CN-121973938-A - Wide-range supersonic electrochemical auxiliary combined power circulation system

CN121973938ACN 121973938 ACN121973938 ACN 121973938ACN-121973938-A

Abstract

The invention provides a wide-range supersonic electrochemical auxiliary combined power circulation system, and belongs to the technical field of aviation propulsion. The problems that an existing supersonic engine cannot compress air stably and efficiently in the cross-speed domain flight and provides stable, clean and air with proper humidity for a fuel cell are solved. The device comprises a propulsion system, a fuel cell system and a lubrication and cooling system, wherein the propulsion system sequentially comprises an air inlet channel, a screw compressor I, a motor I, a screw compressor II, a motor II and an injection tail nozzle from front to back, and motor shafts of the motor I and the motor II are respectively connected with screw shafts of the screw compressor I and the screw compressor II. The invention takes the fuel cell as power, is a high-efficiency and zero-pollution engine, adopts a two-stage screw compressor, has higher supercharging, stable work and insensitivity to inlet air pressure and flow fluctuation, can stably and efficiently compress air during the cross-speed-domain flight, and simultaneously provides stable, clean and air with proper humidity for the fuel cell.

Inventors

JI ZHIXING
HE XIN
CHENG LIWEN
XU ZIBO
HUANG JIAO
WANG ZHANXUE

Assignees

西北工业大学

Dates

Publication Date: 20260505
Application Date: 20260116

Claims (10)

1. The broad-range supersonic electrochemical auxiliary combined power circulation system is characterized by comprising a propulsion system, a fuel cell system and a lubrication and cooling system; The propulsion system sequentially comprises an air inlet channel (1), a screw compressor I (22), a motor I (21), a screw compressor II (18), a motor II (16) and an injection tail nozzle (17) from front to back, wherein motor shafts of the motor I (21) and the motor II (16) are respectively connected with screw shafts of the screw compressor I (22) and the screw compressor II (18); The fuel cell system comprises a fuel cell I (6), a fuel cell II (11), a hydrogen tank (3), a cathode air inlet main runner (4), a fuel cell I cathode air inlet runner (5), a fuel cell II cathode air inlet runner (10), a fuel cell I cathode air outlet runner (8), a fuel cell II cathode air outlet runner (12), an air entraining runner (7) and an anode runner (13), wherein the cathode air inlet main runner (4) is used for entraining air from an air inlet channel (1), passes through cathodes of the fuel cell I (6) and the fuel cell II (11) and is converged into an ejector tail nozzle (17) to flow, an inlet of the fuel cell I cathode air inlet runner (5) is connected with a screw compressor I (22), an outlet of the fuel cell I cathode air inlet runner is connected with a cathode inlet of the fuel cell I (6), an inlet of the fuel cell I cathode air outlet runner (8) is connected with a cathode outlet of the fuel cell I (6), the outlet of the fuel cell I cathode air outlet is converged into the tail nozzle (17) to flow together with gas introduced from the screw compressor I (22) and an intermediate air inlet of the screw compressor (18), the air entraining runner (7) is connected with the screw compressor II air inlet of the fuel cell I (18), the outlet is connected with a cathode inlet of a fuel cell II (11), an inlet of a cathode outlet flow channel (12) of the fuel cell II is connected with a cathode outlet of the fuel cell II (11), the outlet is converged into an injection tail nozzle (17) secondary flow, an inlet of an anode flow channel (13) is connected with a hydrogen tank (3), a fuel cell I (6) and an anode of the fuel cell II (11) are connected in series and then converged into a cathode inlet main flow channel (4), and the fuel cell I (6) and the fuel cell II (11) respectively supply power for a motor I (21) and a motor II (16); the lubricating and cooling system comprises an oil pump (20), an oil sprayer (19) and a lubricating oil conveying oil way, wherein the lubricating oil conveying oil way conveys lubricating oil to the joints of the oil sprayer (19) and the screw compressors to achieve the purposes of lubrication and cooling, and the lubricating oil is collected by the screw compressors and returns to the oil pump (20) through the lubricating oil conveying oil way.
2. The broad range supersonic electrochemical auxiliary combined power cycle system of claim 1, wherein the screw compressor I (22) and the screw compressor II (18), the motor I (21) and the motor II (16) are all multiple and are uniformly arranged in the engine inner runner along the circumferential direction.
3. The broad range supersonic electrochemical auxiliary combined power cycle system of claim 1, wherein the fuel cells I (6) and II (11) are arranged outside the engine flow channel in a circumferential direction uniformly.
4. The broad range supersonic electrochemical auxiliary combined power cycle system of claim 1, wherein said fuel cell I cathode inlet runner (5) and fuel cell II cathode inlet runner (10) bleed air channels in screw compressor I (22) and screw compressor II (18) are T-shaped.
5. The broad-range supersonic electrochemical auxiliary combined power circulation system according to claim 1 is characterized in that a valve (9) is arranged at the outlet of a hydrogen tank (3) on the anode flow channel (13) and used for regulating and controlling the flow of hydrogen, and a valve (9) is arranged on the air-entraining flow channel (7) and used for regulating and controlling the air-entraining amount.
6. The broad range supersonic electrochemical assisted combined power cycle system of claim 1, wherein said cathode inlet primary flowpath (4) is equipped with a diffuser (2) prior to entering fuel cell I (6) to achieve deceleration pressurization of the gas stream.
7. The broad range supersonic electrochemical auxiliary combined power cycle system of claim 1, wherein a one-way valve (15) is installed before the secondary flow is converged into the jet tail pipe (17), the one-way valve (15) is installed at the outlet of the cathode outlet flow channel (8) of the fuel cell I, and the one-way valve (15) is also installed before the anode flow channel (13) is converged into the cathode inlet main flow channel (4) so as to prevent reverse flow of air flow.
8. The broad range supersonic electrochemical auxiliary combined power cycle system of claim 1, wherein a pressure reducing valve (14) is arranged at the outlet of a cathode outlet flow channel (12) of the fuel cell II.
9. The broad range supersonic electrochemical assisted combined power cycle system of claim 1, wherein said oil pump (20) is mounted on an engine axis between screw compressor I (22) and screw compressor II (18).
10. A method of using the broad range supersonic electrochemical auxiliary combined power cycle of any one of claims 1-9, wherein: After the air is subjected to deceleration and pressurization through the air inlet channel (1), a part of air enters the diffuser (2) through the cathode air inlet main flow channel (4) to be further subjected to deceleration and pressurization, and then flows into the cathode of the fuel cell I (6), meanwhile, a valve (9) at the outlet of the hydrogen tank (3) on the anode flow channel (13) is opened, hydrogen enters the anode of the fuel cell I (6), the fuel cell I (6) generates electrochemical reaction to generate electric energy, the electric energy is supplied to the motor I (21), and a screw compressor I (22) connected with the motor I (21) starts to compress the main flow air subjected to deceleration and pressurization through the air inlet channel (1); The residual hydrogen after the reaction of the fuel cell I (6) flows into the anode of the fuel cell II (11) through the anode flow channel (13), the air after the reaction of the fuel cell I (6) flows into the cathode of the fuel cell II (11) through the cathode air inlet main flow channel (4), the fuel cell II (11) generates electric energy through the reaction of electrochemistry to supply power for the motor II (16), and the screw compressor II (18) connected with the motor II (16) starts to compress the main flow air compressed by the screw compressor I (22); After being compressed by a screw compressor I (22) and a screw compressor II (18), main flow air is expanded and accelerated to be ejected at an ejection tail nozzle (17) to generate thrust, a part of air in the screw compressor I (22) and the screw compressor II (18) respectively flows into a fuel cell cathode through a fuel cell I cathode air inlet runner (5) and a fuel cell II cathode air inlet runner (10) with T-shaped air entraining channels to react, and then flows into the ejection tail nozzle (17) through a fuel cell I cathode air outlet runner (8) and a fuel cell II cathode air outlet runner (12) respectively, and the secondary flow is ejected after the ejection tail nozzle (17) is ejected by main flow ejection to generate a part of thrust.

Description

Wide-range supersonic electrochemical auxiliary combined power circulation system Technical Field The invention belongs to the technical field of aviation propulsion, and particularly relates to a wide-range supersonic electrochemical auxiliary combined power circulation system. Background With the increasing demand of the aviation industry for environmental protection and efficient power, the development of zero-carbon or low-emission propulsion systems has become an important direction. Among them, hydrogen fuel cells are considered as important candidates for future aviation power due to their efficient, zero-pollution characteristics. Meanwhile, the development of a stable and economical supersonic engine has important strategic significance for national defense. Conventional supersonic propulsion systems, such as turbofan afterburner or ramjet engines, operate severely dependent on the speed of flight and air intake conditions. During transonic flight, particularly from subsonic acceleration to supersonic, the air flow, pressure and temperature captured by the air intake duct change drastically, which presents an extreme challenge to the stability and efficiency of the engine core components, particularly the front-end compression system. Under such non-design working conditions, the conventional axial flow or centrifugal compressor is easy to surge and stall, and the efficiency is greatly reduced, so that the conventional axial flow or centrifugal compressor becomes a key bottleneck for restricting the wide working condition performance of the engine. On the other hand, fuel cells, particularly proton exchange membrane fuel cells suitable for high power density applications, require a continuous supply of air at a steady pressure, clean and suitable humidity for efficient operation. In summary, there is a lack of a supersonic engine in the prior art that can compress air stably and efficiently during cross-speed domain flight, and can provide stable, clean and air with proper humidity for the fuel cell, so that an innovative system configuration and component design are needed to realize efficient integration of the fuel cell and the supersonic engine. Disclosure of Invention In view of the above, the invention provides a wide-range supersonic electrochemical auxiliary combined power circulation system in order to solve the problems that the existing supersonic engine can not stably and efficiently compress air in the cross-speed-range flight and provide stable, clean and air with proper humidity for a fuel cell. In order to achieve the aim, the invention adopts the following technical scheme that the wide-range supersonic electrochemical auxiliary combined power circulation system comprises a propulsion system, a fuel cell system and a lubrication cooling system; the propulsion system sequentially comprises an air inlet channel, a screw compressor I, a motor I, a screw compressor II, a motor II and an injection tail nozzle from front to back, wherein motor shafts of the motor I and the motor II are respectively connected with screw shafts of the screw compressor I and the screw compressor II; The fuel cell system comprises a fuel cell I, a fuel cell II, a hydrogen tank, a cathode air inlet main runner, a fuel cell I cathode air inlet runner, a fuel cell II cathode air inlet runner, a fuel cell I cathode air outlet runner, a fuel cell II cathode air outlet runner, an air entraining runner and an anode runner; the cathode air inlet main runner is used for introducing air from the air inlet channel, passes through the cathodes of the fuel cell I and the fuel cell II and is converged into the secondary flow of the jet tail nozzle; the fuel cell I cathode inlet runner is connected with the screw compressor I, the outlet is connected with the fuel cell I cathode inlet, the fuel cell I cathode outlet runner inlet is connected with the fuel cell I cathode outlet, the outlet is converged into the jet tail nozzle secondary flow together with gas introduced from the air entraining runner, the air entraining runner is led by the connecting runner between the screw compressor I and the screw compressor II, the fuel cell II cathode inlet runner inlet is connected with the screw compressor II, the outlet is connected with the fuel cell II cathode inlet, the fuel cell II cathode outlet runner inlet is connected with the fuel cell II cathode outlet, the outlet is converged into the jet tail nozzle secondary flow, the anode runner inlet is connected with the hydrogen tank, and the fuel cell I and the fuel cell II anodes are converged into the cathode inlet main runner after being connected in series; The lubricating and cooling system comprises an oil pump, an oil sprayer and a lubricating oil conveying oil way, wherein the lubricating oil conveying oil way conveys lubricating oil to the joint of the oil sprayer and each screw compressor gear to achieve the purposes of lubrication and cooling, and the lubricating oil