阅读说明：本技术 一种回热循环发动机 (Regenerative cycle engine ) 是由 周红 秦浩 吴宇 于 2020-12-29 设计创作，主要内容包括：本申请提供一种回热循环发动机,回热循环发动机包括：压气机最后一级静叶(1),增压泵(2),出液管(3),冷却夹层(4),喷管(5),回液管(6),回液泵(7),燃烧室(8),其中：所述出液管(3)为管状结构,所述出液管(3)上设置有增压泵(2),所述出液管(3)的入口与压气机最后一级静叶(1)的上侧连通,所述出液管(3)的出口与冷却夹层(4)的进口连通；所述回液管(6)为管状结构,冷却夹层(4)上设置有回液泵(7),所述回液管(6)的入口与冷却夹层(4)的出口连通,所述回液管(6)的出口与压气机最后一级静叶(1)的下侧连通；所述冷却夹层(4)为筒状夹层结构,冷却夹层(4)位于喷管(5)外侧。(The application provides a regenerative cycle engine, regenerative cycle engine includes: compressor last stage quiet leaf (1), booster pump (2), drain pipe (3), cooling intermediate layer (4), spray tube (5), return liquid pipe (6), return liquid pump (7), combustion chamber (8), wherein: the liquid outlet pipe (3) is of a tubular structure, a booster pump (2) is arranged on the liquid outlet pipe (3), the inlet of the liquid outlet pipe (3) is communicated with the upper side of the last stage stationary blade (1) of the gas compressor, and the outlet of the liquid outlet pipe (3) is communicated with the inlet of the cooling interlayer (4); the liquid return pipe (6) is of a tubular structure, a liquid return pump (7) is arranged on the cooling interlayer (4), the inlet of the liquid return pipe (6) is communicated with the outlet of the cooling interlayer (4), and the outlet of the liquid return pipe (6) is communicated with the lower side of the last stage stationary blade (1) of the compressor; the cooling interlayer (4) is of a cylindrical interlayer structure, and the cooling interlayer (4) is located on the outer side of the spray pipe (5).)

1. A regenerative cycle engine, comprising: compressor last stage quiet leaf (1), booster pump (2), drain pipe (3), cooling intermediate layer (4), spray tube (5), return liquid pipe (6), return liquid pump (7), combustion chamber (8), wherein:

the liquid outlet pipe (3) is of a tubular structure, a booster pump (2) is arranged on the liquid outlet pipe (3), the inlet of the liquid outlet pipe (3) is communicated with the upper side of the last stage stationary blade (1) of the gas compressor, and the outlet of the liquid outlet pipe (3) is communicated with the inlet of the cooling interlayer (4); a liquid outlet pipe front section (3a) is arranged between the last stage stationary blade (1) of the gas compressor and the booster pump (2), and a liquid outlet pipe rear section (3b) is arranged between the booster pump (2) and the cooling interlayer (4);

the liquid return pipe (6) is of a tubular structure, a liquid return pump (7) is arranged on the cooling interlayer (4), an inlet of the liquid return pipe (6) is communicated with an outlet of the cooling interlayer (4), an outlet of the liquid return pipe (6) is communicated with the lower side of the last stage stationary blade (1) of the compressor, a liquid return pipe front section (6a) is arranged between the cooling interlayer (4) and the liquid return pump (7), and a liquid return pipe rear section (6b) is arranged between the liquid return pump (7) and the lower side of the last stage stationary blade (1) of the compressor;

the cooling interlayer (4) is of a cylindrical interlayer structure, and the cooling interlayer (4) is located on the outer side of the spray pipe (5).

2. The regenerative cycle engine according to claim 1, characterized in that the last stage stator vane (1), the liquid outlet pipe (3), the cooling interlayer (4) and the liquid return pipe (7) of the compressor are filled with a working medium, and the working medium is used for transferring heat of airflow in the nozzle to airflow at the inlet of the combustion chamber.

3. The regenerative cycle engine of claim 2, wherein the working medium comprises a bismuth lead alloy liquid metal.

4. The regenerative cycle engine of claim 3, wherein the bismuth-lead alloy liquid metal has a bismuth content of 56.5%, a melting point of 123.5 ℃ and a boiling point of 1670 ℃.

5. The regenerative cycle engine according to claim 1, characterized in that the booster pump (2) is used for driving bismuth-lead alloy liquid metal to flow from the upper side of the last stage stationary blade (1) of the compressor to the inlet of the cooling interlayer (4) along the liquid outlet pipe (3);

the liquid return pump (7) is used for driving the bismuth-lead alloy liquid metal to flow from the outlet of the cooling interlayer (4) to the lower side of the last stage stationary blade (1) of the compressor along the liquid return pipe (6).

6. The regenerative cycle engine according to claim 1, characterized in that the flow path of the air flow in the nozzle (5) is the same as that of a conventional engine, bismuth-lead alloy liquid metal exchanges heat with the air flow in the nozzle (5) in the cooling interlayer (4), the bismuth-lead alloy liquid metal absorbs heat, and the air flow in the nozzle (5) releases heat;

the flow path of the airflow at the inlet of the combustion chamber is the same as that of a conventional engine, bismuth-lead alloy liquid metal exchanges heat with the airflow at the inlet of the combustion chamber in the last stage stationary blade (1) of the compressor, the bismuth-lead alloy liquid metal releases heat, and the airflow at the inlet of the combustion chamber absorbs heat.

7. Regenerative cycle engine according to claim 1, characterized in that the scavenge pump (7) is mounted close to the lance (5).

8. The regenerative cycle engine of claim 1,

the engine can be started to work after 10-20 minutes of starting, and the oil return pump (7) can be started to work after 5-10 minutes of working.

9. Regenerative cycle engine according to claim 1, characterized in that the cooling sandwich (4) is internally provided with corrugated thin-walled heat exchanger fins.

10. The regenerative cycle engine according to claim 1, characterized in that the compressor last stage stationary vanes (1) are internally provided with multi-channel heat exchange tubes.

Technical Field

The invention belongs to the field of aviation, and relates to a regenerative cycle engine.

Background

The improvement of the heat efficiency of the engine is mainly realized by reforming the thermodynamic cycle or breaking through the technology of major components, and the intercooling regenerative cycle engine is one of the reforming thermodynamic cycle. The working principle of the disclosed intercooled regenerative cycle engine is generally as follows: (1) the indirect cooling ring section is positioned in an external duct of the engine, and guides the fan outlet of the engine or the middle-stage airflow of the compressor to the indirect cooling device through a pipeline to exchange heat with the external atmosphere so as to reduce the compression work; (2) in the heat regeneration step, the heat regenerator is positioned in the spray pipe, and the airflow at the inlet of the combustion chamber is led to the heat regenerator through a pipeline to exchange heat with the airflow in the spray pipe so as to improve the heat efficiency of the engine. However, the process of introducing the engine core flow to the intercooler or the regenerator not only incurs heavy construction and weight costs, but also causes great pressure loss, and finally offsets the benefits of the intercooling regenerative cycle. Therefore, the intercooling regenerative engine with application prospect should realize intercooling regenerative cycle without causing extra pressure loss to the core flow of the engine under the limited cost of structure and weight so as to really improve the propulsion efficiency of the engine. The indirect cooling ring joint is not the research object of the invention because the interstage cooling of the compressor can reduce the cycle heat efficiency and needs to be compensated by increasing the total pressure increase ratio.

Disclosure of Invention

The invention aims to provide a regenerative cycle engine, which effectively improves the thermal efficiency of the engine through limited weight and structure cost on the premise of not additionally increasing the core flow resistance of the engine, reduces the temperature of the wall surface and jet flow of a spray pipe and reduces the infrared radiation characteristic of an airplane.

The application provides a regenerative cycle engine, regenerative cycle engine includes: compressor last stage quiet leaf (1), booster pump (2), drain pipe (3), cooling intermediate layer (4), spray tube (5), return liquid pipe (6), return liquid pump (7), combustion chamber (8), wherein:

the liquid outlet pipe (3) is of a tubular structure, a booster pump (2) is arranged on the liquid outlet pipe (3), the inlet of the liquid outlet pipe (3) is communicated with the upper side of the last stage stationary blade (1) of the gas compressor, and the outlet of the liquid outlet pipe (3) is communicated with the inlet of the cooling interlayer (4); a liquid outlet pipe front section (3a) is arranged between the last stage stationary blade (1) of the gas compressor and the booster pump (2), and a liquid outlet pipe rear section (3b) is arranged between the booster pump (2) and the cooling interlayer (4);

the liquid return pipe (6) is of a tubular structure, a liquid return pump (7) is arranged on the cooling interlayer (4), an inlet of the liquid return pipe (6) is communicated with an outlet of the cooling interlayer (4), an outlet of the liquid return pipe (6) is communicated with the lower side of the last stage stationary blade (1) of the compressor, a liquid return pipe front section (6a) is arranged between the cooling interlayer (4) and the liquid return pump (7), and a liquid return pipe rear section (6b) is arranged between the liquid return pump (7) and the lower side of the last stage stationary blade (1) of the compressor;

the cooling interlayer (4) is of a cylindrical interlayer structure, and the cooling interlayer (4) is located on the outer side of the spray pipe (5).

Specifically, the last stage stationary blade (1), the liquid outlet pipe (3), the cooling interlayer (4) and the liquid return pipe (7) of the gas compressor are filled with working media, and the working media are used for transferring heat of airflow in the spray pipe to airflow at the inlet of the combustion chamber.

Specifically, the working medium comprises bismuth-lead alloy liquid metal.

Specifically, the bismuth-lead alloy liquid metal contains 56.5% of bismuth, has a melting point of 123.5 ℃ and a boiling point of 1670 ℃.

Specifically, the booster pump (2) is used for driving bismuth-lead alloy liquid metal to flow from the upper side of the last stage stationary blade (1) of the compressor to the inlet of the cooling interlayer (4) along the liquid outlet pipe (3);

the liquid return pump (7) is used for driving the bismuth-lead alloy liquid metal to flow from the outlet of the cooling interlayer (4) to the lower side of the last stage stationary blade (1) of the compressor along the liquid return pipe (6).

Specifically, the flow path of the air flow in the spray pipe (5) is the same as that of a conventional engine, bismuth-lead alloy liquid metal exchanges heat with the air flow in the spray pipe (5) in the cooling interlayer (4), the bismuth-lead alloy liquid metal absorbs heat, and the air flow in the spray pipe (5) releases heat;

the flow path of the airflow at the inlet of the combustion chamber is the same as that of a conventional engine, bismuth-lead alloy liquid metal exchanges heat with the airflow at the inlet of the combustion chamber in the last stage stationary blade (1) of the compressor, the bismuth-lead alloy liquid metal releases heat, and the airflow at the inlet of the combustion chamber absorbs heat.

Specifically, the scavenging pump (7) is mounted close to the nozzle (5).

Specifically, the liquid return pump (7) can be started to work after the engine is started for 10-20 minutes, and the booster pump (2) can be started to work after the oil return pump (7) works for 5-10 minutes.

Specifically, corrugated thin-wall heat exchange fins are arranged inside the cooling interlayer (4).

Specifically, a multi-channel heat exchange tube is arranged inside the last stage stationary blade (1) of the gas compressor.

The application provides a regenerative cycle engine, adopt indirect heat transfer's mode, introduce bismuth lead alloy liquid metal as working medium, give combustion chamber entry air current with the heat transfer of air current in the spray tube for combustion chamber entry air current temperature risees, and engine jet, spray tube wall and the temperature of radiating to organism surface reduce simultaneously.

Drawings

Fig. 1 is a schematic structural view of a regenerative cycle engine of the present invention.

Wherein: 1-the last stage of stator blade of the compressor, 2-the booster pump, 3-the drain pipe, 4-the cooling interlayer, 5-the spray pipe, 6-the liquid return pipe, 7-the liquid return pump, 8-the combustion chamber.

Detailed Description

The regenerative cycle engine of the present invention is further described with reference to the accompanying drawings of the specification:

the engine includes: the device comprises a last-stage stationary blade (1) of the gas compressor, a booster pump (2), a liquid outlet pipe (3), a cooling interlayer (4), a spray pipe (5), a liquid return pipe (6), a liquid return pump (7) and a combustion chamber (8); the invention relates to a regenerative cycle engine, wherein a cooling interlayer is arranged on the outer side of a spray pipe, a last stage of stationary blade of a gas compressor is communicated with the cooling interlayer through a liquid outlet pipe and a liquid return pipe, and bismuth-lead alloy liquid metal is filled in the last stage of stationary blade of the gas compressor, the cooling interlayer, the liquid outlet pipe and the liquid return pipe. The liquid outlet pipe is provided with a booster pump, and the liquid return pipe is provided with a liquid return pump for driving the bismuth-lead alloy liquid metal to flow along the pipeline. The high-temperature jet flow in the spray pipe heats the bismuth-lead alloy liquid metal in the cooling interlayer through the heat conduction effect of the wall surface of the spray pipe, and meanwhile, the temperature of the jet flow of the engine, the wall surface of the spray pipe and the surface of a machine body in a radiation area is greatly reduced. The heated bismuth-lead alloy liquid metal flows into the last stage stationary blade of the compressor through a liquid return pipe and a liquid return pump to heat airflow at the inlet of the combustion chamber so as to improve the efficiency of the engine. The bismuth-lead alloy liquid metal is cooled by the air flow at the outlet of the compressor and then returns to the spray pipe through the liquid outlet pipe and the liquid outlet pump. The invention is suitable for the engine with high propulsion efficiency, takes bismuth-lead alloy liquid metal with high heat conductivity coefficient as a working medium, and transfers the heat of airflow in the spray pipe to the airflow at the inlet of the combustion chamber, on one hand, the temperature of the airflow at the inlet of the combustion chamber is increased, and the engine efficiency can be improved; on the other hand, the temperature of the engine jet, the wall of the nozzle and the radiation to the surface of the body is significantly reduced, which reduces the infrared radiation characteristic of the aircraft.