwhile.
Description
Technical Field
The invention belongs to the technical field of precooling combined engines, and mainly relates to an engine gas collecting and distributing device.
Background
The precooling combined engine is an important development direction of a power system of a reusable space carrier, and is one of research hotspots in the field of domestic and international spaceflight. In the current mature aeroengine and ATR (air turbine rocket) engine, the gas turbine and the combustion chamber adopt the same medium, and have close coupling relation, and the medium for driving the turbine directly enters the combustion chamber as fuel after expanding and doing work in the turbine. Unlike the type of engine described above, the pre-cooled combined engine system decouples the turbine from the combustor, and the media type differs from the turbine, and the media flow path driving the turbine must be completely independent of the combustor fuel supply flow path.
According to the characteristics of the precooling combined engine and the structural characteristics of the precooling combined engine, a gas collecting and distributing device is urgently needed to be designed, a medium for driving a turbine and a combustion chamber is isolated, and the medium is redistributed, so that the medium in the engine can be used more reasonably.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the utility model provides an engine gas collects diverging device, can avoid because the too much fuel that leads to the combustion chamber causes the combustion chamber rich combustion environment to the phenomenon that can't light up, discharges or redistributes after collecting the medium that drives the turbine, can provide the fuel supply simultaneously according to the combustion chamber demand.
The technical solution of the invention is as follows: an engine gas collecting and distributing device comprises a shell, a gas inlet collecting pipe, a gas outlet collecting pipe, a partition plate, a support plate and a blocking cover; the shell comprises an inner wall and an outer wall, the inner wall and the outer wall are coaxially arranged, and a space between the inner wall and the outer wall forms an airflow channel; support plates are circumferentially arranged on the outer surface of the inner wall at equal intervals; the inner surface of the inner wall is radially provided with a partition plate which divides the inner wall into a closed front cavity and a closed rear cavity; the outer surface of the outer wall is provided with an air inlet gas collecting pipe and an air outlet gas collecting pipe, the air inlet gas collecting pipe is communicated with the rear cavity, the air outlet gas collecting pipe is communicated with the front cavity, the outer end of the air inlet gas collecting pipe is provided with an air inlet interface, and the outer end of the air outlet gas collecting pipe is provided with an air outlet interface.
The invention collects the inflow gas of the turbine through the front cavity formed by the clapboard and the inner wall, leads the inflow gas out of the exhaust collecting pipe outside the outer wall through the exhaust channel in the support plate, and finally exhausts or distributes the inflow gas to the combustion chamber through the exhaust interface according to the requirement; the gas supply is realized through the rear cavity formed by the partition plate and the inner wall, the gas enters the gas inlet collecting pipe from the gas inlet interface, the gas enters the rear cavity formed by the partition plate and the inner wall through the gas inlet channel in the support plate after being shunted, and is finally supplied to the combustion chamber.
Furthermore, the middle part of the clapboard is provided with a detachable blanking cover, incoming flow gas collected by the front cavity can be selected to be discharged out of the exhaust gas collecting pipe or to be discharged into the combustion chamber by replacing the blanking cover, and fuel can be better distributed according to actual needs.
Furthermore, the blocking cover is in threaded connection with the partition plate, so that the blocking cover can be replaced conveniently.
Further, a through hole is formed in the middle of the blocking cover, and incoming flow gas collected by the front cavity can be discharged to the combustion chamber through the through hole.
Furthermore, the support plate is in a streamline shape, so that the energy loss of the medium is reduced, the gas discharge channel and the gas supply channel are arranged in the support plate and are respectively communicated with the front cavity and the rear cavity, the discharge and supply of the connotative gas are realized, the structural complexity is effectively simplified, and the influence on the flow resistance of an air flow path is reduced to the minimum limit.
Furthermore, the front end and the rear end of the outer wall are respectively provided with a connecting flange a and a connecting flange b, the connecting flange a is connected with a turbine of an engine, and the connecting flange b is connected with a combustion chamber of the engine, so that a communicated airflow channel can be formed among the turbine, the flow dividing device and the combustion chamber, and therefore the front cavity of the device can collect the inflow gas of the turbine and lead the gas into the combustion chamber.
Further, the axes of the air inlet collecting pipe and the air outlet collecting pipe are arranged along the radial direction of the outer wall so as to reduce the flow resistance of the medium.
Further, according to the experience of structural design engineering, in order to meet the structural strength requirement, the exhaust gas collecting pipe and the intake gas collecting pipe are designed into cylindrical structures with semicircular sections, and are welded on the outer surface of the outer wall, and can also be rectangular or other sections as long as the strength requirement can be met.
The invention has the beneficial effects that:
1. according to the invention, the front cavity and the rear cavity are formed by the partition plate and the inner wall, media from different sources are separated and collected and redistributed according to the actual requirement of the combustion chamber, the amount of fuel introduced into the combustion chamber is controlled, and the phenomenon that the combustion chamber is not ignited due to rich combustion environment caused by excessive fuel introduced into the combustion chamber is avoided.
2. The flow dividing device realizes the decoupling of the turbine and the combustion chamber in the engine by replacing the blocking cover, and can meet the development requirements of various test working conditions.
3. The invention arranges the gas discharge channel and the supply channel in the support plate, simplifies the structure of the device and reduces the flow resistance of the air flow path.
4. The flow dividing device is changed to the minimum degree on the basis of the existing product, can meet the requirements of gas collection, flow division and supply in the shortest period, and is simple and convenient to operate.
Drawings
Fig. 1 is an internal structure view of an engine gas collecting and dividing device according to the present invention.
Fig. 2 is a structural diagram of the engine gas collecting and dividing device of the invention.
Fig. 3 is a structural view of the blind plate of the blanking cover of the invention.
Fig. 4 is a structural diagram of the plugging cover of the invention as an orifice plate.
FIG. 5 is a front view of the plate of the present invention.
FIG. 6 is a top view of the plate of the present invention.
Reference numerals: 1-partition board, 2-inner wall, 21-front cavity, 22-rear cavity, 3-support board, 31-gas discharge channel, 32-gas supply channel, 4-outer wall, 41-connecting flange a, 5-exhaust gas collecting pipe, 6-gas inlet collecting pipe, 7-exhaust interface, 8-gas inlet interface, 9-block cover and 91-through hole.
Detailed Description
The invention will be further described with reference to the accompanying drawings in which:
the precooling combined engine decouples the turbine and the combustion chamber, and the flow rate and the type of media of the turbine and the combustion chamber are different, so that an engine gas collecting and shunting device needs to be designed, gas media for driving the turbine are collected and then discharged or redistributed according to the structural characteristics of the precooling combined engine, namely the requirement of coaxial layout of the air compressor and the combustion chamber, and meanwhile, fuel supply can be provided according to the requirement of the combustion chamber. Based on the technical scheme, the invention provides an engine gas collecting and distributing device.
As shown in fig. 1 and 2, the engine gas collecting and distributing device of the present invention includes a housing, an intake manifold 6, an exhaust manifold 5, a partition board 1, a support board 3, and a blocking cover 9.
Specifically, the casing includes inner wall 2, outer wall 4, and preferably, in order to be connected and form the air current passageway with turbine and combustion chamber for convenience, the diverging device wholly is cylindric structure, and inner wall 2 and outer wall 4 are cylindric structure, and both coaxial settings. Specifically, the inner wall 2 is connected to a front end module (i.e. a turbine) and a rear end module (i.e. a combustion chamber) by using a lap joint structure, and the outer wall 4 is connected to the front end module and the rear end module (i.e. the combustion chamber) by using a flange structure, specifically, a connecting flange a41 and a connecting flange b (not shown in the figure) are respectively arranged at the front end and the rear end of the outer wall 4, the connecting flange a41 is connected to the turbine of the engine by using screws, and the connecting flange b is connected.
In order to realize the separation of different source media, partition plates 1 are arranged on the inner surface of the inner wall 2 at equal intervals in the radial direction, the partition plates 1 divide the inner wall 2 into a closed front cavity 21 and a closed rear cavity 22, the front cavity formed by the partition plates and the inner wall collects the inflow gas of the turbine, and the rear cavity realizes the supply of the combustion chamber gas.
In order to realize the discharge and supply of the gas, the support plates 3 are arranged on the outer surface of the inner wall 2 at equal intervals in the circumferential direction, so that the structural strength of the product can be ensured, and the number of the support plates and the flow cross-sectional areas of the gas discharge channel 31 and the gas supply channel 32 can be adjusted according to the design requirements. Meanwhile, an air inlet gas collecting tube 6 and an air outlet gas collecting tube 5 are arranged on the outer surface of the outer wall 4, an air inlet port is arranged at the outer end of the air inlet gas collecting tube 6, an air outlet port 7 is arranged at the outer end of the air outlet gas collecting tube 5, the air inlet gas collecting tube 6 is arranged at the rear end of the outer wall 4, namely, at one end corresponding to the rear cavity 22, the axes of the air inlet gas collecting tube 6 and the air outlet gas collecting tube 5 are radially arranged along the outer wall 4, and a smooth air inlet channel can be formed after the air inlet gas collecting tube 6, the air supply channel 32 of the support plate 3 and the rear cavity 22 are communicated, so that the flow resistance of; the exhaust gas collecting pipe 5 is arranged at the front end of the outer wall 4, namely, at the end corresponding to the front cavity 21, so that a smooth exhaust channel can be formed after the front cavity 21, the gas exhaust channel 31 of the support plate 3 and the exhaust gas collecting pipe 5 are communicated. Specifically, the exhaust gas collecting pipe 5 and the gas inlet collecting pipe 6 are both of a cylindrical structure with a semicircular cross section and are welded on the outer surface of the outer wall 4, an exhaust interface 7 and a gas inlet interface 8 are respectively welded at the outer ports of the exhaust gas collecting pipe 5 and the gas inlet collecting pipe 6, and the exhaust interface 7 and the gas inlet interface 8 are respectively connected with a gas collecting system and a supply system through flange structures.
Preferably, as shown in fig. 5 and 6, the support plate 3 is in a streamline shape, the specific cross section is a diamond shape, the flow resistance of the medium can be reduced, the gas discharge channel 31 and the gas supply channel 32 are arranged in the support plate, the axes of the gas discharge channel 31 and the gas supply channel 32 are arranged in parallel, and the gas discharge channel 31 and the gas supply channel 32 are not communicated, the cross section areas of the gas discharge channel 31 and the gas supply channel 32 are mainly determined according to the gas flow passing through the gas discharge channel and the gas supply channel, and the cross section areas can be adjusted arbitrarily according to the flow rate; the front chamber 21 forms an exhaust passage for gas with the gas exhaust passage 31 and the exhaust header 5, and the rear chamber 22 forms an intake passage for gas with the gas supply passage 32 and the intake header 6. The incoming flow gas collected by the front cavity 21 is led out to the exhaust gas collecting pipe 5 on the outer side of the outer wall 4 through the gas exhaust channel 31 in the support plate 3, and is finally exhausted through the exhaust interface 7 according to the requirement; the gas is supplied through a rear cavity formed by the partition plate and the inner wall, enters the gas inlet collecting pipe 6 from the gas inlet interface, is divided and then enters the rear cavity 22 through the gas supply channel 32 in the support plate 3, and finally is supplied to a subsequent component, namely a combustion chamber.
In order to be suitable for different medium environments, the middle part of the partition plate 1 is provided with a detachable blocking cover 9, and in order to facilitate the replacement of the blocking cover 9, the blocking cover 9 is connected with the partition plate 1 in a threaded mode. In actual use, the blanking cover 9 is replaced by a blind plate or a hole plate with a specific through hole 91 as shown in fig. 3 or 4 according to specific requirements. Specifically, when the blind plate is selected as the blind plate, the blind plate 9 completely isolates the correlation between the front-end collected gas and the rear-end supplied gas, can realize the complete decoupling of the turbine drive and the fuel supply, and can modify the inlet and outlet parameters and types of two paths of media according to the development requirements. When the blocking cover 9 is a pore plate, the flow shunting function can be realized, one part of the incoming flow gas at the front end is supplied to the combustion chamber, and the other part of the incoming flow gas is discharged through the exhaust channel, so that the flow decoupling of turbine driving and fuel supply is realized, and the condition is mainly applied to the condition that the flow of the turbine is greater than the flow required by the combustion of the combustion chamber tissue, and the combustion tissue environment can be improved; the aperture of the orifice plate is designed according to the test requirements.
The engine gas collecting and distributing device is arranged in a precooling combined engine, the inner wall 2 and the outer wall 4 are in butt joint with a turbine to form a closed air flow path, and air flows out of the front-end turbine to enter the engine gas collecting and distributing device and then enters a rear-end combustion chamber.
The details not described in the present specification are within the common general knowledge of those skilled in the art.
Claims (8)
1. The utility model provides an engine gas collects diverging device which characterized in that: comprises a shell, an air inlet gas collecting pipe (6), an air outlet gas collecting pipe (5), a clapboard (1), a support plate (3) and a blanking cover (9); the shell comprises an inner wall (2) and an outer wall (4), and the inner wall (2) and the outer wall (4) are coaxially arranged; support plates (3) are circumferentially arranged on the outer surface of the inner wall (2) at equal intervals; the inner surface of the inner wall (2) is radially provided with a partition plate (1), and the partition plate (1) divides the inner wall (2) into a closed front cavity (21) and a closed rear cavity (22); the outer surface of the outer wall (4) is provided with an air inlet gas collecting pipe (6) and an air exhaust gas collecting pipe (5), the air inlet gas collecting pipe (6) is communicated with the rear cavity (22), the air exhaust gas collecting pipe (5) is communicated with the front cavity (21), the outer end of the air inlet gas collecting pipe (6) is provided with an air inlet interface (8), and the outer end of the air exhaust gas collecting pipe (5) is provided with an air exhaust interface (7).
2. The engine gas collecting and splitting apparatus according to claim 1, wherein: the middle part of the clapboard (1) is provided with a detachable plug cover (9).
3. The engine gas collecting and splitting apparatus according to claim 2, wherein: the blocking cover (9) is in threaded connection with the partition plate (1).
4. An engine gas collecting and dividing device according to claim 2 or 3, wherein: the middle part of the blocking cover (9) is provided with a through hole (91).
5. The engine gas collecting and splitting apparatus according to claim 4, wherein: the support plate (3) is in a streamline shape, a gas discharge channel (31) and a gas supply channel (32) are arranged in the support plate, and the gas discharge channel (31) and the gas supply channel (32) are respectively communicated with the front cavity (21) and the rear cavity (22).
6. The engine gas collecting and splitting apparatus according to claim 5, wherein: the front end and the rear end of the outer wall (4) are respectively provided with a connecting flange a (41) and a connecting flange b, the connecting flange a (41) is connected with a turbine of an engine, and the connecting flange b is connected with a combustion chamber of the engine.
7. The engine gas collecting and splitting apparatus according to claim 1, wherein: the axes of the air inlet collecting pipe (6) and the air outlet collecting pipe (5) are arranged along the radial direction of the outer wall (4).
8. The engine gas collecting and splitting apparatus according to claim 1, wherein: the exhaust gas collecting pipe (5) and the air inlet gas collecting pipe (6) are both of a cylindrical structure with a semicircular section and are welded on the outer surface of the outer wall (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911285954.0A CN111120107B (en) | 2019-12-13 | 2019-12-13 | Engine gas collecting and distributing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911285954.0A CN111120107B (en) | 2019-12-13 | 2019-12-13 | Engine gas collecting and distributing device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111120107A true CN111120107A (en) | 2020-05-08 |
| CN111120107B CN111120107B (en) | 2021-05-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911285954.0A Active CN111120107B (en) | 2019-12-13 | 2019-12-13 | Engine gas collecting and distributing device |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4707982A (en) * | 1981-06-26 | 1987-11-24 | Rockwell International Corporation | Thermal regenerative injector |
| US5025623A (en) * | 1988-09-13 | 1991-06-25 | Mitsubishi Jukogyo Kabushiki Kaisha | Rocket engine |
| JPH0486360A (en) * | 1990-07-30 | 1992-03-18 | Mitsubishi Heavy Ind Ltd | Air liquefying cycle engine |
| CN102606341A (en) * | 2011-12-22 | 2012-07-25 | 沈阳冠能燃气轮机科技有限公司 | Method for refitting retired aircraft into engine, and engine refitted by such method |
| CN106225953A (en) * | 2016-08-02 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of air cooling high temperature resistant test adaptor section |
| CN107795408A (en) * | 2017-06-09 | 2018-03-13 | 胡建新 | A kind of unchoked solid rocket ramjet gas flow adjusting means |
-
2019
- 2019-12-13 CN CN201911285954.0A patent/CN111120107B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4707982A (en) * | 1981-06-26 | 1987-11-24 | Rockwell International Corporation | Thermal regenerative injector |
| US5025623A (en) * | 1988-09-13 | 1991-06-25 | Mitsubishi Jukogyo Kabushiki Kaisha | Rocket engine |
| JPH0486360A (en) * | 1990-07-30 | 1992-03-18 | Mitsubishi Heavy Ind Ltd | Air liquefying cycle engine |
| CN102606341A (en) * | 2011-12-22 | 2012-07-25 | 沈阳冠能燃气轮机科技有限公司 | Method for refitting retired aircraft into engine, and engine refitted by such method |
| CN106225953A (en) * | 2016-08-02 | 2016-12-14 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of air cooling high temperature resistant test adaptor section |
| CN107795408A (en) * | 2017-06-09 | 2018-03-13 | 胡建新 | A kind of unchoked solid rocket ramjet gas flow adjusting means |
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| CN111120107B (en) | 2021-05-04 |
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