WO2024045289A1

WO2024045289A1 - Aero-engine using liquid air as thermal working medium

Info

Publication number: WO2024045289A1
Application number: PCT/CN2022/126108
Authority: WO
Inventors: 易元明
Original assignee: 易元明; 吴桓勋
Priority date: 2022-08-29
Filing date: 2022-10-19
Publication date: 2024-03-07
Also published as: CN117627783A

Abstract

The present invention relates to an aero-engine using liquid air as a thermal working medium. The aero-engine is technically characterized in that liquid air is used as a thermal working medium, and the liquid air absorbs heat to be vaporized from high-heat compressed air generated by a turbine-type normal-temperature air compressor, so as to push a turbine-type high-pressure steam turbine to work; the turbine-type normal-temperature air compressor, a turbine-type low-temperature air compressor and a propeller are driven to operate at the same time; meanwhile, the low-temperature cooling capacity carried by the liquid air is repeatedly utilized by using an opposite forced convection heat transfer composite pipe, so as to efficiently generate a recoil thrust to push an aerospace plane to lift off and take off; and during normal quick navigation, collected relative motion air kinetic energy is used to replace the turbine-type high-pressure steam turbine to work, and liquid air and electric energy are continuously and quantitatively produced.

Description

液态空气热力工质航空发动机Liquid air thermal refrigerant aircraft engine

技术领域Technical field

本发明涉及航空动力设备，特别涉及一种液态空气热力工质航空发动机。The invention relates to aviation power equipment, in particular to a liquid air thermal working medium aircraft engine.

背景技术Background technique

目前的航空飞机，普遍采用燃油发动机为航空动力设备。Current aviation aircraft generally use fuel engines as aviation power equipment.

在其航行中，必须大量携带油料与消耗油料，同时大量产生二氧化碳废气。During its voyage, it must carry and consume a large amount of oil, and at the same time generate a large amount of carbon dioxide exhaust gas.

由于所携带的油料有限，也就决定了其航程有限。由于现有的航空发动机的推进功率有限，也就决定了现有航空飞机的载重量有限。Due to the limited fuel it carries, its range is limited. Since the propulsion power of existing aviation engines is limited, the load capacity of existing aviation aircraft is also limited.

目前采用蓄电池供电的航空飞机，由于其蓄电池的储电量非常有限，也就决定了现有电动航空飞机的航程与载重量十分有限。Currently, aviation aircraft powered by batteries have a very limited storage capacity, which determines that the range and load capacity of existing electric aviation aircraft are very limited.

已有的“航空飞机采用相对运动空气动能的方法与装置”技术发明，仅仅能够为快速航行中的飞机提供推进动力，无法为先前处于静止状态的航空飞机提供升空、起飞的推动动力。Existing technological inventions for "Methods and Devices for Using Relative Motion Aerodynamic Energy for Aircrafts" can only provide propulsion power for fast-flying aircrafts, but cannot provide propulsion power for aircrafts that were previously stationary to take off and take off.

发明内容Contents of the invention

本发明的目的是提供一种新的液态空气热力工质航空发动机，采用液态空气为热力发动机的热力工质，让机载液态空气吸收由涡轮高压汽轮机所驱动的涡轮式常温空气压缩机产生的高热压缩空气中的热量汽化成高压空气，再利用其去驱动涡轮高压汽轮机运转作功，推动航空飞机升空与起飞；然后，利用航空飞机快速航行中所产生的相对运动空气动能高效形成反冲推力、去推动航空飞机快速航行，同时持续定量生产液态空气与电能。从而，全面实现航空飞机从起飞到降落、全航程“零能耗”，以及载重量巨大、拥有无限航程诸项卓越技术效果。The object of the present invention is to provide a new liquid air thermal working medium aeroengine, which uses liquid air as the thermal working medium of the heat engine, allowing the airborne liquid air to absorb the energy generated by the turbine-type normal-temperature air compressor driven by the turbine high-pressure turbine. The heat in the high-heat compressed air vaporizes into high-pressure air, which is then used to drive the turbine high-pressure turbine to perform work, propelling the aircraft into the air and take off; then, the relative motion of the air kinetic energy generated by the aircraft's rapid flight is used to efficiently form a recoil Thrust, to propel aircraft to fly quickly, while continuing to quantitatively produce liquid air and electrical energy. As a result, the aircraft can fully achieve "zero energy consumption" from takeoff to landing and the entire flight, as well as various outstanding technical effects such as huge load capacity and unlimited range.

技术方案Technical solutions

一种液态空气热力工质航空发动机的工艺方法，其方法是采用液态空气为热力发动机的热力工质，让机载液态空气吸收由涡轮高压汽轮机驱动涡轮式常温空气压缩机所产生的高热压缩空气中的热量、汽化成高压空气，再利用其去驱动涡轮高压汽轮机运转；同时采用相向受迫对流换热复合管重复利用液态空气所携带的低温冷量，将涡轮式常温空气压缩机产生的高热压缩空气冷却为低温压缩空气，然后再利用涡轮式低温空气压缩机将其压缩为临界压力空气；最后将高密度的临界压力空气经螺旋桨推进器加速外排、高效转换成反冲推力，推动航空飞机快速行进，同时将其部分临界压力空气重新液化；在航空飞机快速航行中，停止利用液态空气汽化成为高压空气驱动涡轮高压汽轮机运转，改为由相对运动空气动能收集叶轮所收集的相对运动空气动能驱动涡轮式常温空气压缩机、涡轮式低温空气压缩机与螺旋桨推进器工作；同时采用第二相向受迫对流换热复合管，让涡轮式常温空气压缩机产生的高热压缩空气与涡轮式低温空气压缩机将从第一相向受迫对流换热复合管内吸入的低温压缩空气再次压缩成为临界压力空气，让两者在其中换热；最后将高密度的临界压力空气高效转换成推动航空飞机行进的反冲推力；同时，在临界压力空气未输入第二相向受迫对流换热复合管前，将其中的部分临界压力空气输入第一相向受迫对流换热复合管冷端外管的临界压力空气冷却区，让其重新液化、并储存起来，作为航空飞机应急状态情况使用与航空飞机下一次升降时使用。上述液态空气热力工质航空发动机设置在航空飞机主机翼下方，当航空飞机设定在现有机场直线跑道上升空、起飞时，液态空气热力工质航空发动机产生出巨大的水平推力，推动飞机快速行进起飞；当航空飞机设定随时随地垂直升降时，将航空飞机的主机翼设计制造成可以折转90度的形式，让主机翼连同液态空气热力工质航空发动机与主机体垂直，液态空气热力工质航空发动机产生巨大的垂直向上的反冲推力，让航空飞机克服重力平稳升空与降落。A process method for a liquid air thermal working medium aircraft engine. The method is to use liquid air as the thermal working medium of the heat engine, and allow the airborne liquid air to absorb the high-heat compressed air generated by a turbine high-pressure steam turbine driving a turbine-type normal-temperature air compressor. The heat in the liquid air is vaporized into high-pressure air, which is then used to drive the turbine high-pressure steam turbine; at the same time, the opposite forced convection heat exchange composite tube is used to reuse the low-temperature cold energy carried by the liquid air to convert the high heat generated by the turbine-type normal temperature air compressor. The compressed air is cooled into low-temperature compressed air, and then compressed into critical pressure air using a turbine-type low-temperature air compressor. Finally, the high-density critical pressure air is accelerated and discharged through the propeller propeller, and is efficiently converted into recoil thrust to promote aviation. The aircraft travels rapidly and re-liquefies part of its critical pressure air. During the rapid flight of the aircraft, it stops using the vaporization of liquid air to become high-pressure air to drive the turbine and high-pressure steam turbine, and instead uses the kinetic energy of the relative motion of the air to collect the relative motion of the air collected by the impeller. Kinetic energy drives the turbine normal-temperature air compressor, turbine low-temperature air compressor and propeller propeller to work; at the same time, a second opposite forced convection heat exchange composite tube is used to allow the high-heat compressed air generated by the turbine normal-temperature air compressor to mix with the turbine low-temperature air compressor. The air compressor re-compresses the low-temperature compressed air sucked in from the first phase forced convection heat exchange composite tube into critical pressure air, allowing the two to exchange heat; and finally, the high-density critical pressure air is efficiently converted into fuel to propel the aircraft forward. The recoil thrust; at the same time, before the critical pressure air is input into the second phase forced convection heat exchange composite tube, part of the critical pressure air is input into the critical pressure of the cold end outer tube of the first phase forced convection heat exchange composite tube. The air cooling area allows it to be re-liquefied and stored for use in emergency situations and for the next takeoff and landing of the aircraft. The above-mentioned liquid air thermal refrigerant aeroengine is installed under the main wing of the aircraft. When the aircraft is set to take off on the existing straight runway of the airport, the liquid air thermal refrigerant aeroengine generates huge horizontal thrust, pushing the aircraft quickly. Take off; when the aircraft is set to take off vertically at any time, the main wing of the aircraft is designed to be able to be folded 90 degrees, so that the main wing and the liquid air thermal refrigerant engine are perpendicular to the main body, and the liquid air thermal The refrigerant aviation engine generates huge vertical upward recoil thrust, allowing the aircraft to overcome gravity and smoothly lift off and land.

一种液态空气热力工质航空发动机的装置，它包括航空飞机主体、主机翼、尾机翼、起落架，还包括液态空气热力工质航空发动机主体设备、液态空气热力工质航空发动机附属设备；液态空气热力工质航空发动机主体设备设置在航空飞机主机翼下方，它包括主体设备壳体，主体设备前端开口仓，在主体设备前端开口仓内部上、下、左、右侧面设置有相对运动空气动能收集叶轮，在主体设备壳体外部前端设置有空气顺流百叶窗，在开口仓内设置有小型发电机，副机轴、主机轴，变速箱，在主体设备中部设置有涡轮式常温空气压缩机，进气管，电热室，涡轮高压汽轮机，涡轮式低温空气压缩机，螺旋桨推进器，反冲排气管，中压气管，高压气管；液态空气热力工质航空发动机附属设备设置在航空飞机主机翼内部，它包括第一相向受迫对流换热复合管，第二相向受迫对流换热复合管，蓄电池，液态空气储罐，节流阀，工质泵，小型抽气机；在第一相向受迫对流换热复合管内，设置有除湿仓，自动排水管，临界压力空气冷却仓，中压气管，高压液管，尾气管，高压气管；在第二相向受迫对流换热复合管内，设置有除湿仓，自动排水管，中压气管；在反冲排气管、涡轮式低温空气压缩机以及第一相向受迫对流换热复合管以及所有低温部件外壳，均设置保温层。相向受迫对流换热复合管由传热性能好的金属材料制成。在液态空气热力工质航空发动机主体设备与附属设备之间的部分中压气管、高压气管、高压液管之间的连通管中部设置电磁阀。A device for a liquid air thermal working medium aeroengine, which includes an aircraft main body, a main wing, a tail wing, and a landing gear. It also includes the main equipment of a liquid air thermal working medium aeroengine and the auxiliary equipment of a liquid air thermal working medium aeroengine; The main equipment of the liquid air thermal working medium aeroengine is arranged under the main wing of the aircraft. It includes the main equipment shell, the main equipment front-end opening compartment, and the upper, lower, left and right sides of the main equipment are provided with relative motion inside the front-end opening compartment. The air kinetic energy collection impeller is equipped with an air flow shutter at the front end of the outer shell of the main equipment. A small generator, auxiliary shaft, main engine shaft, and gearbox are installed in the open chamber. A turbine-type normal temperature air compressor is installed in the middle of the main equipment. machine, air intake pipe, electric heating chamber, turbine high-pressure steam turbine, turbine low-temperature air compressor, propeller propeller, recoil exhaust pipe, medium-pressure air pipe, high-pressure air pipe; liquid air thermal working medium aviation engine auxiliary equipment is set on the main engine of the aviation aircraft Inside the wing, it includes a first phase forced convection heat exchange composite tube, a second phase forced convection heat exchange composite tube, a battery, a liquid air storage tank, a throttle valve, a working fluid pump, and a small air extractor; in the first The opposing forced convection heat exchange composite tube is equipped with a dehumidification chamber, an automatic drainage pipe, a critical pressure air cooling chamber, a medium pressure gas pipe, a high-pressure liquid pipe, an exhaust pipe, and a high-pressure gas pipe; in the second phase forced convection heat exchange composite tube, It is equipped with a dehumidification chamber, an automatic drainage pipe, and a medium-pressure air pipe; the backwash exhaust pipe, the turbine low-temperature air compressor, the first forced convection heat exchange composite pipe, and the shells of all low-temperature components are all equipped with thermal insulation layers. Opposite forced convection heat exchange composite tubes are made of metal materials with good heat transfer properties. A solenoid valve is installed in the middle of the connecting pipe between some of the medium-pressure air pipes, high-pressure air pipes and high-pressure liquid pipes between the main equipment of the liquid air thermal working medium aircraft engine and the auxiliary equipment.

在航空飞机升空、起飞阶段，首先启动工质泵，从液态空气储罐内抽取液态空气、施加高压后将其泵入第一相向受迫对流换热复合管冷端的高压内管，让其从自然环境温度中吸热汽化为高压空气；然后，将其热端内管的高压空气输入主体设备中的电热室，再由蓄电池向电热室供电产生热量，让高压空气从中吸热升温、驱动涡轮高压汽轮机运转作功；同轴驱动涡轮式常温空气压缩机让其源源不断产生高热压缩空气，并输入第一相向受迫对流换热复合管热端外管，与其内管中的液态空气进行换热；在其热端除湿仓内，高热压缩空气中的水蒸汽在与内管换热时完全液化，后经自动排水管向外排出；干空气继续被内管进一步冷却，直至其温度达到设定温度；低温空气从第一相向受迫对流换热复合管冷端外管的设定位置流出，输入涡轮式低温空气压缩机，然后被进一步压缩成为临界压力状态；最后，临界压力空气与涡轮高压汽轮机尾气一道输入反冲排气管，由螺旋桨推进器加速外排，由此高效形成推动航空飞机行进的反冲推力。其中的部分临界压力空气在输入第二相向受迫对流换热复合管之前，输入第一相向受迫对流换热复合管冷端外管的临界压力空气冷却仓冷凝液化后，再经由节流阀输入液态空气储罐。During the take-off and take-off stages of an aviation aircraft, the working fluid pump is first started to extract liquid air from the liquid air storage tank, apply high pressure, and then pump it into the high-pressure inner tube at the cold end of the first phase forced convection heat exchange composite tube, allowing it to It absorbs heat from the natural environment temperature and vaporizes it into high-pressure air; then, the high-pressure air in the inner tube of the hot end is input into the electric heating chamber in the main equipment, and then the battery supplies power to the electric heating chamber to generate heat, allowing the high-pressure air to absorb heat from it to heat up and drive The turbine high-pressure steam turbine operates to work; the coaxially driven turbine-type normal temperature air compressor allows it to continuously generate high-heat compressed air, and inputs it into the hot-end outer tube of the first opposite forced convection heat exchange composite tube to interact with the liquid air in the inner tube. Heat exchange; in its hot end dehumidification chamber, the water vapor in the high-heat compressed air is completely liquefied when exchanging heat with the inner tube, and is then discharged outward through the automatic drainage pipe; the dry air continues to be further cooled by the inner tube until its temperature reaches Set the temperature; the low-temperature air flows out from the set position of the cold end outer tube of the first phase forced convection heat exchange composite tube, enters the turbine low-temperature air compressor, and is further compressed to a critical pressure state; finally, the critical pressure air and The exhaust gas of the turbine high-pressure turbine is input into the recoil exhaust pipe, and is accelerated and discharged by the propeller propeller, thereby efficiently forming the recoil thrust that propels the aircraft forward. Part of the critical pressure air is condensed and liquefied in the critical pressure air cooling chamber of the cold end outer tube of the first forced convection heat exchange composite tube before being input into the second phase forced convection heat exchange composite tube, and then passes through the throttle valve. Enter the liquid air tank.

在航空飞机升空、起飞达到设定航速快速飞行后，停止涡轮高压汽轮机运转，改由相对运动空气动能收集叶轮收集的动能同轴驱动涡轮式常温空气压缩机、涡轮式低温空气压缩机，小型发电机、螺旋桨推进器运转；涡轮式常温空气压缩机产生的高热压缩空气改为输入第二相向受迫对流换热复合管热端外管，与内管中的临界压力空气进行换热；常温空气中携带的水蒸汽在换热过程中被冷凝液化，经自动排水管外排；高热压缩空气初步冷却后，再输入第一相向受迫对流换热复合管热端外管，进一步冷却后，再输入涡轮式低温空气压缩机、将其压缩成为临界压力空气；其中的大部分临界压力空气输入第二相向受迫对流换热复合管冷端内管，与外管中的高热压缩空气换热后，经中压气管输入反冲排气管，再由螺旋桨推进器加速外排形成反冲推力、推动航空飞行行进；少部分临界压力空气输入第一相向受迫对流换热复合管冷端外管的临界空气冷却仓，待其冷凝液化后经由节流阀、流入液态空气储罐。在上述工艺流程中，由工质泵泵出的液态空气在第一相向受迫对流换热复合管内管与从第二相向对流换热复合管冷端外管排出的压缩空气换热，第一相向受迫对流换热复合管热端内管中的低温液态空气的温度由-196℃上升为-140.7℃的临界温度，经由设置在热端的高压液管回流输入节流阀，再度成为压力为常压、温度为-196℃的液态空气。After the aircraft takes off and reaches the set speed and flies quickly, the turbine high-pressure turbine stops running, and the kinetic energy collected by the relative motion air kinetic energy collection impeller coaxially drives the turbine normal temperature air compressor, turbine low temperature air compressor, small The generator and propeller are running; the high-heat compressed air generated by the turbine-type normal-temperature air compressor is instead input into the hot-end outer tube of the second phase forced convection heat exchange composite tube to exchange heat with the critical pressure air in the inner tube; normal temperature The water vapor carried in the air is condensed and liquefied during the heat exchange process, and is discharged through the automatic drainage pipe; after the high-heat compressed air is initially cooled, it is then input into the hot-end outer tube of the first opposite forced convection heat exchange composite tube. After further cooling, Then it is input into the turbine low-temperature air compressor to compress it into critical pressure air; most of the critical pressure air is input into the inner tube of the cold end of the second phase forced convection heat exchange composite tube to exchange heat with the high-heat compressed air in the outer tube. After that, it is input into the recoil exhaust pipe through the medium-pressure air pipe, and then accelerated by the propeller propeller to form a recoil thrust to promote the aviation flight; a small part of the critical pressure air is input into the cold end of the first phase forced convection heat exchange composite tube. The critical air cooling chamber of the tube waits for it to condense and liquefy, then flow into the liquid air storage tank through the throttle valve. In the above process flow, the liquid air pumped by the working fluid pump exchanges heat between the inner tube of the first phase forced convection heat exchange composite tube and the compressed air discharged from the cold end outer tube of the second phase phase forced convection heat exchange composite tube. The temperature of the low-temperature liquid air in the inner tube of the hot end of the opposite forced convection heat exchange composite tube rises from -196°C to the critical temperature of -140.7°C. It is returned to the throttle valve through the high-pressure liquid pipe set at the hot end, and the pressure becomes again Liquid air at normal pressure and temperature -196°C.

工质泵的泵液流量，由上述工艺过程中所需要的低温冷量确定。The pump liquid flow rate of the working fluid pump is determined by the low-temperature cooling capacity required in the above process.

小型抽气机负责及时将液态空气储罐内高于常压的空气抽走，由此确保罐内气压稳定为常压，罐内温度稳定保持在-196℃；同时采用多具第一相向受迫对流换热复合管，间断性地轮换将第一相向受迫对流换热复合管热端内管中的高热高压空气，调头转向流经另一具结冰的内管的方法，及时融解内管外壁上的结冰层。The small air extractor is responsible for promptly removing the air above normal pressure in the liquid air storage tank, thereby ensuring that the air pressure in the tank is stabilized at normal pressure and the temperature in the tank is maintained at -196°C; at the same time, multiple first phase receiving devices are used The forced convection heat exchange composite tube intermittently rotates the high-temperature and high-pressure air in the hot end inner tube of the first forced convection heat exchange composite tube to flow through the other frozen inner tube to melt the air in time. Ice layer on the outer wall of the tube.

在本发明中，所述同时采用多具第一相向受迫对流换热复合管，是指它可以是一具，也可以是两具，还可以是两具以上。In the present invention, the simultaneous use of multiple first opposing forced convection heat exchange composite tubes means that it can be one tube, two tubes, or more than two tubes.

本发明采用液态空气为热力发动机的热力工质，让机载液态空气吸收由涡轮高压汽轮机所驱动的涡轮式常温空气压缩机产生的高热压缩空气中的热量汽化成高压空气，再利用其去驱动涡轮高压汽轮机运转作功，推动航空飞机升空与起飞；然后，利用航空飞机快速航行中所产生的相对运动空气动能高效形成反冲推力、去推动航空飞机快速航行，同时持续定量生产液态空气。从而，全面实现航空飞机从起飞到降落、全航程“零能耗”，以及载重量巨大、拥有无限航程诸项卓越技术效果。The invention uses liquid air as the thermal working fluid of the heat engine, allowing the airborne liquid air to absorb the heat in the high-heat compressed air generated by the turbine-type normal-temperature air compressor driven by the turbine-high-pressure steam turbine, vaporize it into high-pressure air, and then use it to drive The turbine high-pressure steam turbine operates to propel the aircraft into the air and take off; then, the relative motion of the aerodynamic energy generated by the aircraft's fast flight is used to efficiently form recoil thrust to propel the aircraft into fast flight while continuously producing liquid air in a quantitative manner. As a result, the aircraft can fully achieve "zero energy consumption" from takeoff to landing and the entire flight, as well as various outstanding technical effects such as huge load capacity and unlimited range.

附图说明Description of drawings

下面结合附图对本发明做详细描述。The present invention will be described in detail below with reference to the accompanying drawings.

图1是液态空气热力工质航空发动机主体设备构造示意图。Figure 1 is a schematic structural diagram of the main equipment of a liquid air thermal working medium aeroengine.

图2是液态空气热力工质航空发动机附属设备构造示意图。Figure 2 is a schematic structural diagram of the liquid air thermal working fluid aircraft engine auxiliary equipment.

图3是航空飞机水平航行时的液态空气热力工质航空发动机装配位置示意图。Figure 3 is a schematic diagram of the assembly position of the liquid air thermal working medium aeroengine when the aircraft is flying horizontally.

图4是航空飞机垂直升降时的液态空气热力工质航空发动机装配位置示意图。Figure 4 is a schematic diagram of the assembly position of the liquid air thermal working medium aeroengine when the aircraft takes off vertically.

具体实施方式Detailed ways

参看图1、图2、图3、与图4，本发明所述的液态空气热力工质航空发动机设备装置采用液态空气为热力发动机的热力工质，让机载液态空气吸收由涡轮高压汽轮机所驱动的涡轮式常温空气压缩机产生的高热压缩空气中的热量汽化成高压空气，再利用其去驱动涡轮高压汽轮机运转作功，推动航空飞机升空与起飞；然后，利用航空飞机快速航行中所产生的相对运动空气动能高效形成反冲推力、去推动航空飞机快速航行，同时持续定量生产液态空气与电能。Referring to Figures 1, 2, 3, and 4, the liquid air thermal working medium aircraft engine equipment device of the present invention uses liquid air as the thermal working medium of the heat engine, allowing the airborne liquid air to absorb the heat generated by the turbine high-pressure steam turbine. The heat in the high-heat compressed air generated by the driven turbine-type normal-temperature air compressor is vaporized into high-pressure air, which is then used to drive the turbine-high-pressure steam turbine to operate and propel the aircraft into the air and take off; The generated relative motion aerodynamic energy efficiently forms recoil thrust to propel the aircraft into fast navigation, while continuously producing liquid air and electrical energy in a quantitative manner.

本发明所述的液态空气热力工质航空发动机的工艺方法的特点是采用液态空气为热力发动机的热力工质，让机载液态空气吸收由涡轮高压汽轮机驱动涡轮式常温空气压缩机所产生的高热压缩空气中的热量、汽化成高压空气，再利用其去驱动涡轮高压汽轮机运转；同时采用相向受迫对流换热复合管重复利用液态空气所携带的低温冷量，将涡轮式常温空气压缩机产生的高热压缩空气冷却为低温压缩空气，然后再利用涡轮式低温空气压缩机将其压缩为临界压力空气；最后将高密度的临界压力空气经螺旋桨推进器加速外排、高效转换成反冲推力，推动航空飞机快速行进，同时将其部分临界压力空气重新液化；在航空飞机快速航行中，停止利用液态空气汽化成为高压空气驱动涡轮高压汽轮机运转，改为由相对运动空气动能收集叶轮所收集的相对运动空气动能驱动涡轮式常温空气压缩机、涡轮式低温空气压缩机与螺旋桨推进器工作；同时采用第二相向受迫对流换热复合管，让涡轮式常温空气压缩机产生的高热压缩空气与涡轮式低温空气压缩机将从第一相向受迫对流换热复合管内吸入的低温压缩空气再次压缩成为临界压力空气，让两者在其中换热；最后将高密度的临界压力空气高效转换成推动航空飞机行进的反冲推力；同时，在临界压力空气未输入第二相向受迫对流换热复合管前，将其中的部分临界压力空气输入第一相向受迫对流换热复合管冷端外管的临界压力空气冷却区，让其重新液化、并储存起来，作为航空飞机应急状态情况使用与航空飞机下一次升降时使用。上述液态空气热力工质航空发动机设置在航空飞机主机翼下方，当航空飞机设定在现有机场直线跑道上升空、起飞时，液态空气热力工质航空发动机产生出巨大的水平推力，推动飞机快速行进起飞；当航空飞机设定随时随地垂直升降时，将航空飞机的主机翼设计制造成可以折转90度的形式，让主机翼连同液态空气热力工质航空发动机与主机体垂直，液态空气热力工质航空发动机产生巨大的垂直向上的反冲推力，让航空飞机克服重力随时随地实现平稳升空与降落。The characteristic of the process method of the liquid air thermal working medium aeroengine of the present invention is to use liquid air as the thermal working medium of the heat engine, so that the airborne liquid air absorbs the high heat generated by the turbine high-pressure steam turbine driving the turbine-type normal temperature air compressor. The heat in the compressed air is vaporized into high-pressure air, which is then used to drive the turbine high-pressure turbine. At the same time, the opposite forced convection heat exchange composite tube is used to reuse the low-temperature cold energy carried by the liquid air to generate the energy generated by the turbine-type normal temperature air compressor. The high-heat compressed air is cooled into low-temperature compressed air, and then compressed into critical pressure air using a turbine-type low-temperature air compressor; finally, the high-density critical pressure air is accelerated and discharged through the propeller propeller, and is efficiently converted into recoil thrust. Promote the rapid travel of the aircraft and re-liquefy part of its critical pressure air; during the rapid flight of the aircraft, the liquid air vaporization is stopped to become high-pressure air to drive the turbine high-pressure turbine operation, and the relative motion of the air kinetic energy collected by the impeller is replaced. The kinetic energy of moving air drives the turbine normal-temperature air compressor, turbine low-temperature air compressor and propeller propeller to work; at the same time, a second opposite forced convection heat exchange composite tube is used to allow the high-heat compressed air generated by the turbine normal-temperature air compressor to interact with the turbine The low-temperature air compressor will re-compress the low-temperature compressed air sucked into the first phase forced convection heat exchange composite tube into critical pressure air, allowing the two to exchange heat; finally, the high-density critical pressure air will be efficiently converted into propellant air. The recoil thrust of the aircraft traveling; at the same time, before the critical pressure air is input into the second phase forced convection heat exchange composite tube, part of the critical pressure air is input into the cold end outer tube of the first phase forced convection heat exchange composite tube. The critical pressure air cooling zone allows it to be re-liquefied and stored for use in emergency situations and for the next takeoff and landing of the aircraft. The above-mentioned liquid air thermal refrigerant aeroengine is installed under the main wing of the aircraft. When the aircraft is set to take off on the existing straight runway of the airport, the liquid air thermal refrigerant aeroengine generates huge horizontal thrust, pushing the aircraft quickly. Take off; when the aircraft is set to take off vertically at any time, the main wing of the aircraft is designed to be able to be folded 90 degrees, so that the main wing and the liquid air thermal refrigerant engine are perpendicular to the main body, and the liquid air thermal The refrigerant aviation engine generates huge vertical upward recoil thrust, allowing aircraft to overcome gravity and achieve smooth takeoff and landing anytime and anywhere.

本发明所述的液态空气热力工质航空发动机设备装置利用上述方法加以实施；如图1、图2、图3与图4所示，一种液态空气热力工质航空发动机设备装置包括航空飞机主体1、主机翼2、尾机翼3、起落架4，还包括液态空气热力工质航空发动机主体设备5、液态空气热力工质航空发动机附属设备6；液态空气热力工质航空发动机主体设备5设置在航空飞机主机翼2下方，它包括主体设备壳体7，主体设备前端开口仓8，在主体设备前端开口仓8内部上、下、左、右侧面设置有相对运动空气动能收集叶轮9，在主体设备壳体7外部前端设置有空气顺流百叶窗10，在开口仓8内设置有小型发电机11，副机轴12、主机轴13，变速箱14，在主体设备5中部设置有涡轮式常温空气压缩机15，进气口16，电热室17，涡轮高压汽轮机18，涡轮式低温空气压缩机19，螺旋桨推进器20，反冲排气管21，中压气管31、33、34、35，尾气管36，高压气管32；液态空气热力工质航空发动机附属设备6设置在航空飞机主机翼2内部，它包括第一相向受迫对流换热复合管22，第二相向受迫对流换热复合管23，蓄电池24，液态空气储罐25，节流阀26，工质泵27，小型抽气机28；在第一相向受迫对流换热复合管22内，设置有除湿仓29，自动排水管30，临界压力空气冷却仓31。中压气管42、43、44、中压液管38、39、高压液管37、41、高压气管40；在第二相向受迫对流换热复合管23 内，设置有除湿仓29，自动排水管30，中压气管45、46、47、48；在反冲排气管21、涡轮式低温空气压缩机19以及第一相向受迫对流换热复合管22以及所有低温部件外壳，均设置保温层，相向受迫对流换热复合管由传热性能好的金属材料制成。在液态空气热力工质航空发动机主体设备与附属设备之间的部分中压气管、高压气管、高压液管之间的连通管中部设置电磁阀。The liquid air thermal working medium aircraft engine equipment device of the present invention is implemented using the above method; as shown in Figures 1, 2, 3 and 4, a liquid air thermal working medium aircraft engine equipment device includes an aircraft main body 1. Main wing 2, tail wing 3, landing gear 4, also includes the main equipment of the liquid air thermal working medium aeroengine 5, the liquid air thermal working medium aeroengine auxiliary equipment 6; the main equipment 5 of the liquid air thermal working medium aeroengine is set Under the main wing 2 of the aviation aircraft, it includes a main equipment shell 7, a main equipment front-end open compartment 8, and relative motion aerodynamic energy collecting impellers 9 are provided on the upper, lower, left and right sides of the main equipment front-end open compartment 8. An air flow louver 10 is provided at the outer front end of the main equipment casing 7 . A small generator 11 , an auxiliary shaft 12 , a main shaft 13 and a gearbox 14 are provided in the open chamber 8 . A turbine type is provided in the middle of the main equipment 5 Normal temperature air compressor 15, air inlet 16, electric heating chamber 17, turbo high pressure steam turbine 18, turbine low temperature air compressor 19, propeller propeller 20, recoil exhaust pipe 21, medium

pressure air pipes

31, 33, 34, 35 , exhaust pipe 36, high-pressure air pipe 32; liquid air thermal working medium aviation engine auxiliary equipment 6 is arranged inside the main wing 2 of the aviation aircraft, which includes a first phase forced convection heat exchange composite pipe 22, a second phase phase forced convection heat exchange composite tube 22 Composite pipe 23, battery 24, liquid air storage tank 25, throttle valve 26, working medium pump 27, small air extractor 28; in the first phase forced convection heat exchange composite pipe 22, a dehumidification chamber 29 is provided. Drainage pipe 30, critical pressure air cooling chamber 31. Medium-

pressure air pipes

42, 43, 44, medium-

pressure liquid pipes

38, 39, high-

pressure liquid pipes

37, 41, and high-pressure air pipes 40; in the second opposite forced convection heat exchange composite pipe 23, a dehumidification chamber 29 is provided for automatic drainage. Pipe 30, medium

pressure air pipes

45, 46, 47, 48; thermal insulation is provided in the recoil exhaust pipe 21, the turbine low-temperature air compressor 19 and the first forced convection heat exchange composite pipe 22 as well as the shells of all low-temperature components. Layer, opposite forced convection heat exchange composite tubes are made of metal materials with good heat transfer performance. A solenoid valve is installed in the middle of the connecting pipe between some of the medium-pressure air pipes, high-pressure air pipes and high-pressure liquid pipes between the main equipment of the liquid air thermal working medium aircraft engine and the auxiliary equipment.

在航空飞机升空、起飞阶段，首先启动工质泵27，从液态空气储罐25内抽取液态空气、施加高压后将其泵入第一相向受迫对流换热复合管22冷端的高压内管37，让其从自然环境温度中吸热汽化为高压空气；然后，将其热端内管42的高压空气经由高压气管32输入主体设备5中的电热室17，再经由蓄电池24向电热室17供电产生热量，让高压空气从中吸热升温、驱动涡轮高压汽轮机18运转作功；同轴驱动涡轮式常温空气压缩机15让其源源不断产生高热压缩空气，经由中压气管31输入第一相向受迫对流换热复合管22热端外管42，与其内管40中的液态空气进行换热；在热端除湿仓29内，高热压缩空气中的水蒸汽在与内管40换热时被完全液化，后经自动排水管30向外排出；干空气继续被低温内管进一步冷却，直至温度达到设定温度；低温空气从第一相向受迫对流换热复合管22冷端外管44冷端的设定位置流出，经由中压气管33输入涡轮式低温空气压缩机19，然后被进一步压缩成为临界压力状态；最后，临界压力空气经中压气管34、35与涡轮高压汽轮机18尾气经尾气管36一道输入反冲排气管21，由螺旋桨推进器20加速外排，由此高效形成推动航空飞机行进的反冲推力。其中的部分临界压力空气在输入第二相向受迫对流换热复合管23之前，经中压气管34、43、输入第一相向受迫对流换热复合管22冷端的临界压力空气冷却仓31冷凝液化后，再经由节流阀26输入液态空气储罐25。During the take-off and take-off stages of the aircraft, the working medium pump 27 is first started to extract liquid air from the liquid air storage tank 25, apply high pressure, and then pump it into the high-pressure inner tube at the cold end of the first forced convection heat exchange composite tube 22. 37, let it absorb heat from the natural environment temperature and vaporize into high-pressure air; then, input the high-pressure air from the inner tube 42 of the hot end into the electric heating chamber 17 in the main equipment 5 through the high-pressure air pipe 32, and then to the electric heating chamber 17 via the battery 24. The power supply generates heat, allowing the high-pressure air to absorb heat and heat up, driving the turbine high-pressure steam turbine 18 to operate; the coaxially driven turbine-type normal-temperature air compressor 15 allows it to continuously generate high-heat compressed air, which is input to the first phase receiving air through the medium-pressure air pipe 31 The forced convection heat exchange composite pipe 22 hot-end outer pipe 42 exchanges heat with the liquid air in the inner pipe 40; in the hot-end dehumidification chamber 29, the water vapor in the high-heat compressed air is completely eliminated when exchanging heat with the inner pipe 40. It is liquefied and then discharged outward through the automatic drain pipe 30; the dry air continues to be further cooled by the low-temperature inner tube until the temperature reaches the set temperature; the low-temperature air is forced convection heat exchange composite tube 22 cold end outer tube 44 cold end from the first phase It flows out at the set position, is input to the turbine low-temperature air compressor 19 through the medium-pressure air pipe 33, and is further compressed to a critical pressure state; finally, the critical pressure air passes through the medium-

pressure air pipes

34, 35 and the exhaust gas of the turbine high-pressure turbine 18 passes through the exhaust pipe 36 One input is the recoil exhaust pipe 21, and the propeller thruster 20 accelerates the exhaust, thereby efficiently forming a recoil thrust to propel the aircraft forward. Part of the critical pressure air is condensed through the intermediate

pressure air pipes

34 and 43 and the critical pressure air cooling chamber 31 at the cold end of the first opposing forced convection heat exchange composite tube 22 before being input into the second opposite forced convection heat exchange composite tube 23. After liquefaction, the liquid air is then input into the storage tank 25 via the throttle valve 26 .

在航空飞机升空、起飞达到设定航速快速飞行后，停止涡轮高压汽轮机18运转，改由相对运动空气动能收集叶轮9收集的动能同轴驱动涡轮式常温空气压缩机15、涡轮式低温空气压缩机19，小型发电机11、螺旋桨推进器20运转；涡轮式常温空气压缩机15产生的高热压缩空气改为经中压气管31首先输入第二相向受迫对流换热复合管23热端外管48，与内管47中的临界压力空气进行换热；常温空气中携带的水蒸气在换热过程中被冷凝液化，经自动排水管30外排；高热压缩空气初步冷却后，再将其从中压气管46输入第一相向对流换热复合管22热端外管42，进一步冷却后，经中压气管44、33再输入涡轮式低温空气压缩机19、将其压缩成为临界压力空气；其中的大部分临界压力空气经中压气管34输入第二相向受迫对流换热复合管23冷端内管45，与外管48中的高热压缩空气换热后，经中压气管47、35输入反冲排气管21，再由螺旋桨推进器20加速外排形成反冲推力、推动航空飞机行进；少部分临界压力空气经中压气管34进入第一相向受迫对流换热复合管22冷端外管43，输入临界空气冷却仓31，待其冷凝液化后经由节流阀26节流、流入液态空气储罐25。在上述工艺流程中，由工质泵27泵出的液态空气在第一相向受迫对流换热复合管22内管37与从第二相向对流换热复合管23冷端外管46排出的压缩空气换热，第一相向受迫对流换热复合管22热端内管41中的低温液态空气的温度由-196℃上升为-140.7℃的临界温度，经由设置在冷端的高压液管39回流输入节流阀26降压，再度成为压力为常压、温度为-196℃的液态空气。After the aircraft takes off and reaches the set speed and flies quickly, the operation of the turbine high-pressure turbine 18 is stopped, and the kinetic energy collected by the relative motion air kinetic energy collection impeller 9 is coaxially driven to drive the turbine-type normal temperature air compressor 15. Turbine-type low-temperature air compression The machine 19, the small generator 11, and the propeller 20 are running; the high-heat compressed air generated by the turbine normal-temperature air compressor 15 is first input into the second opposite forced convection heat exchange composite pipe 23 hot end outer pipe through the medium-pressure air pipe 31 48, perform heat exchange with the critical pressure air in the inner tube 47; the water vapor carried in the normal temperature air is condensed and liquefied during the heat exchange process, and is discharged through the automatic drainage pipe 30; after the high-heat compressed air is initially cooled, it is The pressure air pipe 46 is input into the hot end outer pipe 42 of the first counter-convection heat exchange composite pipe 22. After further cooling, it is input into the turbine low-temperature air compressor 19 through the medium

pressure air pipes

44 and 33 to compress it into critical pressure air; where Most of the critical pressure air is input into the cold-end inner tube 45 of the second opposite forced convection heat exchange composite tube 23 through the medium-pressure air pipe 34. After exchanging heat with the high-heat compressed air in the outer tube 48, it is input back through the medium-

pressure air pipes

47 and 35. It rushes into the exhaust pipe 21, and then is accelerated by the propeller propeller 20 to form a recoil thrust to propel the aircraft forward; a small part of the critical pressure air enters the cold end of the first opposite forced convection heat exchange composite pipe 22 through the medium pressure air pipe 34. Pipe 43 enters the critical air cooling chamber 31. After it is condensed and liquefied, it is throttled through the throttle valve 26 and flows into the liquid air storage tank 25. In the above process flow, the liquid air pumped by the working fluid pump 27 is compressed in the inner tube 37 of the first forced convection heat exchange composite tube 22 and the cold end outer tube 46 of the second opposite convection heat exchange composite tube 23. During air heat exchange, the temperature of the low-temperature liquid air in the inner tube 41 of the hot end of the first forced convection heat exchange composite tube 22 rises from -196°C to a critical temperature of -140.7°C, and then flows back through the high-pressure liquid pipe 39 provided at the cold end. The input throttle valve 26 reduces the pressure and becomes liquid air with a pressure of normal pressure and a temperature of -196°C again.

工质泵27的泵液流量，由上述工艺过程中所需要的低温冷量确定。The pump liquid flow rate of the working medium pump 27 is determined by the low-temperature cooling capacity required in the above process.

小型抽气机28负责及时将液态空气储罐25内高于常压的空气抽走，由此确保罐内气压稳定为常压，罐内温度稳定保持在-196℃；同时采用多具第一相向受迫对流换热复合管22，间断性地轮换将第一相向受迫对流换热复合管22热端内管40中的高热高压空气，调头转向流经另一具结冰的内管的方法，及时融解内管40外壁上的结冰层。The small air extractor 28 is responsible for promptly removing the air above normal pressure in the liquid air storage tank 25, thereby ensuring that the air pressure in the tank is stabilized at normal pressure and the temperature in the tank is stably maintained at -196°C; at the same time, multiple first tools are used The opposing forced convection heat exchange composite tube 22 intermittently rotates the high-heat and high-pressure air in the hot-end inner tube 40 of the first opposing forced convection heat exchange composite tube 22 to turn around and flow through the other frozen inner tube. Method, the ice layer on the outer wall of the inner tube 40 is melted in time.

在本发明中，所述同时采用多具第一相向受迫对流换热复合管22，是指它可以是一具，也可以是两具，还可以是两具以上。In the present invention, the simultaneous use of multiple first opposing forced convection heat exchange composite tubes 22 means that it can be one, two, or more than two.

参看图1、图2、图3与图4，本发明所述一种液态空气热力工质航空发动机设备装置的使用操作程序如下：Referring to Figures 1, 2, 3 and 4, the operating procedures for the liquid air thermal working medium aeroengine equipment device of the present invention are as follows:

一、航空飞机在现有机场直线跑道上实行升降的操作程序：1. Operational procedures for aircraft taking off and landing on existing airport straight runways:

1、起飞前，向停放在机场上的航空飞机主机翼2内的液态空气储罐25充注液态空气，同时向其中的蓄电池24充电。1. Before taking off, fill the liquid air storage tank 25 in the main wing 2 of the aircraft parked at the airport with liquid air, and at the same time charge the battery 24 therein.

2、关闭设置在第一相向受迫对流换热复合管22热端内管41与冷端外管39之间连通管中部的电磁阀，关闭第二相向受迫对流换热复合管23热端外管48与涡轮常温空气压缩机15的中压气管31之间的连通管中部的电磁阀。2. Close the solenoid valve located in the middle of the connecting pipe between the hot end inner tube 41 and the cold end outer tube 39 of the first opposing forced convection heat exchange composite tube 22, and close the hot end of the second opposing forced convection heat exchange composite tube 23. A solenoid valve in the middle of the communication pipe between the outer pipe 48 and the medium-pressure air pipe 31 of the turbine normal-temperature air compressor 15.

3、同时打开设置在第一相向受迫对流换热复合管22热端内管40与电热室17高压气管32之间的电磁阀，打开设置在第一相向受迫对流换热复合管22热端外管42与涡轮式常温空气压缩机15的中压气管31之间的连通管中部的电磁阀。3. At the same time, open the solenoid valve disposed between the hot end inner tube 40 of the first opposing forced convection heat exchange composite tube 22 and the high-pressure gas pipe 32 of the electric heating chamber 17, and open the heat exchanger disposed between the first opposing forced convection heat exchange composite tube 22. A solenoid valve in the middle of the communication pipe between the end outer pipe 42 and the medium-pressure air pipe 31 of the turbine-type normal temperature air compressor 15.

4、启动工质泵27，将液态空气储罐24内的液态空气施以高压，从冷端泵入第一相向受迫对流换热复合管22内管37。4. Start the working fluid pump 27, apply high pressure to the liquid air in the liquid air storage tank 24, and pump it from the cold end into the inner tube 37 of the first phase forced convection heat exchange composite tube 22.

5、在第一相向受迫对流换热复合管22内管37中的液态空气从常温环境吸热汽化后，让其经热端内管42、高压输气管32输入液态空气热力工质航空发动机主体设备5中的电热室17；由蓄电池24向电热室17内供电，加热输入的高压空气。5. After the liquid air in the inner tube 37 of the first opposite forced convection heat exchange composite tube 22 absorbs heat from the normal temperature environment and vaporizes, it is input into the thermal working medium aviation engine through the hot end inner tube 42 and the high-pressure gas transmission pipe 32 The electric heating chamber 17 in the main equipment 5 supplies power to the electric heating chamber 17 from the battery 24 to heat the input high-pressure air.

6、已经在电热室17吸热升温的高压空气驱动涡轮高压汽轮机18运转，同轴驱动涡轮式常温空气压缩机15运转、并从进气口16吸入自然常温空气，将其压缩成高热压缩空气。汽轮机尾气经尾气管36输入反冲气管21，经螺旋桨推进器20加速外排。6. The high-pressure air that has absorbed heat and heated up in the electric heating chamber 17 drives the turbine high-pressure steam turbine 18 to operate, coaxially drives the turbine-type normal-temperature air compressor 15 to operate, sucks natural normal-temperature air from the air inlet 16, and compresses it into high-heat compressed air. . The turbine exhaust gas is input into the recoil air pipe 21 through the exhaust pipe 36, and is accelerated by the propeller propeller 20 for discharge.

7、涡轮式常温空气压缩机15产生的高热压缩空气经中压气管31输入第一相向受迫对流换热复合管22热端外管42，与内管40中的低温液态空气进行热量交换。高热压缩空气中的水蒸汽，在除湿仓29内冷凝液化、经自动排水管30排出。7. The high-heat compressed air generated by the turbine normal-temperature air compressor 15 is input into the hot end outer tube 42 of the first forced convection heat exchange composite tube 22 through the medium-pressure air pipe 31, and exchanges heat with the low-temperature liquid air in the inner tube 40. The water vapor in the high-heat compressed air is condensed and liquefied in the dehumidification chamber 29 and discharged through the automatic drain pipe 30 .

8、高热压缩空气在第一相向受迫对流换热复合管22冷端，冷却成为低温压缩空气，在设定位置经中压气管44、33输入涡轮式低温空气压缩机19。涡轮式低温空气压缩机19在涡轮高压汽轮机18的驱动下，将输入的低温压缩空气进一步压缩成为临界压力空气。8. The high-heat compressed air is cooled into low-temperature compressed air at the cold end of the first opposite forced convection heat exchange composite pipe 22, and is input into the turbine-type low-temperature air compressor 19 through the medium-

pressure air pipes

44 and 33 at the set position. Driven by the turbine high-pressure steam turbine 18, the turbine low-temperature air compressor 19 further compresses the input low-temperature compressed air into critical pressure air.

9、临界压力空气经中压气管34、35大部分输入反冲排气管21，螺旋桨推进器20在涡轮高压汽轮机18驱动下将反冲排气管21内的临界压力空气加速外排，由此形成反冲推力、推动航天飞机在机场跑道上快速行进。少部分临界压力空气经中压气管34、43输入第一相向受迫对流换热复合管22冷端的临界压力空气冷却仓31，液化后，经节流阀26流入液态空气储罐25。9. Most of the critical pressure air is input into the recoil exhaust pipe 21 through the medium

pressure air pipes

34 and 35. The propeller propeller 20 is driven by the turbine high-pressure turbine 18 to accelerate the critical pressure air in the recoil exhaust pipe 21 and discharge it. This creates a recoil thrust that propels the space shuttle forward quickly on the airport runway. A small part of the critical pressure air is input into the critical pressure air cooling chamber 31 at the cold end of the first forced convection heat exchange composite tube 22 through the medium

pressure air pipes

34 and 43. After liquefaction, it flows into the liquid air storage tank 25 through the throttle valve 26.

10、航空飞机在跑道上快速行进中，其主机翼2产生升力，航空飞机实行升空、起飞。10. When the aircraft is traveling rapidly on the runway, its main wing 2 generates lift, and the aircraft lifts off and takes off.

11、在航空飞机快速行进过程中，液态空气热力工质航空发动机主体设备5中的相对运动空气动能收集叶轮9产生的大量相对运动空气动能，经副机轴12、变速箱14驱动主机轴13运转。停止将高压空气输入电热室17、停止蓄电池24向电热室17供电，停止涡轮高压汽轮机18运转工作，改由相对运动空气动能驱动涡轮式常温空气压缩机15、涡轮式低温空气压缩机19与螺旋桨推进器20运转工作。11. During the rapid travel of an aircraft, the relative motion aerodynamic energy in the main equipment 5 of the liquid air thermal working medium aeroengine collects a large amount of relative motion aerodynamic energy generated by the impeller 9, and drives the main engine shaft 13 through the auxiliary shaft 12 and the gearbox 14. operation. Stop inputting high-pressure air into the electric heating chamber 17, stop the battery 24 from supplying power to the electric heating chamber 17, stop the operation of the turbine high-pressure steam turbine 18, and instead use the relative motion air kinetic energy to drive the turbine normal-temperature air compressor 15, the turbine low-temperature air compressor 19 and the propeller The propeller 20 operates.

12、关闭设置在第一相向受迫对流换热复合管22热端内管40与电热室17的高压气管32之间的连通管中部的电磁阀，关闭设置在第一相向受迫对流换热复合管22热端外管42与涡轮式常温空气压缩机15的中压气管31之间的连通管中部设置的电磁阀。12. Close the solenoid valve arranged in the middle of the connecting pipe between the hot end inner tube 40 of the first opposite forced convection heat exchange composite tube 22 and the high-pressure air pipe 32 of the electric heating chamber 17, and close the solenoid valve arranged in the first opposite forced convection heat exchanger. A solenoid valve is provided in the middle of the communication pipe between the hot-end outer pipe 42 of the composite pipe 22 and the medium-pressure air pipe 31 of the turbine normal-temperature air compressor 15 .

13、同时打开设置在第一相向受迫对流换热复合管22热端内管41与冷端外管39之间的连通管中部的电磁阀，打开设置在第一相向受迫对流换热复合管22热端外管42与第二相向受迫对流换热复合管 23冷端外管46之间连通管中部的电磁阀。13. At the same time, open the solenoid valve located in the middle of the connecting pipe between the hot end inner tube 41 and the cold end outer tube 39 of the first opposing forced convection heat exchange composite tube 22, and open the solenoid valve located in the first opposing forced convection heat exchange composite tube. The solenoid valve in the middle of the tube is connected between the hot end outer tube 42 of the tube 22 and the cold end outer tube 46 of the second opposing forced convection heat exchange composite tube 23.

14、打开设置在第二相向受迫对流换热复合管23热端外管48与涡轮式常温空气压缩机15中压气管31之间的连通管中部的电磁阀。14. Open the solenoid valve located in the middle of the communication pipe between the hot-end outer pipe 48 of the second opposing forced convection heat exchange composite pipe 23 and the medium-pressure air pipe 31 of the turbine normal-temperature air compressor 15 .

15、涡轮式常温空气压缩机15产生的高热压缩空气通过中压气管31输入第二相向受迫对流换热复合管22热端外管48，与内管45中的由涡轮式低温空气压缩机19产生的临界压力空气进行换热。第二相向受迫对流换热复合管23热端内管47中的临界压力空气经中压气管35输入反冲排气管21，再由螺旋桨推进器20加速外排，形成反冲推力、推动航空飞机行进。15. The high-heat compressed air generated by the turbine normal-temperature air compressor 15 is input into the hot-end outer tube 48 of the second opposite forced convection heat exchange composite tube 22 through the medium-pressure air pipe 31, and is connected to the hot-end outer tube 48 of the turbine-type low-temperature air compressor in the inner tube 45. 19 generates critical pressure air for heat exchange. The critical pressure air in the inner tube 47 of the hot end of the second opposite forced convection heat exchange composite tube 23 is input into the recoil exhaust pipe 21 through the medium pressure air pipe 35, and then is accelerated and discharged by the propeller propeller 20 to form recoil thrust and push. Aviation plane travels.

16、涡轮式常温空气压缩机15产生的高热压缩空气中的水蒸汽在第二相向受迫对流换热复合管23热端的除湿仓29遇冷液化，经自动排水管30排出。其中干冷压缩空气经中压气管46输入第一相向受迫对流换热复合管22热端外管42，经与内管41中的临界状况低温液态空气换热，成为低温压缩空气；在设定位置经中压气管44输入涡轮式低温空气压缩机19，将其进一步压缩成为临界压力空气。大部分临界压力空气经中压气管34输入第二相向受迫对流换热复合管23内管45。少部分临界压力空气经中压气管34输入第一相向受迫对流换热复合管22冷端外管43，输入临界压力空气冷却仓31液化，液化后经节流阀26流入液态空气储罐25。16. The water vapor in the high-heat compressed air generated by the turbine normal-temperature air compressor 15 is cooled and liquefied in the dehumidification chamber 29 at the hot end of the second forced convection heat exchange composite pipe 23, and is discharged through the automatic drain pipe 30. The dry-cooled compressed air is input into the hot-end outer tube 42 of the first forced convection heat exchange composite tube 22 through the medium-pressure air pipe 46, and becomes low-temperature compressed air after exchanging heat with the critical low-temperature liquid air in the inner tube 41; The position is input to the turbine low-temperature air compressor 19 through the medium-pressure air pipe 44, which further compresses it into critical pressure air. Most of the critical pressure air is input into the inner tube 45 of the second opposite forced convection heat exchange composite tube 23 through the medium pressure air tube 34 . A small part of the critical pressure air is input into the cold end outer tube 43 of the first forced convection heat exchange composite tube 22 through the medium pressure air pipe 34, and is input into the critical pressure air cooling warehouse 31 to be liquefied. After liquefaction, it flows into the liquid air storage tank 25 through the throttle valve 26. .

17、小型发电机11在相对运动空气动能驱动下发电，发出的电力，一部分供给航空飞机主机体1内电器，一部分输入蓄电池24储存。17. The small generator 11 generates electricity driven by the kinetic energy of the relative motion of the air. Part of the electricity generated is supplied to the electrical appliances in the main body 1 of the aircraft, and part is input to the battery 24 for storage.

18、返航时，停止液态空气热力工质航空发动机主体设备5中的主机轴13对涡轮常温空气压缩机15、涡轮低温空气压缩机19与螺旋桨推进器20的驱动，依靠起落架4中的轮胎与机场跑道地面之间的摩擦力、克服航空飞机惯性动能，让航空飞机停止行进，实现安全平稳降落。18. When returning, stop the main engine shaft 13 in the main equipment 5 of the liquid air thermal refrigerant aeroengine from driving the turbine normal temperature air compressor 15, turbine cryogenic air compressor 19 and propeller propeller 20, and rely on the tires in the landing gear 4 The friction with the airport runway ground overcomes the inertial kinetic energy of the aircraft, allowing the aircraft to stop and achieve a safe and smooth landing.

二、航空飞机在停机坪实行垂直升降的操作程序：2. Operation procedures for vertical takeoff and landing of aviation aircraft on the apron:

1、将停机坪上停放的航空飞机的主机翼2，由水平方向调整为垂直方向，让在主机翼2下方设置的液态空气热力工质航空发动机主体设备5的开口仓8朝上，其反冲排气管21朝下。1. Adjust the main wing 2 of the aircraft parked on the apron from the horizontal direction to the vertical direction, so that the opening chamber 8 of the main equipment 5 of the liquid air thermal working medium aeroengine 5 set under the main wing 2 faces upward, and its opposite direction. Flush the exhaust pipe 21 downward.

2、关闭设置在第一相向受迫对流换热复合管22热端内管41与冷端外管39之间连通管中部的电磁阀，关闭第二相向受迫对流换热复合管23热端外管48与涡轮式常温空气压缩机15的中压气管31之间的连通管中部的电磁阀。2. Close the solenoid valve located in the middle of the connecting pipe between the hot end inner tube 41 and the cold end outer tube 39 of the first opposing forced convection heat exchange composite tube 22, and close the hot end of the second opposing forced convection heat exchange composite tube 23. A solenoid valve in the middle of the communication pipe between the outer pipe 48 and the medium-pressure air pipe 31 of the turbine-type normal-temperature air compressor 15.

4、起飞前，向主机翼2内的液态空气储罐25充注液态空气，同时，向主机翼2内的蓄电池24充电。4. Before taking off, the liquid air storage tank 25 in the main wing 2 is filled with liquid air, and at the same time, the battery 24 in the main wing 2 is charged.

5、启动工质泵27将液态空气储罐24内的液态空气施以高压、从冷端泵入第一相向受迫对流换热复合管22内管37。5. Start the working medium pump 27 to apply high pressure to the liquid air in the liquid air storage tank 24, and pump it from the cold end into the inner tube 37 of the first forced convection heat exchange composite tube 22.

6、第一相向受迫对流换热复合管22内管37中的液态空气、从自然常温环境吸热汽化后，让其从热端内管40经高压气管32输入电热室17，同时由蓄电池24向电热室17供电，让其吸热升温。6. After the liquid air in the inner tube 37 of the first forced convection heat exchange composite tube 22 absorbs heat from the natural room temperature environment and vaporizes, it is input into the electric heating chamber 17 from the hot end inner tube 40 through the high-pressure air pipe 32, and is simultaneously supplied by the battery. 24 supplies power to the electric heating chamber 17 to allow it to absorb heat and heat up.

7、吸热升温后的高压空气驱动涡轮高压汽轮机18运转工作，首先同轴驱动涡轮式常温空气压缩机15、将其从进气口16吸入的自然常温空气压缩成高热压缩空气。高热压缩空气经中压气管31输入第一相向受迫对流换热复合管22热端外管42，与内管40中的高压空气换热；其中的水蒸汽在热端的除湿仓29液化，经自动排水管30排出；干冷空气继续与低温内管40换热、冷却成为低温压缩空气，在设定位置经中压气管44输入涡轮式低温空气压缩机19，将其进一步压缩成为临界压力空气。7. The high-pressure air that has absorbed heat and heated up drives the turbine high-pressure steam turbine 18 to operate. First, it coaxially drives the turbine-type normal-temperature air compressor 15 to compress the natural normal-temperature air sucked in from the air inlet 16 into high-heat compressed air. The high-heat compressed air is input into the hot-end outer tube 42 of the first forced convection heat exchange composite tube 22 through the medium-pressure air pipe 31, and exchanges heat with the high-pressure air in the inner tube 40; the water vapor therein is liquefied in the dehumidification chamber 29 at the hot end, and is The automatic drain pipe 30 is discharged; the dry cold air continues to exchange heat with the low-temperature inner pipe 40 and is cooled to become low-temperature compressed air. At the set position, it is input to the turbine-type low-temperature air compressor 19 through the medium-pressure air pipe 44 to further compress it into critical pressure air.

8、临界压力空气经中压气管34、35输入反冲排气管21，再经螺旋桨推进器20加速外排，形成反冲推力、推动航空飞机离地升空。8. The critical pressure air is input into the recoil exhaust pipe 21 through the medium

pressure air pipes

34 and 35, and then is accelerated and discharged through the propeller thruster 20 to form recoil thrust and propel the aircraft to lift off the ground.

9、航空飞机升空后，调整其主机翼2角度，让其从垂直方向改为倾斜方向，让其反冲推力在克服航空飞机重力的同时，推动航空飞机朝水平方向前行。9. After the aircraft takes off, adjust the angle of its main wing 2 from the vertical direction to the inclined direction, so that its recoil thrust can push the aircraft forward in the horizontal direction while overcoming the gravity of the aircraft.

10、在航空飞机水平行进速度达到设定速度后，将其主机翼2角度调整为与主机体平行。其时，停止涡轮高压汽轮机18运转工作，停止向电热室17供电，改为由相对运动空气动能驱动涡轮式常温空气压缩机15、涡轮式低温空气压缩机19与螺旋桨推进器20运转。航空飞机进入正常航行工况，由相对运动空气动能驱动的涡轮式常温空气压缩机15将大量常温空气压缩成为高热压缩空气，经中压气管 31输入第二相向受迫对流换热复合管22外管48与由涡轮式低温空气空压机19产生的临界压力空气换热。关闭设置在第一相向受迫对流换热复合管22热端内管40与电热室17的高压气管32之间的连通管中部的电磁阀，关闭设置在第一相向受迫对流换热复合管22热端外管42与涡轮式常温空气压缩机15的中压气管31之间的连通管中部设置的电磁阀。10. After the horizontal traveling speed of the aircraft reaches the set speed, adjust the angle of its main wing 2 to be parallel to the main body. At this time, the operation of the high-pressure turbine 18 is stopped, the power supply to the electric heating chamber 17 is stopped, and the relative motion air kinetic energy is used to drive the turbine normal-temperature air compressor 15, the turbine low-temperature air compressor 19 and the propeller propeller 20 to operate. When the aircraft enters normal flight conditions, the turbine-type normal-temperature air compressor 15 driven by the kinetic energy of the relative motion of the air compresses a large amount of normal-temperature air into high-heat compressed air, which is input to the outside of the second opposite forced convection heat exchange composite pipe 22 through the medium-pressure air pipe 31 The tube 48 exchanges heat with critical pressure air generated by the turbine cryogenic air compressor 19 . Close the solenoid valve provided in the middle of the connecting pipe between the hot end inner tube 40 of the first opposing forced convection heat exchange composite tube 22 and the high-pressure gas pipe 32 of the electric heating chamber 17, and close the solenoid valve provided in the first opposing forced convection heat exchange composite tube. 22. A solenoid valve is provided in the middle of the communication pipe between the hot end outer pipe 42 and the medium pressure air pipe 31 of the turbine normal temperature air compressor 15.

11、同时打开设置在第一相向受迫对流换热复合管22热端内管41与冷端外管39之间的连通管中部的电磁阀，打开设置在第一相向受迫对流换热复合管22热端外管42与第二相向受迫对流换热复合管23冷端外管46之间连通管中部的电磁阀。11. At the same time, open the solenoid valve located in the middle of the connecting pipe between the hot end inner tube 41 and the cold end outer tube 39 of the first opposing forced convection heat exchange composite tube 22, and open the solenoid valve located in the first opposing forced convection heat exchange composite tube. The solenoid valve in the middle of the pipe is connected between the hot end outer pipe 42 of the pipe 22 and the cold end outer pipe 46 of the second opposite forced convection heat exchange composite pipe 23.

12、打开设置在第二相向受迫对流换热复合管23热端外管48与涡轮式常温空气压缩机15中压气管31之间的连通管中部的电磁阀。12. Open the solenoid valve located in the middle of the communication pipe between the hot-end outer pipe 48 of the second opposite forced convection heat exchange composite pipe 23 and the medium-pressure air pipe 31 of the turbine normal-temperature air compressor 15 .

13、高热压缩空气中的水蒸汽在第二相向受迫对流换热复合管22热端外管48的除湿仓29液化，经自动排水管30外排。其中的干空气冷却后经中压气管46输入第一相向受迫对流换热复合管22外管42，与内管中的临界液态空气换热，冷却为低温压缩空气，在设定位置经中压气管44、33输入涡轮式低温空气压缩机19，将其进一步压缩成为临界压力空气。13. The water vapor in the high-heat compressed air is liquefied in the dehumidification chamber 29 of the hot end outer pipe 48 of the second opposite forced convection heat exchange composite pipe 22 and is discharged through the automatic drainage pipe 30. The dry air is cooled and then input into the outer tube 42 of the first forced convection heat exchange composite tube 22 through the medium-pressure air pipe 46. It exchanges heat with the critical liquid air in the inner tube and is cooled into low-temperature compressed air. The

compressed air pipes

44 and 33 are input to the turbine low-temperature air compressor 19, which further compresses it into critical pressure air.

14、大部分临界压力空气经中压气管34、35输入反冲排气管21，再由螺旋桨推进器20加速外排，产生反冲推力，推动航空飞机行进。少量临界压力空气经中压气管34、第一相向受迫对流换热复合管22冷端外管43输入临界压力空气冷却仓31冷凝液化，再经节流阀26 节流，流入液态空气储罐25。14. Most of the critical pressure air is input into the recoil exhaust pipe 21 through the medium

pressure air pipes

34 and 35, and then is accelerated and discharged by the propeller propeller 20 to generate recoil thrust to propel the aircraft forward. A small amount of critical pressure air passes through the medium pressure air pipe 34 and the first forced convection heat exchange composite pipe 22 and the cold end outer pipe 43 and is input into the critical pressure air cooling warehouse 31 for condensation and liquefaction, and then is throttled by the throttle valve 26 and flows into the liquid air storage tank. 25.

15、相对运动空气动能同时驱动小型发电机11发电，其发电量部分供给航空飞机主机体1内电器，部分输入蓄电池24储存。15. The relative motion aerodynamic energy simultaneously drives the small generator 11 to generate electricity. Part of the power generated is supplied to the electrical appliances in the main body 1 of the aircraft, and part is input to the battery 24 for storage.

16、临近返航降落前，先期启动涡轮高压汽轮机18工作运转，快速将主机翼2角度调整到垂直方向，利用快速水平航行阶段所产生的液态空气与电力，联合驱动已经是垂直方向的液态空气热力工质航空发动机运转工作，让其朝下产生出巨大的反冲推力，由其克服航空飞机重力，在设定地面位置实现平稳安全降落。16. Before returning home and landing, start the operation of the high-pressure turbine 18 in advance, quickly adjust the angle of the main wing 2 to the vertical direction, and use the liquid air and electricity generated during the rapid horizontal navigation stage to jointly drive the liquid air heat in the vertical direction. The working fluid aeroengine operates, causing it to generate a huge downward recoil thrust, which overcomes the gravity of the aircraft and achieves a smooth and safe landing at the set ground position.

本发明用途广泛，本发明在原理、工业和商业的应用都包括在本发明权利要求范围内，任何在此基础上的改进都取自本发明的权利要求。The present invention has a wide range of uses. The principles, industrial and commercial applications of the present invention are all included in the scope of the claims of the present invention, and any improvements based on this are taken from the claims of the present invention.

Claims

一种液态空气热力工质航空发动机的方法采用热力发动机驱动航空飞机升空、起飞，其特征在于，采用液态空气为热力发动机的热力工质，让机载液态空气吸收由涡轮高压汽轮机驱动涡轮式常温空气压缩机所产生的高热压缩空气中的热量、汽化成高压空气，再利用其去驱动涡轮高压汽轮机运转；同时采用相向受迫对流换热复合管、重复利用液态空气所携带的低温冷量，将涡轮式常温空气压缩机产生的高热压缩空气冷却为低温压缩空气，然后再利用涡轮式低温空气压缩机将其压缩为临界压力空气；最后将高密度的临界压力空气经螺旋桨推进器加速外排、高效转换成反冲推力，推动航空飞机快速行进，同时将其部分临界压力空气重新液化；在航空飞机快速航行中，停止利用液态空气汽化成为高压空气驱动涡轮高压汽轮机运转，改为由相对运动空气动能收集叶轮所收集的相对运动空气动能驱动涡轮式常温空气压缩机、涡轮式低温空气压缩机与螺旋桨推进器工作；同时采用第二相向受迫对流换热复合管，让涡轮式常温空气压缩机产生的高热压缩空气与涡轮式低温空气压缩机将从第一相向对流换热管复合管内吸入的低温压缩空气再次压缩成为临界压力空气，让两者在其中换热；最后将高密度的临界压力空气高效转换成推动航空飞机行进的反冲推力；同时，在临界压力空气未输入第二相向受迫对流换热复合管前，将其中的部分临界压力空气输入第一相向受迫对流换热复合管冷端外管的临界压力空气冷却区，让其重新液化、并储存起来，作为航空飞机应急状态情况使用与航空飞机下一次升降时使用。上述液态空气热力工质航空发动机设置在航空飞机主机翼下方，当航空飞机设定在现有机场直线跑道上升空、起飞时，液态空气热力工质航空发动机产生出巨大的水平推力，推动飞机快速行进起飞；当航空飞机设定随时随地垂直升降时，将航空飞机的主机翼设计制造成可以折转90度的形式，让主机翼连同液态空气热力工质航空发动机与主机体垂直，液态空气热力工质航空发动机产生巨大的垂直向上的反冲推力，让航空飞机克服重力平稳升空与降落。A liquid air thermal working medium aviation engine method uses a thermal engine to drive an aircraft to take off and take off. It is characterized in that liquid air is used as the thermal working fluid of the thermal engine, and the airborne liquid air is absorbed by a turbine high-pressure steam turbine to drive the turbine. The heat in the high-heat compressed air generated by the normal-temperature air compressor is vaporized into high-pressure air, which is then used to drive the turbine high-pressure turbine. At the same time, opposing forced convection heat exchange composite tubes are used to reuse the low-temperature cold energy carried by the liquid air. , the high-heat compressed air generated by the turbine normal-temperature air compressor is cooled into low-temperature compressed air, and then the turbine low-temperature air compressor is used to compress it into critical pressure air; finally, the high-density critical pressure air is accelerated by the propeller. Discharge and efficient conversion into recoil thrust, propelling the aircraft to travel quickly, and at the same time re-liquefying part of the critical pressure air; during the rapid flight of the aircraft, the vaporization of liquid air into high-pressure air is stopped to drive the operation of the turbine high-pressure turbine, and the relatively high-pressure steam turbine is used instead. Moving air kinetic energy collection The relative moving air kinetic energy collected by the impeller drives the turbine normal temperature air compressor, turbine low temperature air compressor and propeller propeller to work; at the same time, a second opposite forced convection heat exchange composite tube is used to allow the turbine normal temperature air The high-heat compressed air generated by the compressor and the turbine-type low-temperature air compressor compress the low-temperature compressed air sucked from the first counter-current convection heat exchange tube composite tube into critical pressure air, allowing the two to exchange heat; finally, the high-density air is compressed into critical pressure air. The critical pressure air is efficiently converted into the recoil thrust that propels the aircraft forward; at the same time, before the critical pressure air is input into the second phase forced convection heat exchange composite tube, part of the critical pressure air is input into the first phase forced convection heat exchanger. The critical pressure air cooling area of the outer tube at the cold end of the thermal composite pipe allows it to be re-liquefied and stored for use in emergency situations and for the next takeoff and landing of the aircraft. The above-mentioned liquid air thermal refrigerant aeroengine is installed under the main wing of the aircraft. When the aircraft is set to take off on the existing straight runway of the airport, the liquid air thermal refrigerant aeroengine generates huge horizontal thrust, pushing the aircraft quickly. Take off; when the aircraft is set to take off vertically at any time, the main wing of the aircraft is designed to be able to be folded 90 degrees, so that the main wing and the liquid air thermal refrigerant engine are perpendicular to the main body, and the liquid air thermal The refrigerant aviation engine generates huge vertical upward recoil thrust, allowing the aircraft to overcome gravity and smoothly lift off and land.
一种液态空气热力工质航空发动机的装置，它包括航空飞机主体，主机翼、尾机翼、起落架，其特征在于，它还包括液态空气热力工质航空发动机主体设备、液态空气热力工质航空发动机附属设备；液态空气热力工质航空发动机主体设备设置在航空飞机主机翼下方，它包括主体设备壳体，主体设备前端开口仓，在主体设备前端开口仓内部上、下、左、右侧面设置有相对运动空气动能收集叶轮，在主体设备壳体外部前端设置有空气顺流百叶窗，在开口仓内设置有小型发电机，副机轴、主机轴，变速箱，在主体设备中部设置有涡轮式常温空气压缩机，进气管，电热室，涡轮高压汽轮机，涡轮式低温空气压缩机，螺旋桨推进器，反冲排气管，中压气管，高压气管；液态空气热力工质航空发动机附属设备设置在航空飞机主机翼内部，它包括第一相向受迫对流换热复合管，第二相向受迫对流换热复合管，蓄电池，液态空气储罐，节流阀，工质泵，抽气机；在第一相向受迫对流换热复合管内，设置有除湿仓，自动排水管，临界压力空气冷却仓，中压气管，高压液管，高压气管；在第二相向受迫对流换热复合管内，设置有除湿仓，自动排水管，中压气管；在反冲排气管、涡轮式低温空气压缩机以及第一相向受迫对流换热复合管以及所有低温部件外壳，均设置保温层。相向受迫对流换热复合管由传热性能好的金属材料制成。在液态空气热力工质航空发动机主体设备与附属设备之间的部分中压气管、高压气管、高压液管之间的连通管中部设置电磁阀。A device for a liquid air thermal working medium aeroengine, which includes the main body of an aircraft, a main wing, a tail wing, and a landing gear. It is characterized in that it also includes the main equipment of a liquid air thermal working medium aeroengine, a liquid air thermal working medium Auxiliary equipment of the aeroengine; the main equipment of the liquid air thermal refrigerant aeroengine is arranged under the main wing of the aircraft. It includes the main equipment shell, the front-end opening compartment of the main equipment, and the upper, lower, left and right sides of the main equipment front-end opening compartment. There is a relatively moving aerodynamic energy collection impeller on the surface, an air flow shutter is provided at the front end of the outer shell of the main equipment, a small generator, an auxiliary shaft, a main engine shaft, and a gearbox are installed in the open chamber. In the middle of the main equipment, there is an Turbine normal temperature air compressor, air intake pipe, electric heating chamber, turbine high-pressure steam turbine, turbine low-temperature air compressor, propeller propeller, recoil exhaust pipe, medium-pressure air pipe, high-pressure air pipe; liquid air thermal working medium aviation engine ancillary equipment Set inside the main wing of an aviation aircraft, it includes a first phase forced convection heat exchange composite tube, a second phase forced convection heat exchange composite tube, a battery, a liquid air storage tank, a throttle valve, a working medium pump, and an air extractor. ;In the first phase forced convection heat exchange composite pipe, there are dehumidification chamber, automatic drainage pipe, critical pressure air cooling warehouse, medium pressure air pipe, high pressure liquid pipe, high pressure air pipe; in the second phase forced convection heat exchange composite pipe , equipped with a dehumidification bin, an automatic drainage pipe, and a medium-pressure air pipe; the recoil exhaust pipe, the turbine low-temperature air compressor, the first forced convection heat exchange composite pipe, and the shells of all low-temperature components are all equipped with thermal insulation layers. Opposite forced convection heat exchange composite tubes are made of metal materials with good heat transfer properties. A solenoid valve is installed in the middle of the connecting pipe between some of the medium-pressure air pipes, high-pressure air pipes and high-pressure liquid pipes between the main equipment of the liquid air thermal working medium aircraft engine and the auxiliary equipment.

同时采用多具第一相向受迫对流换热复合管，间断性地轮换将第一相向受迫对流换热复合管热端内管中的高热高压空气，调头转向流经另一具结冰的内管的方法，及时融解内管外壁上的结冰层。At the same time, multiple first phase forced convection heat exchange composite tubes are used to intermittently rotate the high-heat and high-pressure air in the hot end inner tube of the first phase forced convection heat exchange composite tube to turn around and flow through another icing tube. The inner tube method can promptly melt the ice layer on the outer wall of the inner tube.
根据权利要求2所述装置，其特征在于，在本发明中，所述同时采用多具第一相向受迫对流换热复合管，是指它可以是一具，也可以是两具，还可以是两具以上。The device according to claim 2, characterized in that in the present invention, the simultaneous use of multiple first opposing forced convection heat exchange composite tubes means that it can be one, or two, or There are more than two.