CN114542289A - Precooling engine energy cascade system and design method thereof - Google Patents
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 239000001307 helium Substances 0.000 claims abstract description 109
- 229910052734 helium Inorganic materials 0.000 claims abstract description 109
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims abstract description 109
- 239000001257 hydrogen Substances 0.000 claims abstract description 58
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 58
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 55
- 239000007788 liquid Substances 0.000 claims abstract description 34
- 238000007906 compression Methods 0.000 claims description 93
- 230000006835 compression Effects 0.000 claims description 92
- 230000001172 regenerating effect Effects 0.000 claims description 84
- 238000001816 cooling Methods 0.000 claims description 22
- 101100134058 Caenorhabditis elegans nth-1 gene Proteins 0.000 claims description 10
- 238000010521 absorption reaction Methods 0.000 claims description 10
- 230000005540 biological transmission Effects 0.000 claims description 5
- 239000000446 fuel Substances 0.000 description 6
- 239000007789 gas Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- UPMXNNIRAGDFEH-UHFFFAOYSA-N 3,5-dibromo-4-hydroxybenzonitrile Chemical compound OC1=C(Br)C=C(C#N)C=C1Br UPMXNNIRAGDFEH-UHFFFAOYSA-N 0.000 description 3
- 150000002431 hydrogen Chemical class 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
- F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
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Abstract
The invention discloses a precooling engine energy cascade system and a design method thereof, wherein the system comprises a high-temperature module, a medium-temperature module and a low-temperature module, wherein the three modules are helium loops which respectively exchange heat with an air pipeline and a liquid hydrogen pipeline, and the flow directions of working media in the air pipeline and the liquid hydrogen pipeline are opposite; the high-temperature module is positioned at the inlet end of the air pipeline, namely the outlet end of the liquid hydrogen pipeline; the low-temperature module is positioned at the outlet end of the air pipeline, namely the inlet end of the liquid hydrogen pipeline; the middle temperature module is positioned between the high temperature module and the low temperature module; all include the closed brayton unit more than two in every module, every closed brayton unit all includes: two or three heat exchangers, a compressor and a turbine; the heat exchanger, the compressor and the turbine are connected in series through pipelines to form a closed loop; the invention can complete the design of the thermal cycle of the precooling engine with different requirements on thrust and specific impulse performance according to the use requirement of the precooling engine.
Description
Technical Field
The invention belongs to the technical field of combined engines, and particularly relates to a precooling engine energy cascade system and a design method thereof.
Background
Conventional fuel direct pre-cooling engines and deep pre-cooling engine thermodynamic cycles represented by SABRE engines are shown in fig. 1 and 2, respectively. In the precooling engines, the fuel cooling dosage required for cooling air to the target temperature is often far greater than the combustion dosage, so that the specific impulse of the precooling engines is low, and the precooling engines become one of the main factors for restricting the development of the precooling engines.
Aiming at the problems of serious fuel waste and low specific impulse of an engine in precooling, the following solutions are proposed:
(1) the ramjet engine or the rocket engine is connected in parallel, the excessive fuel of the precooling engine is consumed, and the overall specific impulse of the engine is improved;
(2) the thermal cycle of the precooling engine is optimized, the precooling depth is reduced, and the fuel cooling consumption is reduced.
Although the specific impact performance of the whole engine can be effectively improved by the mode that the precooling engine is connected with other types of engines in parallel, the size and the weight of the whole engine are obviously increased and the thrust-weight ratio of the whole engine is reduced because the precooling engine is connected with one complete engine of other types in parallel; the thermodynamic cycle design optimization of the precooling engine is very difficult, and particularly for flight tasks with different use requirements such as cruise type flight tasks and carrying type flight tasks, the precooling engine with different thrust and specific impact performance requirements is lack of a systematic thermodynamic cycle design method at present.
Disclosure of Invention
In view of this, the invention provides an energy cascade system of a pre-cooling engine and a design method thereof, which can complete the design of thermal cycle of the pre-cooling engine with different requirements on thrust and specific impulse performance according to the use requirements of the pre-cooling engine.
The invention is realized by the following technical scheme:
an energy cascade system of a precooled engine comprises three modules, namely a high-temperature module, a medium-temperature module and a low-temperature module, wherein the three modules are helium loops which exchange heat with an air pipeline and a liquid hydrogen pipeline respectively, and the flowing directions of working media in the air pipeline and the liquid hydrogen pipeline are opposite; the high-temperature module is positioned at the inlet end of the air pipeline, namely the outlet end of the liquid hydrogen pipeline; the low-temperature module is positioned at the outlet end of the air pipeline, namely the inlet end of the liquid hydrogen pipeline; the medium temperature module is located between the high temperature module and the low temperature module.
Further, all include more than two closed type brayton unit in every module, every closed type brayton unit all includes: two or three heat exchangers, a compressor C and a turbine T; two or three heat exchangers, a compressor C and a turbine T are connected in series through pipelines to form a closed loop, and helium is filled in the pipelines of the closed loop; at least one heat exchanger is arranged between the compressor C and the turbine T;
more than two closed Brayton units in each module are respectively a No. 1 unit, a No. 2 unit, … unit and an Nth unit from high temperature to low temperature; the unit 1 comprises two heat exchangers, all the other units comprise three heat exchangers, the first heat exchanger of the unit 1 exchanges heat with the air pipeline, the second heat exchanger of the unit 1 exchanges heat with the first heat exchanger of the unit 2, the second heat exchanger of the unit 2 exchanges heat with the air pipeline, the third heat exchanger of the unit 2 exchanges heat with the first heat exchanger of the unit 3, …, and so on, …, the third heat exchanger of the unit N-1 exchanges heat with the first heat exchanger of the unit N, the second heat exchanger of the unit N exchanges heat with the air pipeline, and the third heat exchanger of the unit N exchanges heat with the liquid hydrogen pipeline; and N in each module is a positive integer greater than 2.
Further, the values of N of the three modules are not necessarily the same.
A design method of precooling engine energy cascade is based on the energy cascade system and comprises the following specific steps:
firstly, constructing a cold end shunting regenerative compression subsystem of an energy cascade system, cooling helium which is expanded and does work in an Nth unit by liquid hydrogen and then pressurizing the cooled helium between high-temperature air and low-temperature hydrogen to be used as a cold source A of the Nth-1 unit, cooling the helium which is expanded and does work in the Nth-1 unit by the cold source A and then pressurizing the cooled helium to be used as a cold source B of the Nth-2 unit, and so on, and completing the cooling and compression of all helium by the transmission of the cold source;
and secondly, designing a step structure of a hydrogen cold source: continuously constructing two cold end flow-dividing regenerative compression subsystems on the basis of the first step; the three cold end shunting regenerative compression subsystems are respectively defined as a primary regenerative compression system, a secondary regenerative compression system and a tertiary regenerative compression system, namely the cold end shunting regenerative compression subsystem taking low-temperature liquid hydrogen as a cold source is defined as the primary regenerative compression system, the cold end shunting regenerative compression system taking medium-temperature hydrogen as the cold source is defined as the secondary regenerative compression system, the cold end shunting regenerative compression system taking hydrogen with the highest temperature as the cold source is defined as the tertiary regenerative compression system, helium in the primary regenerative compression system is low-temperature helium, helium in the secondary regenerative compression system is medium-temperature helium, and helium in the tertiary regenerative compression system is high-temperature helium;
thirdly, distributing high and low temperature steps of the heat absorbing end: the heat absorption end is divided into a high-temperature heat exchanger HX1, a medium-temperature heat exchanger HX2 and a low-temperature heat exchanger HX 3; after the low-temperature helium of the primary regenerative compression system exchanges heat with the low-temperature heat exchanger HX3 of the air pipeline, the low-temperature helium cools the low-temperature air with lower temperature, and the low-temperature helium is heated up, the heated low-temperature helium is mixed with the medium-temperature helium in the secondary regenerative compression system and exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, the medium-temperature air with higher temperature is cooled together, and the medium-temperature helium is heated up, the heated medium-temperature helium is mixed with the high-temperature helium in the tertiary regenerative compression system and exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and the high-temperature air is further cooled together.
The other design method of the precooling engine energy cascade is based on the energy cascade system, and comprises the following specific steps:
the first step, design hydrogen cold source's cascade structure: respectively constructing a primary regenerative compression system, a secondary regenerative compression system and a tertiary regenerative compression system, namely defining a cold end taking low-temperature liquid hydrogen as a cold source as the primary regenerative compression system, defining a cold end taking medium-temperature hydrogen as the cold source as the secondary regenerative compression system, defining a cold end taking hydrogen with the highest temperature as the cold source as the tertiary regenerative compression system, wherein helium in the primary regenerative compression system is low-temperature helium, helium in the secondary regenerative compression system is medium-temperature helium, and helium in the tertiary regenerative compression system is high-temperature helium;
secondly, a cold end shunting regenerative compression subsystem in each regenerative compression system is constructed, helium which is expanded and does work in the Nth unit is cooled and then pressurized by liquid hydrogen between high-temperature air and low-temperature hydrogen to serve as a cold source A of the Nth-1 unit, helium which is expanded and does work in the Nth-1 unit is cooled and then pressurized by the cold source A to serve as a cold source B of the Nth-2 unit, and the rest is done in the same way, and all the helium is cooled and compressed by the transmission of the cold source;
thirdly, distributing high and low temperature steps of the heat absorbing end: the heat absorption end is divided into a high-temperature heat exchanger HX1, a medium-temperature heat exchanger HX2 and a low-temperature heat exchanger HX 3; after the low-temperature helium of the primary regenerative compression system exchanges heat with the low-temperature heat exchanger HX3 of the air pipeline, the low-temperature helium cools the low-temperature air with lower temperature, and the low-temperature helium is heated up, the heated low-temperature helium is mixed with the medium-temperature helium in the secondary regenerative compression system and exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, the medium-temperature air with higher temperature is cooled together, and the medium-temperature helium is heated up, the heated medium-temperature helium is mixed with the high-temperature helium in the tertiary regenerative compression system and exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and the high-temperature air is further cooled together.
Has the advantages that:
(1) the invention provides an energy cascade system of a precooling engine and a design method thereof aiming at the problem that the cooling consumption is far more than the combustion consumption in the thermal cycle of a deep precooling engine represented by an SABRE engine, and all available heat sinks in the system are fully utilized to form closed cycle; at the closed circulation heat absorption end, cooling working media are arranged and combined according to temperature distribution, high-temperature air is cooled in a gradient mode, and finally the design of the thermal circulation of the precooling engine under different thrust and specific impact performance requirements can be completed according to the use requirements of the precooling engine.
Drawings
FIG. 1 is a schematic diagram of a conventional PCTJ fuel direct pre-cool engine cycle;
FIG. 2 is a diagram of a conventional SABRE engine thermal cycle;
FIG. 3 is a schematic structural component view of the present invention;
FIG. 4 is a diagram of a cold side split-flow regenerative compression subsystem of the present invention;
FIG. 5 is a step structure view of the hydrogen cooling source of the present invention;
FIG. 6 is a high and low temperature step distribution diagram of the heat absorption end of the present invention.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
Example 1:
the embodiment provides an energy cascade system of a precooling engine, and referring to the attached drawing 3, the system comprises three modules, namely a high-temperature module, a medium-temperature module and a low-temperature module, wherein the three modules exchange heat with an air pipeline and a liquid hydrogen pipeline respectively, and the flowing directions of working media in the air pipeline and the liquid hydrogen pipeline are opposite; the high-temperature module is positioned at the inlet end (the highest air temperature end) of the air pipeline, namely the outlet end (the highest liquid hydrogen temperature end) of the liquid hydrogen pipeline; the low-temperature module is positioned at the outlet end (the lowest air temperature end) of the air pipeline, namely the inlet end (the lowest liquid hydrogen temperature end) of the liquid hydrogen pipeline; the middle temperature module is positioned between the high temperature module and the low temperature module;
all include the closed brayton unit more than two in every module, every closed brayton unit all includes: two or three heat exchangers, a compressor C and a turbine T; two or three heat exchangers, a compressor C and a turbine T are connected in series through pipelines to form a closed loop, and helium is filled in the pipelines of the closed loop; at least one heat exchanger is arranged between the compressor C and the turbine T;
more than two closed Brayton units in each module are respectively a No. 1 unit, a No. 2 unit, … unit and an Nth unit from high temperature to low temperature; the unit 1 comprises two heat exchangers, all the other units comprise three heat exchangers, the first heat exchanger of the unit 1 exchanges heat with the air pipeline, the second heat exchanger of the unit 1 exchanges heat with the first heat exchanger of the unit 2, the second heat exchanger of the unit 2 exchanges heat with the air pipeline, the third heat exchanger of the unit 2 exchanges heat with the first heat exchanger of the unit 3, …, and so on, …, the third heat exchanger of the unit N-1 exchanges heat with the first heat exchanger of the unit N, the second heat exchanger of the unit N exchanges heat with the air pipeline, and the third heat exchanger of the unit N exchanges heat with the liquid hydrogen pipeline; and N in each module is a positive integer greater than 2, and the values of N of the three modules are not necessarily the same.
The working principle is as follows: liquid hydrogen in the liquid hydrogen pipeline is respectively subjected to heat exchange with helium in a closed Brayton unit in the low-temperature module, the medium-temperature module and the high-temperature module in sequence, and the helium in the low-temperature module, the medium-temperature module and the high-temperature module is respectively subjected to step cooling; and high-temperature air in the air pipeline is subjected to heat exchange with the cooled helium in all closed Brayton units in the high-temperature module, the medium-temperature module and the low-temperature module in sequence, so that the high-temperature air in the air pipeline is subjected to step cooling.
Example 2:
the embodiment provides a design method of an energy cascade of a precooling engine on the basis of embodiment 1, and the method specifically comprises the following steps:
the method comprises the following steps that firstly, a cold end shunting and backheating compression subsystem of an energy cascade system is constructed, wherein the cold end shunting and backheating compression subsystem is a heat exchange compression process between cooled helium gas after heat exchange between a closed Brayton unit and a liquid hydrogen pipeline in each module; the cold end shunting and backheating compression subsystem is the basis of a precooling engine energy cascade design method, the basic principle of the cold end shunting and backheating compression subsystem is shown in figure 4, each module divides a large closed Brayton cycle into N closed Brayton units with equal flow, and the stable work of each closed Brayton unit needs to meet the requirements of pressure balance and flow balance; therefore, each closed Brayton unit is provided with a compressor and a turbine, and the compressor is used for pressurizing and heating helium; the turbine is used for performing expansion work on the helium; the purpose of the regenerative compression of the compressor is to cool and compress all the high-temperature low-pressure helium gas which has done work so as to recover to an initial state for the next cycle; between high-temperature air and low-temperature hydrogen, helium expanded and acted in the Nth unit is cooled by liquid hydrogen and then pressurized to serve as a cold source A of the Nth-1 unit, helium expanded and acted in the Nth-1 unit is cooled by the cold source A and then pressurized to serve as a cold source B of the Nth-2 unit, and the rest is done, and cooling and compression of all helium are completed through transmission of the cold source; on the basis of 1 path of cold source, the cold end shunting heat return compression subsystem can obtain 1 low-temperature path and N-1 high-temperature paths with the pressure returning to the initial state, and the temperature of the helium working medium of the high-temperature path is equivalent to the temperature of the helium turbine outlet.
And secondly, designing a step structure of a hydrogen cold source: the cascade utilization of the hydrogen cold source refers to that high-temperature and high-pressure hydrogen after absorbing the heat of the closed Brayton unit is expanded and cooled in a turbine and can be used as a new cold source, and more than two cold end shunt regenerative compression subsystems are continuously constructed on the basis of the new cold source; in this embodiment, three cold-end split-flow regenerative compression subsystems are constructed, and the three cold-end split-flow regenerative compression subsystems are respectively defined as a primary regenerative compression system, a secondary regenerative compression system and a tertiary regenerative compression system, that is, the cold-end split-flow regenerative compression subsystem using low-temperature liquid hydrogen as a cold source is defined as the primary regenerative compression system, the cold-end split-flow regenerative compression system using medium-temperature hydrogen as the cold source is defined as the secondary regenerative compression system, and the cold-end split-flow regenerative compression system using hydrogen with the highest temperature as the cold source is defined as the tertiary regenerative compression system, as shown in fig. 5; helium in the first-stage regenerative compression system is low-temperature helium, helium in the second-stage regenerative compression system is medium-temperature helium, and helium in the third-stage regenerative compression system is high-temperature helium; the cascade utilization of a hydrogen cold source aims to maximize the heat sink utilization of a cooling working medium in a precooling engine as much as possible, and the helium branches can be compressed and restored to an initial high-pressure state through cooling as much as possible.
Thirdly, distributing high and low temperature steps of the heat absorbing end: according to the idea of energy cascade utilization, a closed circulation heat absorption end of an energy cascade system is constructed, wherein the closed circulation heat absorption end is a heat exchange process of a closed Brayton unit and an air pipeline in each module; the closed cycle heat absorption end is designed into a cycle configuration shown in fig. 6, and the heat absorption end in the figure is divided into a high-temperature heat exchanger HX1, a medium-temperature heat exchanger HX2 and a low-temperature heat exchanger HX 3; after the low-temperature helium of the first-stage regenerative compression system exchanges heat with the low-temperature heat exchanger HX3 of the air pipeline, the low-temperature helium cools the low-temperature air with lower temperature, and the low-temperature helium is heated up, the heated low-temperature helium is mixed with the medium-temperature helium in the second-stage regenerative compression system, exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, cools the medium-temperature air with higher temperature together, and the medium-temperature helium is heated up, the heated medium-temperature helium is mixed with the high-temperature helium in the third-stage regenerative compression system, exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and further cools the high-temperature air together; the flow rates of the low-temperature helium gas, the medium-temperature helium gas and the high-temperature helium gas are determined by the total flow rate of the cold ends, and the flow rate entering each closed Brayton unit can be changed between 0 and the maximum flow rate; according to precooling engines with different use requirements, helium of a plurality of closed Brayton units at the cold end is combined and distributed at the hot end, so that the design of the thermodynamic cycle of the precooling engines with different performance requirements is achieved.
Example 3:
this example is based on example 2, and the first step and the second step can be exchanged.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. An energy cascade system of a precooling engine is characterized by comprising three modules, namely a high-temperature module, a medium-temperature module and a low-temperature module, wherein the three modules are helium loops which exchange heat with an air pipeline and a liquid hydrogen pipeline respectively, and the flowing directions of working media in the air pipeline and the liquid hydrogen pipeline are opposite; the high-temperature module is positioned at the inlet end of the air pipeline, namely the outlet end of the liquid hydrogen pipeline; the low-temperature module is positioned at the outlet end of the air pipeline, namely the inlet end of the liquid hydrogen pipeline; the medium temperature module is located between the high temperature module and the low temperature module.
2. The pre-chill engine energy step system of claim 1, wherein more than two closed Brayton units are included in each module, each closed Brayton unit comprising: two or three heat exchangers, a compressor C and a turbine T; two or three heat exchangers, a compressor C and a turbine T are connected in series through pipelines to form a closed loop, and helium is filled in the pipelines of the closed loop; at least one heat exchanger is arranged between the compressor C and the turbine T;
more than two closed Brayton units in each module are respectively a No. 1 unit, a No. 2 unit, … unit and an Nth unit from high temperature to low temperature; the unit 1 comprises two heat exchangers, all the other units comprise three heat exchangers, the first heat exchanger of the unit 1 exchanges heat with the air pipeline, the second heat exchanger of the unit 1 exchanges heat with the first heat exchanger of the unit 2, the second heat exchanger of the unit 2 exchanges heat with the air pipeline, the third heat exchanger of the unit 2 exchanges heat with the first heat exchanger of the unit 3, …, and so on, …, the third heat exchanger of the unit N-1 exchanges heat with the first heat exchanger of the unit N, the second heat exchanger of the unit N exchanges heat with the air pipeline, and the third heat exchanger of the unit N exchanges heat with the liquid hydrogen pipeline; and N in each module is a positive integer greater than 2.
3. The pre-chill engine energy step system of claim 2, wherein the values of N of the three modules are not necessarily the same.
4. A design method of a precooling engine energy cascade, which is based on the energy cascade system of claim 2, and is characterized in that the method comprises the following specific steps:
firstly, constructing a cold end shunting regenerative compression subsystem of an energy cascade system, cooling helium which is expanded and does work in an Nth unit by liquid hydrogen and then pressurizing the cooled helium between high-temperature air and low-temperature hydrogen to be used as a cold source A of the Nth-1 unit, cooling the helium which is expanded and does work in the Nth-1 unit by the cold source A and then pressurizing the cooled helium to be used as a cold source B of the Nth-2 unit, and so on, and completing the cooling and compression of all helium by the transmission of the cold source;
the second step, design hydrogen cold source's cascade structure: continuously constructing two cold end flow-dividing regenerative compression subsystems on the basis of the first step; the three cold end shunting regenerative compression subsystems are respectively defined as a primary regenerative compression system, a secondary regenerative compression system and a tertiary regenerative compression system, namely the cold end shunting regenerative compression subsystem taking low-temperature liquid hydrogen as a cold source is defined as the primary regenerative compression system, the cold end shunting regenerative compression system taking medium-temperature hydrogen as the cold source is defined as the secondary regenerative compression system, the cold end shunting regenerative compression system taking hydrogen with the highest temperature as the cold source is defined as the tertiary regenerative compression system, helium in the primary regenerative compression system is low-temperature helium, helium in the secondary regenerative compression system is medium-temperature helium, and helium in the tertiary regenerative compression system is high-temperature helium;
thirdly, distributing high and low temperature steps of the heat absorbing end: the heat absorption end is divided into a high-temperature heat exchanger HX1, a medium-temperature heat exchanger HX2 and a low-temperature heat exchanger HX 3; after the low-temperature helium of the primary regenerative compression system exchanges heat with the low-temperature heat exchanger HX3 of the air pipeline, the low-temperature helium cools the low-temperature air with lower temperature, and the low-temperature helium is heated up, the heated low-temperature helium is mixed with the medium-temperature helium in the secondary regenerative compression system and exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, the medium-temperature air with higher temperature is cooled together, and the medium-temperature helium is heated up, the heated medium-temperature helium is mixed with the high-temperature helium in the tertiary regenerative compression system and exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and the high-temperature air is further cooled together.
5. A design method of a precooling engine energy cascade, which is based on the energy cascade system of claim 2, and is characterized in that the method comprises the following specific steps:
the first step, design hydrogen cold source's cascade structure: respectively constructing a primary regenerative compression system, a secondary regenerative compression system and a tertiary regenerative compression system, namely defining a cold end taking low-temperature liquid hydrogen as a cold source as the primary regenerative compression system, defining a cold end taking medium-temperature hydrogen as the cold source as the secondary regenerative compression system, defining a cold end taking hydrogen with the highest temperature as the cold source as the tertiary regenerative compression system, wherein helium in the primary regenerative compression system is low-temperature helium, helium in the secondary regenerative compression system is medium-temperature helium, and helium in the tertiary regenerative compression system is high-temperature helium;
secondly, a cold end shunting regenerative compression subsystem in each regenerative compression system is constructed, helium which is expanded and does work in the Nth unit is cooled and then pressurized by liquid hydrogen between high-temperature air and low-temperature hydrogen to serve as a cold source A of the Nth-1 unit, helium which is expanded and does work in the Nth-1 unit is cooled and then pressurized by the cold source A to serve as a cold source B of the Nth-2 unit, and the rest is done in the same way, and all the helium is cooled and compressed by the transmission of the cold source;
thirdly, distributing high and low temperature steps of the heat absorbing end: the heat absorption end is divided into a high-temperature heat exchanger HX1, a medium-temperature heat exchanger HX2 and a low-temperature heat exchanger HX 3; after the low-temperature helium of the primary regenerative compression system exchanges heat with the low-temperature heat exchanger HX3 of the air pipeline, the low-temperature helium cools the low-temperature air with lower temperature, and the low-temperature helium is heated up, the heated low-temperature helium is mixed with the medium-temperature helium in the secondary regenerative compression system and exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, the medium-temperature air with higher temperature is cooled together, and the medium-temperature helium is heated up, the heated medium-temperature helium is mixed with the high-temperature helium in the tertiary regenerative compression system and exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and the high-temperature air is further cooled together.
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