CN215408905U - Pre-cooling air supply control system for scramjet and RBCC engine and engine - Google Patents
Pre-cooling air supply control system for scramjet and RBCC engine and engine Download PDFInfo
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- CN215408905U CN215408905U CN202121257243.5U CN202121257243U CN215408905U CN 215408905 U CN215408905 U CN 215408905U CN 202121257243 U CN202121257243 U CN 202121257243U CN 215408905 U CN215408905 U CN 215408905U
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Abstract
The invention discloses a pre-cooling air supply control system of a scramjet and RBCC engine and the engine, comprising a power controller, a pre-pump valve, a filter, a fuel storage tank, an air turbine, a fuel pump, a temperature sensor, a high-temperature distributor, a secondary high-temperature control valve, a fuel liquid collecting port, an air inlet channel third wedge, an air taking device, an air pre-cooler, a fuel regulator, a fuel gas collecting port, a pressure sensor and a primary high-temperature control valve. According to the invention, based on the third wedge gas of the air inlet channel, the air in the atmosphere is directly utilized through the supply mode that the fuel cools the third wedge gas and then drives the turbine pump, and the consumption of the propellant is not additionally increased; in addition, a multi-stage fuel control mode of regulating the total flow of the fuel after pumping and distributing the cooled fuel is adopted, so that the technical problems of wide working range and high-performance multi-stage fuel supply control and comprehensive heat management of the scramjet engine and the RBCC engine are solved.
Description
Technical Field
The invention belongs to the field of engines, and particularly relates to a pre-cooling air supply control system of a scramjet and RBCC engine and an engine.
Background
The scramjet engine and the RBCC (Rocked-Based Combined Cycle, RBCC) engine are one of power devices of various aircrafts such as a hypersonic aircraft, a world round-trip transportation system and the like, wherein the system composition, the working principle and the working range of the RBCC engine in an air suction type working mode are basically consistent with those of the scramjet engine.
The function of the engine supply control system is to supply the different injectors of the engine with propellant that meets the requirements of a given flow, pressure, etc. The supply control system of the air-breathing type module of the scramjet engine and the RBCC engine generally adopts the supply modes of an air turbine pump, a gas turbine pump, a motor pump and the like, wherein the gas turbine pump mode needs to be additionally provided with additional devices such as a gas generator, a fuel storage tank, a fuel regulator and the like, and the comprehensive specific impulse of the engine is reduced because the gas turbine needs to consume additional propellant; the motor pump has the advantages of simple structure, convenient use and maintenance and the like, but the power density of the motor and the battery is difficult to be greatly improved in a foreseeable considerable period of time, so that the scheme of the motor pump is not suitable for long-endurance flying tasks. The air turbine pump scheme adopts the air in the atmosphere to pressurize the fuel pump, and theoretically can work in an infinite way. However, when the scramjet and RBCC engine works under a high Mach number, the total incoming flow temperature is as high as 1600-2400K, and how to solve the cooling and structural reliability of the air turbine is a great technical problem.
In addition, the working Mach number and the working height range of the scramjet and RBCC engines are wide, the fuel flow variation range is wide, and the stamping combustion chamber generally adopts multi-stage fuel injection, namely a supply control system also needs to realize multi-stage fuel high-precision adjustment and quick response control; on the other hand, when the scramjet engine and the RBCC engine work, the temperature of the combustion chamber is very high, structural thermal protection measures such as active cooling and the like need to be taken for the structure of the combustion chamber, and the available coolant is only fuel oil.
Therefore, how to realize the fuel supply, regulation, control and comprehensive thermal management of the scramjet and RBCC engine is a prominent problem to be solved by a supply control system.
Disclosure of Invention
The invention aims to provide a pre-cooling air supply control system of a scramjet and RBCC engine and the engine, so as to solve the technical problems of fuel supply, regulation, control and comprehensive heat management of the scramjet and RBCC engine.
In order to solve the technical problems, the specific technical scheme of the invention is as follows:
the pre-cooling air supply control system of the scramjet and RBCC engine comprises a power controller, a pre-pump valve, a filter, a fuel storage tank, an air turbine, a fuel pump, a temperature sensor, a high-temperature distributor, a secondary high-temperature control valve, a fuel liquid collecting port, an air inlet third wedge, an air taking device, an air pre-cooler, a fuel regulator, a fuel gas collecting port, a pressure sensor and a primary high-temperature control valve;
the power controller is respectively connected with the pre-pump valve, the fuel oil regulator, the high-temperature distributor, the primary high-temperature control valve, the secondary high-temperature control valve, the temperature sensor and the pressure sensor to control the scramjet engine and the RBCC engine;
the fuel storage tank is connected with a filter, a pre-pump valve, an air turbine, a fuel pump, an air precooler and a fuel regulator;
the third wedge of the air inlet channel is sequentially connected with an air taking device and an air precooler;
one end of the fuel regulator is connected with the fuel pump, and the other end of the fuel regulator is connected with the air precooler;
the air precooler is connected with the fuel oil collecting port;
the fuel oil collection port is connected with the fuel oil collection port;
the fuel oil gas collecting port is connected with a high-temperature distributor;
one end of the high-temperature distributor is connected with a primary high-temperature control valve and a primary combustion chamber of the engine; the other end of the high-temperature distributor is connected with a secondary high-temperature control valve and a secondary combustion chamber of the engine.
Furthermore, the third wedge of the air inlet channel is provided with an air taking groove longitudinally along the flow direction.
The invention provides an engine, which adopts the pre-cooling air supply control system of the scramjet and RBCC engine.
The pre-cooling air supply control system of the scramjet and RBCC engine and the engine have the following advantages that:
(1) the boundary layer suction measure of the high-speed air inlet channel is combined with the air turbine pump supply system, so that the problem that high-temperature air which is sucked independently is difficult to discharge is solved, and the power input requirement required by pump pressurization is also met;
(2) the online measurement and control mode of the power controller, the pressure sensor, the temperature regulator and the high-temperature distributor is adopted, the control of the total fuel flow and the control of the fuel distribution proportion are realized, and the problem that the high-temperature fuel cannot be accurately measured and controlled is solved;
(3) by adopting the air precooler, the total temperature of the air for driving the turbine is reduced, and the technical problem of thermal protection of a high-temperature turbine structure is solved.
Drawings
FIG. 1 is a schematic illustration of a pre-cooled air supply control system and engine for a scramjet and RBCC engine of the present invention;
FIG. 2 is a third spanwise view of the inlet of the present invention;
FIG. 3 is a cross-sectional view of the air extraction slot of the present invention.
The notation in the figure is: 1. a power controller; 2. a pre-pump valve; 3. a filter; 4. a fuel storage tank; 5. an air turbine; 6. a fuel pump; 7. a temperature sensor; 8. a high temperature distributor; 9. a secondary high temperature control valve; 10. a fuel oil collection port; 11. a third wedge of the air inlet channel; 12. a gas taking device; 13. an air precooler; 14. a fuel regulator; 15. a fuel oil collection port; 16. a pressure sensor; 17. a first-stage high-temperature control valve; 18. an air intake groove.
Detailed Description
For a better understanding of the objects, structure and function of the present invention, a scramjet and RBCC engine pre-cooling air supply control system and engine will be described in further detail with reference to the accompanying drawings.
As shown in figure 1, the invention comprises a power controller 1, a pre-pump valve 2, a filter 3, a fuel storage tank 4, an air turbine 5, a fuel pump 6, a temperature sensor 7, a high-temperature distributor 8, a secondary high-temperature control valve 9, a fuel collecting port 10, an air inlet third wedge 11, an air taking device 12, an air precooler 13, a fuel regulator 14, a fuel collecting port 15, a pressure sensor 16 and a primary high-temperature control valve 17.
The fuel storage tank 4 is connected with the filter 3, the pre-pump valve 2, the air turbine 5, the fuel pump 6, the air precooler 13 and the fuel regulator 14. The low-pressure fuel in the fuel storage tank 4 enters the fuel pump 6 after passing through the filter 3 and the pre-pump valve 2, the air turbine 5 pressurizes the fuel pump 6, and the pressurized high-pressure fuel enters the air precooler 13 after passing through the fuel regulator 14.
The air precooler 13 is arranged at the right side of the third wedge 11 of the air inlet, and an air taking device 12 is connected between the third wedge 11 of the air inlet and the air precooler 13. A thicker boundary layer exists at the third wedge 11 of the air inlet channel, a plurality of air taking grooves 18 are longitudinally arranged at the third wedge 11 of the air inlet channel along the flow direction, and as shown in figures 2 and 3, part of air in the separation boundary layer enters the air taking device 12 after passing through the air taking grooves and enters the air precooler 13.
In the air precooler 13, the fuel oil exchanges heat with high-temperature air, the air temperature is reduced, and the fuel oil temperature is increased.
The cooled air enters the air turbine 5 to drive the air turbine 5 to do work, the turbine drives the fuel pump 6 to start rotating, and the low-pressure and low-temperature air passing through the air turbine 5 is discharged out of the engine body.
The air precooler 13 is connected with the fuel oil collecting port 10, and the fuel oil collecting port 10 is connected with the fuel oil collecting port 15. The fuel oil after being heated enters the fuel oil collecting port 10 of the engine to actively cool the engine structure and is finally discharged from the fuel oil collecting port 15, and the fuel oil is in a gaseous state or a two-phase flow state; the fuel oil collecting port 15 is connected with the high-temperature distributor 8, the fuel oil enters the high-temperature distributor 8 after passing through the fuel oil collecting port 15 and then is divided into two paths, the first path of high-temperature distributor 8 is connected with the primary high-temperature control valve 17, the high-temperature distributor 8 enters the primary combustion chamber of the engine after passing through the primary high-temperature control valve 17, the second path of high-temperature distributor 8 is connected with the secondary high-temperature control valve, and the high-temperature distributor enters the secondary combustion chamber of the engine after passing through the secondary high-temperature control valve 9;
the power controller 1 is respectively connected with the pump front valve 2, the fuel oil regulator 14, the high-temperature distributor 8, the first-stage high-temperature control valve 17, the second-stage high-temperature control valve 9, the temperature sensor 7 and the pressure sensor 16 through a cable group and branches thereof, and controls the scramjet engine and the RBCC engine.
When the scramjet engine and the RBCC engine work, the power controller 1 receives flight state parameters and engine self-measured parameters, calculates an engine thrust instruction or an oil supply instruction in real time, and controls the total fuel flow of the engine through the fuel regulator 14;
when the scramjet engine and the RBCC engine work, the power controller 1 receives flight state parameters and parameters such as temperature and pressure measured by the engine and corrects the fuel distribution proportion of the high-temperature distributor 8 in real time through an internally bound control rule, so that the fuel flow entering a first-stage combustion chamber and a second-stage combustion chamber of the engine is corrected.
The patent provides a supply mode of taking gas based on a third wedge 11 of an air inlet channel, cooling the gas by fuel oil and then driving a turbine pump, directly utilizes air in the atmosphere and does not additionally increase propellant consumption; in addition, a multi-stage fuel control mode of regulating the total flow of the fuel after pumping and distributing the cooled fuel is adopted, so that the technical problems of wide working range and high-performance multi-stage fuel supply control and comprehensive heat management of the scramjet engine and the RBCC engine are solved.
It is to be understood that the present invention has been described with reference to certain embodiments, and that various changes in the features and embodiments, or equivalent substitutions may be made therein by those skilled in the art without departing from the spirit and scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed, but that the invention will include all embodiments falling within the scope of the appended claims.
Claims (3)
1. A pre-cooling air supply control system of a scramjet and RBCC engine is characterized by comprising a power controller (1), a pre-pump valve (2), a filter (3), a fuel storage tank (4), an air turbine (5), a fuel pump (6), a temperature sensor (7), a high-temperature distributor (8), a secondary high-temperature control valve (9), a fuel liquid collecting port (10), an air inlet third wedge (11), an air taking device (12), an air precooler (13), a fuel regulator (14), a fuel gas collecting port (15), a pressure sensor (16) and a primary high-temperature control valve (17);
the power controller (1) is respectively connected with the pre-pump valve (2), the fuel regulator (14), the high-temperature distributor (8), the primary high-temperature control valve (17), the secondary high-temperature control valve (9), the temperature sensor (7) and the pressure sensor (16) to control the scramjet engine and the RBCC engine;
the fuel storage tank (4) is connected with a filter (3), a pre-pump valve (2), an air turbine (5), a fuel pump (6), an air precooler (13) and a fuel regulator (14);
the third wedge (11) of the air inlet channel is sequentially connected with an air taking device (12) and an air precooler (13);
one end of the fuel oil regulator (14) is connected with the fuel oil pump (6), and the other end of the fuel oil regulator is connected with the air precooler (13);
the air precooler (13) is connected with the fuel oil collecting port (10);
the fuel oil collecting port (10) is connected with a fuel oil collecting port (15);
the fuel oil air collecting port (10) is connected with the high-temperature distributor (8);
one end of the high-temperature distributor (8) is connected with a primary high-temperature control valve (17) and a primary combustion chamber of the engine; the other end of the high-temperature distributor (8) is connected with a secondary high-temperature control valve (9) and a secondary combustion chamber of the engine.
2. The pre-cooled air supply control system for a scramjet and RBCC engine as claimed in claim 1, wherein said third wedge (11) of the air intake channel is provided with an air intake slot (18) longitudinally along the flow direction.
3. An engine comprising the overfire and RBCC engine pre-cooling air supply control system of any of claims 1-2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121257243.5U CN215408905U (en) | 2021-06-07 | 2021-06-07 | Pre-cooling air supply control system for scramjet and RBCC engine and engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121257243.5U CN215408905U (en) | 2021-06-07 | 2021-06-07 | Pre-cooling air supply control system for scramjet and RBCC engine and engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215408905U true CN215408905U (en) | 2022-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121257243.5U Active CN215408905U (en) | 2021-06-07 | 2021-06-07 | Pre-cooling air supply control system for scramjet and RBCC engine and engine |
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| CN (1) | CN215408905U (en) |
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2021
- 2021-06-07 CN CN202121257243.5U patent/CN215408905U/en active Active
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Effective date of registration: 20221114 Address after: 710000 C409-C30, Floor 4, Building 1, Huigu Commercial Street, Southeast Silk Road, Cross of Shenzhou 6th Road and Hangtuo Road, Xi'an National Civil Aerospace Industry Base, Shaanxi Province Patentee after: Xi'an Tanhuo Aerospace Technology Co.,Ltd. Address before: No. 29, Qinhuai District, Qinhuai District, Nanjing, Jiangsu Patentee before: Nanjing University of Aeronautics and Astronautics |
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Effective date of registration: 20230131 Address after: 215000 158 Chengsi Road, Lili Town, Wujiang District, Suzhou City, Jiangsu Province Patentee after: Aerospace Promotion (Suzhou) Aerospace Technology Co.,Ltd. Address before: 710000 C409-C30, Floor 4, Building 1, Huigu Commercial Street, Southeast Silk Road, Cross of Shenzhou 6th Road and Hangtuo Road, Xi'an National Civil Aerospace Industry Base, Shaanxi Province Patentee before: Xi'an Tanhuo Aerospace Technology Co.,Ltd. |
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