CN114542289B - Precooling engine energy cascade system and design method thereof - Google Patents
Precooling engine energy cascade system and design method thereof Download PDFInfo
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- 238000000034 method Methods 0.000 title claims abstract description 15
- 238000013461 design Methods 0.000 title abstract description 16
- 239000001307 helium Substances 0.000 claims abstract description 114
- 229910052734 helium Inorganic materials 0.000 claims abstract description 114
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 claims abstract description 114
- 239000001257 hydrogen Substances 0.000 claims abstract description 59
- 229910052739 hydrogen Inorganic materials 0.000 claims abstract description 59
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 claims abstract description 49
- 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 87
- 239000007789 gas Substances 0.000 claims description 35
- 238000001816 cooling Methods 0.000 claims description 20
- 150000002431 hydrogen Chemical class 0.000 claims description 10
- 238000010521 absorption reaction Methods 0.000 claims description 9
- 230000005540 biological transmission Effects 0.000 claims description 5
- 238000010586 diagram Methods 0.000 description 6
- 239000000446 fuel Substances 0.000 description 6
- 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
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000011010 flushing procedure Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 238000010248 power generation Methods 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
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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
-
- 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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Separation By Low-Temperature Treatments (AREA)
Abstract
The invention discloses an energy cascade system of a precooling engine 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, the helium loops exchange heat with an air pipeline and a liquid hydrogen pipeline respectively, and the flowing directions of working mediums 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 positioned between the high temperature module and the low temperature module; each module comprises more than two closed Brayton units, and each closed Brayton unit comprises: 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 thermodynamic cycle of the precooling engine with different thrust and specific impulse performance requirements according to the use requirements of the precooling engine.
Description
Technical Field
The invention belongs to the technical field of combined engines, and particularly relates to an energy cascade system of a precooling engine and a design method of the energy cascade system.
Background
Conventional fuel direct precooling engines and deep precooling engine thermodynamic cycles represented by SABRE engines are shown in fig. 1 and 2, respectively. In the precooling engine, the fuel cooling amount required for cooling the air to the target temperature is often far greater than the combustion amount, so that the specific flushing of the engine is low, and the precooling engine becomes one of main factors for restricting the development of the precooling engine.
Aiming at the problems of serious fuel waste and low engine specific impulse of a precooled engine, the following solution is proposed:
(1) The parallel ramjet engine or rocket engine consumes excessive fuel of the precooling engine, and improves the overall specific impulse of the engine;
(2) Optimizing the thermodynamic cycle of the precooling engine, reducing the precooling depth and reducing the cooling consumption of fuel.
Though the specific impulse performance of the whole engine can be effectively improved by connecting the precooling engine with other types of engines in parallel, the whole engine size and weight are obviously increased and the thrust-weight ratio of the whole engine is reduced due to the fact that the precooling engine is connected with a complete other type of engine in parallel; the design optimization of the thermodynamic cycle of the precooling engine is very difficult, and particularly, the precooling engine under different thrust and specific impact performance requirements is aimed at flight tasks with different use requirements such as cruising type and carrying type, and a thermodynamic cycle design method of a system is lacking currently.
Disclosure of Invention
In view of the above, the present invention provides an energy cascade system for a precooling engine and a design method thereof, which can complete the design of thermodynamic cycles of the precooling engine with different thrust and specific impact performance requirements according to the use requirements of the precooling engine.
The invention is realized by the following technical scheme:
the system comprises three modules, namely a high-temperature module, a medium-temperature module and a low-temperature module, wherein the three modules are helium loops, the helium loops exchange heat with an air pipeline and a liquid hydrogen pipeline respectively, and the flowing directions of working mediums 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 positioned between the high temperature module and the low temperature module.
Further, each module includes more than two closed brayton units, and each closed brayton unit 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 a pipeline to form a closed loop, and helium is filled in the pipeline of the closed loop; and at least one heat exchanger is arranged between the compressor C and the turbine T;
the more than two closed Brayton units in each module are respectively a 1 st unit, a 2 nd unit, a … th unit and an N th unit according to the sequence from high temperature to low temperature; the first heat exchanger of the 1 st unit exchanges heat with the air pipeline, the second heat exchanger of the 1 st unit exchanges heat with the first heat exchanger of the 2 nd unit, the second heat exchanger of the 2 nd unit exchanges heat with the air pipeline, the third heat exchanger of the 2 nd unit exchanges heat with the first heat exchanger of the 3 rd unit, … and the like, …, the third heat exchanger of the N-1 th unit exchanges heat with the first heat exchanger of the N th unit, the second heat exchanger of the N th unit exchanges heat with the air pipeline, and the third heat exchanger of the N th unit exchanges heat with the liquid hydrogen pipeline; wherein 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 steps is based on the energy step system, and comprises the following specific steps:
firstly, constructing a cold end split-flow regenerative compression subsystem of an energy cascade system, cooling helium gas expanded in an N-th unit by liquid hydrogen between high-temperature air and low-temperature hydrogen, pressurizing the helium gas, which is expanded in the N-th unit and is subjected to work, serving as a cold source A of the N-1-th unit, pressurizing the helium gas expanded in the N-1-th unit after being cooled by the cold source A, serving as a cold source B of the N-2-th unit, and so on, completing cooling and compression of all helium gas through transmission of the cold source;
step two, designing a step structure of a hydrogen cold source: continuously constructing two cold end split-flow regenerative compression subsystems on the basis of the first step; the three cold end split-flow regenerative compression subsystems are respectively defined as a first-stage regenerative compression system, a second-stage regenerative compression system and a third-stage regenerative compression system, namely the cold end split-flow regenerative compression subsystem taking low-temperature liquid hydrogen as a cold source is defined as a first-stage regenerative compression system, the cold end split-flow regenerative compression system taking medium-temperature hydrogen as the cold source is defined as a second-stage regenerative compression system, the cold end split-flow regenerative compression system taking the hydrogen with the highest temperature as the cold source is defined as a third-stage regenerative compression system, 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;
thirdly, distributing the 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 HX3; 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 low-temperature air with lower temperature, the low-temperature helium is heated, the heated low-temperature helium is mixed with medium-temperature helium in the second-stage regenerative compression system, exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, jointly cools medium-temperature air with higher temperature, and the medium-temperature helium is heated, the heated medium-temperature helium is mixed with high-temperature helium in the third-stage regenerative compression system, exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and jointly further cools the high-temperature air.
Another design method of precooling engine energy steps is based on the energy step system, and the method comprises the following specific steps:
step one, designing a step structure of a hydrogen cold source: respectively constructing a first-stage regenerative compression system, a second-stage regenerative compression system and a third-stage regenerative compression system, namely defining a cold end taking low-temperature liquid hydrogen as a cold source as a first-stage regenerative compression system, defining a cold end taking medium-temperature hydrogen as the cold source as a second-stage regenerative compression system, defining a cold end taking hydrogen with highest temperature as the cold source as a third-stage regenerative compression system, wherein 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;
secondly, constructing a cold end split-flow regenerative compression subsystem in each regenerative compression system, cooling the helium gas expanded and acted in the N unit by liquid hydrogen between high-temperature air and low-temperature hydrogen, pressurizing the helium gas, serving as a cold source A of the N-1 unit, cooling the helium gas expanded and acted in the N-1 unit by the cold source A, pressurizing the helium gas, serving as a cold source B of the N-2 unit, and so on, completing cooling and compression of all helium gas through transmission of the cold source;
thirdly, distributing the 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 HX3; 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 low-temperature air with lower temperature, the low-temperature helium is heated, the heated low-temperature helium is mixed with medium-temperature helium in the second-stage regenerative compression system, exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, jointly cools medium-temperature air with higher temperature, and the medium-temperature helium is heated, the heated medium-temperature helium is mixed with high-temperature helium in the third-stage regenerative compression system, exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and jointly further cools the high-temperature air.
The beneficial effects are that:
(1) Aiming at the problem that the cooling consumption is far greater than the combustion consumption in the deep precooling engine thermodynamic cycle represented by the SABRE engine, all available heat sinks in the system are fully utilized to form closed cycle, and on the basis of referencing the parallel type heat power conversion scheme and the heat transfer idea of the ground power generation system, the invention provides an energy cascade system of the precooling engine and a design method thereof, wherein the core idea is that the low-temperature and medium-temperature heat sinks in the system are subjected to cascade utilization of different degrees in the closed cycle heat release end according to the engine performance requirement; at the closed circulation heat absorption end, according to temperature distribution, the cooling working medium is arranged and combined, high-temperature air is cooled in a step mode, and finally, the design of the thermodynamic cycle 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 precooling engine cycle;
FIG. 2 is a diagram of a conventional SABRE engine thermodynamic cycle;
FIG. 3 is a schematic diagram of the structural composition 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 diagram of the hydrogen cold source of the present invention;
fig. 6 is a high and low temperature gradient distribution diagram of the heat absorbing end of the present invention.
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
Example 1:
the embodiment provides an energy cascade system of a precooling engine, referring to fig. 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 medium temperature module is positioned between the high temperature module and the low temperature module;
each module comprises more than two closed Brayton units, and each closed Brayton unit comprises: 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 a pipeline to form a closed loop, and helium is filled in the pipeline of the closed loop; and at least one heat exchanger is arranged between the compressor C and the turbine T;
the more than two closed Brayton units in each module are respectively a 1 st unit, a 2 nd unit, a … th unit and an N th unit according to the sequence from high temperature to low temperature; the first heat exchanger of the 1 st unit exchanges heat with the air pipeline, the second heat exchanger of the 1 st unit exchanges heat with the first heat exchanger of the 2 nd unit, the second heat exchanger of the 2 nd unit exchanges heat with the air pipeline, the third heat exchanger of the 2 nd unit exchanges heat with the first heat exchanger of the 3 rd unit, … and the like, …, the third heat exchanger of the N-1 th unit exchanges heat with the first heat exchanger of the N th unit, the second heat exchanger of the N th unit exchanges heat with the air pipeline, and the third heat exchanger of the N th unit exchanges heat with the liquid hydrogen pipeline; n in each module is a positive integer greater than 2, and N values of the three modules are not necessarily the same.
Working principle: the liquid hydrogen in the liquid hydrogen pipeline is sequentially in heat exchange with helium in a closed brayton unit in the low temperature module, the medium temperature module and the high temperature module respectively, and the helium in the low temperature module, the medium temperature module and the high temperature module is subjected to gradient cooling respectively; and the high-temperature air in the air pipeline is subjected to heat exchange with the cooled helium in all the closed Brayton units in the high-temperature module, the medium-temperature module and the low-temperature module in sequence respectively, so that the gradient cooling of the high-temperature air in the air pipeline is realized.
This example 2:
the embodiment provides a design method of a pre-cooling engine energy step based on embodiment 1, which comprises the following specific steps:
firstly, constructing a cold end split-flow regenerative compression subsystem of an energy cascade system, wherein the cold end split-flow regenerative compression subsystem is a heat exchange compression process between closed brayton units in each module and helium after heat exchange with a liquid hydrogen pipeline; the cold end split-flow regenerative compression subsystem is the basis of an energy cascade design method of a precooling engine, the basic principle is shown in fig. 4, each module divides a large closed brayton cycle into N closed brayton units with equal flow, and the stable operation of each closed brayton unit needs to meet the pressure balance and the 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 expanding helium to do work; the purpose of backheating and compression through the compressor is to cool all high-temperature low-pressure helium gas which does work and then compress the helium gas so as to restore to an initial state for next circulation; between high-temperature air and low-temperature hydrogen, the helium gas after expansion and work doing in the N-th unit is cooled by liquid hydrogen and then pressurized to be used as a cold source A of the N-1-th unit, the helium gas after expansion and work doing in the N-1-th unit is cooled by the cold source A and then pressurized to be used as a cold source B of the N-2-th unit, and the like, and all helium gas is cooled and compressed through the transmission of the cold source; the cold end split-flow regenerative compression subsystem can obtain 1 low-temperature path and N-1 high-temperature paths with pressure returning to an initial state on the basis of 1 path of cold source, and the temperature of a high Wen Luhai working medium is equivalent to the temperature of a helium turbine outlet.
Step two, designing a step structure of a hydrogen cold source: the cascade utilization of the hydrogen cold source refers to that the hydrogen with high temperature and high pressure after absorbing the heat of the closed Brayton unit can be used as a new cold source after being expanded and cooled in a turbine, and more than two cold end split-flow regenerative compression subsystems are continuously constructed based on the hydrogen cold source; in this embodiment, three cold-end split-flow regenerative compression subsystems are constructed, wherein the three cold-end split-flow regenerative compression subsystems are respectively defined as a first-stage regenerative compression system, a second-stage regenerative compression system and a third-stage regenerative compression system, namely, the cold-end split-flow regenerative compression subsystem using low-temperature liquid hydrogen as a cold source is defined as a first-stage regenerative compression system, the cold-end split-flow regenerative compression system using medium-temperature hydrogen as the cold source is defined as a second-stage 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 a third-stage 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 the hydrogen cold source aims at maximizing the heat sink utilization of the cooling working medium in the precooling engine as much as possible, and realizing that as many helium branches as possible can be compressed and restored to an initial high-pressure state through cooling.
Thirdly, distributing the 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 the heat exchange process of a closed Brayton unit and an air pipeline in each module; the closed circulation heat absorption end is designed into a circulation 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 HX3; after the low-temperature helium gas of the first-stage regenerative compression system exchanges heat with the low-temperature heat exchanger HX3 of the air pipeline, the low-temperature helium gas cools low-temperature air with lower temperature, the low-temperature helium gas is heated, the heated low-temperature helium gas is mixed with the medium-temperature helium gas in the second-stage regenerative compression system, exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, jointly cools the medium-temperature air with higher temperature, the medium-temperature helium gas is heated, the heated medium-temperature helium gas is mixed with the high-temperature helium gas in the third-stage regenerative compression system, exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and jointly further cools the high-temperature air; 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 end, 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 gas 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 engine with different performance requirements is achieved.
Example 3:
this embodiment can be based on embodiment 2, where the first step and the second step are exchanged.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (4)
1. The precooling engine energy cascade system 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, the helium loops exchange heat with an air pipeline and a liquid hydrogen pipeline respectively, and the flowing directions of working mediums 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 positioned between the high temperature module and the low temperature module;
each module comprises more than two closed Brayton units, and each closed Brayton unit comprises: 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 a pipeline to form a closed loop, and helium is filled in the pipeline of the closed loop; and at least one heat exchanger is arranged between the compressor C and the turbine T;
the more than two closed Brayton units in each module are respectively a 1 st unit, a 2 nd unit, a … th unit and an N th unit according to the sequence from high temperature to low temperature; the first heat exchanger of the 1 st unit exchanges heat with the air pipeline, the second heat exchanger of the 1 st unit exchanges heat with the first heat exchanger of the 2 nd unit, the second heat exchanger of the 2 nd unit exchanges heat with the air pipeline, the third heat exchanger of the 2 nd unit exchanges heat with the first heat exchanger of the 3 rd unit, … and the like, …, the third heat exchanger of the N-1 th unit exchanges heat with the first heat exchanger of the N th unit, the second heat exchanger of the N th unit exchanges heat with the air pipeline, and the third heat exchanger of the N th unit exchanges heat with the liquid hydrogen pipeline; wherein N in each module is a positive integer greater than 2.
2. A pre-chilled engine energy step system as in claim 1, wherein the N values of the three modules are not necessarily the same.
3. A method of designing a pre-cooled engine energy cascade based on the energy cascade system of claim 1, characterized by the specific steps of:
firstly, constructing a cold end split-flow regenerative compression subsystem of an energy cascade system, cooling helium gas expanded in an N-th unit by liquid hydrogen between high-temperature air and low-temperature hydrogen, pressurizing the helium gas, which is expanded in the N-th unit and is subjected to work, serving as a cold source A of the N-1-th unit, pressurizing the helium gas expanded in the N-1-th unit after being cooled by the cold source A, serving as a cold source B of the N-2-th unit, and so on, completing cooling and compression of all helium gas through transmission of the cold source;
step two, designing a step structure of a hydrogen cold source: continuously constructing two cold end split-flow regenerative compression subsystems on the basis of the first step; the three cold end split-flow regenerative compression subsystems are respectively defined as a first-stage regenerative compression system, a second-stage regenerative compression system and a third-stage regenerative compression system, namely the cold end split-flow regenerative compression subsystem taking low-temperature liquid hydrogen as a cold source is defined as a first-stage regenerative compression system, the cold end split-flow regenerative compression system taking medium-temperature hydrogen as the cold source is defined as a second-stage regenerative compression system, the cold end split-flow regenerative compression system taking the hydrogen with the highest temperature as the cold source is defined as a third-stage regenerative compression system, 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;
thirdly, distributing the 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 HX3; 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 low-temperature air with lower temperature, the low-temperature helium is heated, the heated low-temperature helium is mixed with medium-temperature helium in the second-stage regenerative compression system, exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, jointly cools medium-temperature air with higher temperature, and the medium-temperature helium is heated, the heated medium-temperature helium is mixed with high-temperature helium in the third-stage regenerative compression system, exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and jointly further cools the high-temperature air.
4. A method of designing a pre-cooled engine energy cascade based on the energy cascade system of claim 1, characterized by the specific steps of:
step one, designing a step structure of a hydrogen cold source: respectively constructing a first-stage regenerative compression system, a second-stage regenerative compression system and a third-stage regenerative compression system, namely defining a cold end taking low-temperature liquid hydrogen as a cold source as a first-stage regenerative compression system, defining a cold end taking medium-temperature hydrogen as the cold source as a second-stage regenerative compression system, defining a cold end taking hydrogen with highest temperature as the cold source as a third-stage regenerative compression system, wherein 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;
secondly, constructing a cold end split-flow regenerative compression subsystem in each regenerative compression system, cooling the helium gas expanded and acted in the N unit by liquid hydrogen between high-temperature air and low-temperature hydrogen, pressurizing the helium gas, serving as a cold source A of the N-1 unit, cooling the helium gas expanded and acted in the N-1 unit by the cold source A, pressurizing the helium gas, serving as a cold source B of the N-2 unit, and so on, completing cooling and compression of all helium gas through transmission of the cold source;
thirdly, distributing the 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 HX3; 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 low-temperature air with lower temperature, the low-temperature helium is heated, the heated low-temperature helium is mixed with medium-temperature helium in the second-stage regenerative compression system, exchanges heat with the medium-temperature heat exchanger HX2 of the air pipeline, jointly cools medium-temperature air with higher temperature, and the medium-temperature helium is heated, the heated medium-temperature helium is mixed with high-temperature helium in the third-stage regenerative compression system, exchanges heat with the high-temperature heat exchanger HX1 of the air pipeline, and jointly further cools the high-temperature air.
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