CN110735678A - power cycle system for independent air propulsion device - Google Patents

power cycle system for independent air propulsion device Download PDF

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Publication number
CN110735678A
CN110735678A CN201911233619.6A CN201911233619A CN110735678A CN 110735678 A CN110735678 A CN 110735678A CN 201911233619 A CN201911233619 A CN 201911233619A CN 110735678 A CN110735678 A CN 110735678A
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CN
China
Prior art keywords
inlet
outlet
oxygen
carbon dioxide
fuel
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Pending
Application number
CN201911233619.6A
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Chinese (zh)
Inventor
郑开云
黄志强
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Shanghai Power Equipment Research Institute Co Ltd
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Shanghai Power Equipment Research Institute Co Ltd
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Priority to CN201911233619.6A priority Critical patent/CN110735678A/en
Publication of CN110735678A publication Critical patent/CN110735678A/en
Pending legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/10—Adaptations for driving, or combinations with, electric generators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K25/00—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for
    • F01K25/08—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours
    • F01K25/10—Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
    • F01K25/103—Carbon dioxide
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K7/00—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating
    • F01K7/32—Steam engine plants characterised by the use of specific types of engine; Plants or engines characterised by their use of special steam systems, cycles or processes; Control means specially adapted for such systems, cycles or processes; Use of withdrawn or exhaust steam for feed-water heating the engines using steam of critical or overcritical pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/44—Preheating devices; Vaporising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2202/00—Liquid fuel burners

Abstract

The invention discloses power cycle systems for air-independent propulsion units, which comprise a fuel tank, a fuel preheater, a liquid oxygen tank, a liquid oxygen gasifier, an oxygen preheater, a combustion chamber, a high-pressure turbine, a high-temperature regenerator, a low-temperature regenerator, a th separator, a condenser, a low-pressure turbine and a second separator, wherein a fuel inlet of the fuel preheater is communicated with a fuel outlet of the fuel tank, an oxygen inlet of the liquid oxygen gasifier is communicated with an oxygen outlet of the liquid oxygen tank, and a carbon dioxide outlet of the liquid oxygen gasifier is communicated with an inlet of a liquid carbon dioxide tank for storing liquid carbon dioxide.

Description

power cycle system for independent air propulsion device
Technical Field
The invention relates to the technical field of power circulation systems, in particular to power circulation systems independent of an air propulsion device.
Background
The conventional submarine usually supplies power for a propulsion motor through a diesel generator and a storage battery, the diesel engine cannot work due to the fact that air does not exist when the submarine sails underwater, the storage battery is used for supplying power, and due to the fact that the storage capacity is limited, the submarine needs to frequently float out of the water surface and is charged by the diesel engine, and adverse effects are brought to concealment. In order to ensure that the submarine can sail under the water surface for a long time without floating out of the water surface for charging, the 'independent air propulsion device' is equipped with the conventional submarine, does not depend on oxygen carried on the submarine in the running process of the air propulsion device, and does not need to obtain oxygen from the air.
At present, the power systems independent of the air propulsion device are mainly divided into four types, namely a stirling engine, a fuel cell, a closed cycle diesel engine, a closed cycle steam turbine and the like, but still face new requirements of deeper latency, faster navigation speed, quieter performance and the like, and the development of efficient systems independent of the air propulsion device is far from the task.
In recent years, advanced supercritical carbon dioxide circulation power generation technology appears in the power generation field, the thermodynamic circulation efficiency is greatly improved, the supercritical carbon dioxide circulation adopts carbon dioxide as a working medium, the carbon dioxide is inert in chemical property, colorless, tasteless, nontoxic, safe, low in price and easy to obtain, and is excellent natural working media, when the submarine works at the temperature of over 900 ℃, the thermal efficiency of the supercritical carbon dioxide circulation can reach over 55 percent and can be comparable with a fuel cell.
Disclosure of Invention
In order to solve the problems in the prior art, the invention aims to provide power cycle systems which are used for a power cycle system independent of an air propulsion device, have reasonable design and simple structure, and can ensure that the heat generated by the combustion of fuel and oxygen in a combustion chamber is absorbed by a supercritical carbon dioxide working medium, the temperature of the supercritical carbon dioxide working medium can reach over 900 ℃, and the thermal efficiency of the supercritical carbon dioxide cycle can be improved to over 55%.
In order to solve the technical problems, the invention adopts the following technical scheme:
A power cycle system for an air propulsion independent device, comprising
a fuel tank for storing fuel;
a fuel preheater for preheating fuel output from the fuel tank, the fuel inlet of the fuel preheater being in communication with the fuel outlet of the fuel tank;
a liquid oxygen tank for storing liquid oxygen;
a liquid oxygen gasifier for gasifying the liquid oxygen output from the liquid oxygen tank, wherein the oxygen inlet of the liquid oxygen gasifier is communicated with the oxygen outlet of the liquid oxygen tank, and the carbon dioxide outlet of the liquid oxygen gasifier is communicated with the inlet of a liquid carbon dioxide tank for storing liquid carbon dioxide;
an oxygen preheater for preheating the oxygen output from the liquid oxygen gasifier, the oxygen inlet of the oxygen preheater is communicated with the oxygen outlet of the liquid oxygen gasifier;
a combustion chamber for burning fuel and oxygen in carbon dioxide working medium, the fuel inlet of the combustion chamber is communicated with the fuel outlet of the fuel preheater, the oxygen inlet of the combustion chamber is communicated with the oxygen outlet of the oxygen preheater;
is used for driving the electric generator to generate electricity to start the high pressure turbine of the compressor, the air inlet of the high pressure turbine is communicated with the air outlet of the combustion chamber, the air outlet of the high pressure turbine is communicated with the air inlet of the fuel preheater;
a high-temperature regenerator for recovering heat of carbon dioxide working medium discharged from the high-pressure turbine, wherein the low-pressure side inlet of the high-temperature regenerator is communicated with the gas outlet of the fuel preheater, the high-pressure side outlet of the high-temperature regenerator is communicated with the carbon dioxide working medium inlet of the combustion chamber, and the high-pressure side inlet of the high-temperature regenerator is communicated with the outlet of the compressor;
a low-temperature regenerator for recovering heat of carbon dioxide working medium discharged from the high-temperature regenerator, wherein the low-pressure side inlet of the low-temperature regenerator is communicated with the low-pressure side outlet of the high-temperature regenerator, the high-pressure side outlet of the low-temperature regenerator is communicated with the high-pressure side inlet of the high-temperature regenerator, and the high-pressure side inlet of the low-temperature regenerator is communicated with the carbon dioxide outlet of the liquid oxygen gasifier;
a separator for separating moisture carried in carbon dioxide working medium discharged from the low-temperature regenerator, wherein the inlet of the separator is communicated with the low-pressure side outlet of the low-temperature regenerator, and the outlet of the separator is communicated with the inlet of the compressor;
condenser for cooling and liquefying part of carbon dioxide working medium output from separator, wherein the inlet of the condenser is communicated with the outlet of separator, and the outlet of the condenser is communicated with the inlet of high pressure side of low temperature regenerator;
a low pressure turbine for driving a second generator to generate electricity, the inlet of the low pressure turbine being in communication with the second exhaust of the high pressure turbine, the outlet of the low pressure turbine being in communication with the carbon dioxide inlet of the oxygen preheater;
a second separator for separating the moisture carried in the carbon dioxide working medium output from the oxygen preheater, the inlet of the second separator is communicated with the carbon dioxide outlet of the oxygen preheater, and the outlet of the second separator is communicated with the carbon dioxide inlet of the liquid oxygen gasifier.
In preferred embodiments of the present invention, the power cycle system for an air independent propulsion device further comprises a fuel pump for delivering fuel in the fuel tank to the fuel preheater for preheating, the fuel inlet of the fuel pump being in communication with the fuel outlet of the fuel tank, and the fuel outlet of the fuel pump being in communication with the fuel inlet of the fuel preheater.
In preferred embodiments of the present invention, the power cycle system for independent air propulsion device further comprises a liquid oxygen pump for delivering liquid oxygen in the liquid oxygen tank to the liquid oxygen gasifier for gasification, wherein an oxygen inlet of the liquid oxygen pump is communicated with an oxygen outlet of the liquid oxygen tank, and an oxygen outlet of the liquid oxygen pump is communicated with an oxygen inlet of the liquid oxygen gasifier.
In preferred embodiments of the present invention, the power cycle system for independent air propulsion device further comprises a th carbon dioxide pump for delivering the liquid cooled and liquefied by the condenser to the low-temperature regenerator for low-temperature heating, wherein a liquid inlet of the th carbon dioxide pump is communicated with a liquid outlet of the condenser, and a liquid outlet of the th carbon dioxide pump is communicated with a high-pressure side inlet of the low-temperature regenerator;
second carbon dioxide pumps are arranged between the carbon dioxide outlet of the liquid oxygen gasifier and the liquid inlet of the carbon dioxide pump, the inlet of each second carbon dioxide pump is communicated with the carbon dioxide outlet of the liquid oxygen gasifier, and the outlet of each second carbon dioxide pump is communicated with the liquid inlet of the carbon dioxide pump.
Compared with the prior art, the heat generated by combustion of fuel and oxygen in the combustion chamber is absorbed by the supercritical carbon dioxide working medium, the high temperature of the combustion chamber can reach over 900 ℃, the heat efficiency of the supercritical carbon dioxide circulation can reach over 55 percent, and simultaneously, water and carbon dioxide generated by combustion can be collected.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a control schematic diagram of the present invention.
Detailed Description
In order to make the technical means, the original characteristics, the achievement purposes and the functions of the invention easy to understand, the invention is further described in combination with the detailed drawings.
Referring to fig. 1, there are shown power cycle systems for an air independent propulsion device, including a fuel tank 100, a fuel preheater 200, a liquid oxygen tank 300, a liquid oxygen gasifier 400, an oxygen preheater 500, a combustion chamber 600, a high pressure turbine 700, a high temperature regenerator 800, a low temperature regenerator 900, a th separator 1000, a condenser 1100, a low pressure turbine 1200 and a second separator 1300, a th generator 1400, a second generator 1500, a fuel pump 1600, a compressor 1700, a liquid oxygen pump 1800, a liquid carbon dioxide tank 1900, a second carbon dioxide pump 2000, a th carbon dioxide pump 2100.
The fuel tank 100 stores fuel, the fuel preheater 200 preheats the fuel output from the fuel tank 100, a fuel inlet of the fuel preheater 200 is communicated with a fuel outlet of the fuel tank 100, and the liquid oxygen tank 300 stores liquid oxygen.
The fuel pump 1600 is used to deliver fuel in the fuel tank 100 to the fuel preheater 200 for preheating, a fuel inlet of the fuel pump 1600 is communicated with a fuel outlet of the fuel tank 100, and a fuel outlet of the fuel pump 1600 is communicated with a fuel inlet of the fuel preheater 200.
The liquid oxygen vaporizer 300 is used to vaporize liquid oxygen output from the liquid oxygen tank 300, an oxygen inlet of the liquid oxygen vaporizer 400 is communicated with an oxygen outlet of the liquid oxygen tank 300, and a carbon dioxide outlet of the liquid oxygen vaporizer 300 is communicated with an inlet of the liquid carbon dioxide tank 1900 for storing liquid carbon dioxide.
The liquid oxygen pump 1800 is used for conveying liquid oxygen in the liquid oxygen tank 300 into the liquid oxygen gasifier 400 for gasification, an oxygen inlet of the liquid oxygen pump 1800 is communicated with an oxygen outlet of the liquid oxygen tank 300, and an oxygen outlet of the liquid oxygen pump 1800 is communicated with an oxygen inlet of the liquid oxygen gasifier 400.
The oxygen preheater 500 is used for preheating the oxygen output from the liquid oxygen gasifier 400, the oxygen inlet of the oxygen preheater 500 is communicated with the oxygen outlet of the liquid oxygen gasifier 400, the combustion chamber 600 is used for combusting fuel and oxygen in carbon dioxide working medium, the fuel inlet of the combustion chamber 600 is communicated with the fuel outlet of the fuel preheater 500, and the oxygen inlet of the combustion chamber 600 is communicated with the oxygen outlet of the oxygen preheater 500.
The high pressure turbine 700 is used to drive the th generator 1400 to generate electricity to start the compressor 1700, the inlet of the high pressure turbine 1400 is connected to the outlet of the combustion chamber 600, and the th outlet of the high pressure turbine 1400 is connected to the inlet of the fuel preheater 200.
The high-temperature heat regenerator 800 is used for recovering heat of carbon dioxide working medium discharged by the high-pressure turbine 700, a low-pressure side inlet of the high-temperature heat regenerator 800 is communicated with an air outlet of the fuel preheater 200, a high-pressure side outlet of the high-temperature heat regenerator 800 is communicated with a carbon dioxide working medium inlet of the combustion chamber 600, and a high-pressure side inlet of the high-temperature heat regenerator 800 is communicated with an outlet of the compressor 1700.
The low-temperature regenerator 900 is used for recovering heat of carbon dioxide working medium discharged by the high-temperature regenerator 800, a low-pressure side inlet of the low-temperature regenerator 900 is communicated with a low-pressure side outlet of the high-temperature regenerator 800, a high-pressure side outlet of the low-temperature regenerator 900 is communicated with a high-pressure side inlet of the high-temperature regenerator 800, and a high-pressure side inlet of the low-temperature regenerator 900 is communicated with a carbon dioxide outlet of the liquid oxygen gasifier 400.
The th separator 1000 is used for separating moisture carried in carbon dioxide working medium discharged from the low temperature regenerator 800, an inlet of the th separator 1000 is communicated with an outlet on the low pressure side of the low temperature regenerator 900, and an outlet of the th separator 1000 is communicated with an inlet of the compressor 1700.
The condenser 1100 is used for cooling and liquefying part of the carbon dioxide working medium output from the th separator 1000, an inlet of the condenser 1100 is communicated with an outlet of the th separator 1000, and an outlet of the condenser 1000 is communicated with a high-pressure side inlet of the low-temperature heat regenerator 900.
The carbon dioxide pump 2100 is used to deliver the liquid cooled and liquefied by the condenser 1100 to the low-temperature heat regenerator 900 for low-temperature heating, the liquid inlet of the carbon dioxide pump 2100 is communicated with the liquid outlet of the condenser 1100, and the liquid outlet of the carbon dioxide pump 2100 is communicated with the high-pressure side inlet of the low-temperature heat regenerator 900.
second carbon dioxide pump 2000 is arranged between the carbon dioxide outlet of the liquid oxygen gasifier 400 and the liquid inlet of the carbon dioxide pump 2100, the inlet of the second carbon dioxide pump 2000 is communicated with the carbon dioxide outlet of the liquid oxygen gasifier 400, and the outlet of the second carbon dioxide pump 2000 is communicated with the liquid inlet of the carbon dioxide pump 2100.
The low pressure turbine 1200 is used to drive the second generator 1500 to generate electricity, the inlet of the low pressure turbine 1200 is connected to the second exhaust of the high pressure turbine 700, and the outlet of the low pressure turbine 1200 is connected to the carbon dioxide inlet of the oxygen preheater 500.
The second separator 1300 is used for separating moisture carried in the carbon dioxide working medium output from the oxygen preheater 500, an inlet of the second separator 1300 is communicated with a carbon dioxide outlet of the oxygen preheater 1300, and an outlet of the second separator 1300 is communicated with a carbon dioxide inlet of the liquid oxygen gasifier 400.
The specific working principle of the invention is as follows:
when the system operates, carbon dioxide operates circularly, a carbon dioxide pump 2100 boosts a liquid carbon dioxide working medium to about 16MPa, the boosted carbon dioxide working medium enters a low-temperature heat regenerator 900 to be heated to about 130 ℃, then paths of carbon dioxide working medium boosted by a compressor 1700 are converged and enter a high-temperature heat regenerator 800, the carbon dioxide working medium is heated to about 700 ℃ by the high-temperature heat regenerator 800, then enters a combustion chamber 600 to be heated to 900 ℃, then enters a high-pressure turbine 700 to be expanded to about 6MPa, the high-pressure turbine 700 pushes a 0 generator 1400 to generate electric power, paths in exhaust gas of the high-pressure turbine 700 sequentially pass through a fuel preheater 200, the high-temperature heat regenerator 800 and a low-temperature heat regenerator 900 to release waste heat, then pass through a separator 1000 to separate moisture, an outlet working medium of a separator 1000 is divided into two paths, a path enters a compressor to be pressurized and enter a high-temperature regenerator 900, another path 4 path is liquefied by a condenser 1100 and then returns to a carbon dioxide pump 2100, another path in exhaust gas of the high-pressure turbine 700 enters a low-pressure turbine 1200, the low-pressure turbine 700 to enter a low-pressure-turbine 200, the low-pressure-oxygen-liquid-combustion-liquid-gasifying device, the tail gas is gasified from a low-liquid-gasifying device, the tail gas-.
In the embodiment, the supercritical carbon dioxide circulation efficiency is about 55-57%, and in order to improve the circulation efficiency in step , the inlet temperature of the high-pressure turbine 2 can be increased, such as 1000 ℃, and the circulation efficiency can reach more than 60%, so that the underwater endurance mileage of the submarine can be prolonged.
To sum up, the heat generated by the combustion of the fuel and the oxygen in the combustion chamber is absorbed by the supercritical carbon dioxide working medium, so that the temperature of the supercritical carbon dioxide working medium can reach a high temperature of over 900 ℃, the heat efficiency of the supercritical carbon dioxide circulation can reach over 55 percent, and simultaneously, the water and the carbon dioxide generated by the combustion can be collected.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are given by way of illustration of the principles of the present invention, and that various changes and modifications may be made without departing from the spirit and scope of the invention as defined by the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims (4)

  1. A power cycle system for an air independent propulsion device, comprising
    a fuel tank for storing fuel;
    a fuel preheater for preheating fuel output from the fuel tank, the fuel inlet of the fuel preheater being in communication with the fuel outlet of the fuel tank;
    a liquid oxygen tank for storing liquid oxygen;
    a liquid oxygen gasifier for gasifying the liquid oxygen output from the liquid oxygen tank, wherein the oxygen inlet of the liquid oxygen gasifier is communicated with the oxygen outlet of the liquid oxygen tank, and the carbon dioxide outlet of the liquid oxygen gasifier is communicated with the inlet of a liquid carbon dioxide tank for storing liquid carbon dioxide;
    an oxygen preheater for preheating the oxygen output from the liquid oxygen gasifier, the oxygen inlet of the oxygen preheater is communicated with the oxygen outlet of the liquid oxygen gasifier;
    a combustion chamber for burning fuel and oxygen in carbon dioxide working medium, the fuel inlet of the combustion chamber is communicated with the fuel outlet of the fuel preheater, the oxygen inlet of the combustion chamber is communicated with the oxygen outlet of the oxygen preheater;
    is used for driving the electric generator to generate electricity to start the high pressure turbine of the compressor, the air inlet of the high pressure turbine is communicated with the air outlet of the combustion chamber, the air outlet of the high pressure turbine is communicated with the air inlet of the fuel preheater;
    a high-temperature regenerator for recovering heat of carbon dioxide working medium discharged from the high-pressure turbine, wherein the low-pressure side inlet of the high-temperature regenerator is communicated with the gas outlet of the fuel preheater, the high-pressure side outlet of the high-temperature regenerator is communicated with the carbon dioxide working medium inlet of the combustion chamber, and the high-pressure side inlet of the high-temperature regenerator is communicated with the outlet of the compressor;
    a low-temperature regenerator for recovering heat of carbon dioxide working medium discharged from the high-temperature regenerator, wherein the low-pressure side inlet of the low-temperature regenerator is communicated with the low-pressure side outlet of the high-temperature regenerator, the high-pressure side outlet of the low-temperature regenerator is communicated with the high-pressure side inlet of the high-temperature regenerator, and the high-pressure side inlet of the low-temperature regenerator is communicated with the carbon dioxide outlet of the liquid oxygen gasifier;
    a separator for separating moisture carried in carbon dioxide working medium discharged from the low-temperature regenerator, wherein the inlet of the separator is communicated with the low-pressure side outlet of the low-temperature regenerator, and the outlet of the separator is communicated with the inlet of the compressor;
    condenser for cooling and liquefying part of carbon dioxide working medium output from separator, wherein the inlet of the condenser is communicated with the outlet of separator, and the outlet of the condenser is communicated with the inlet of high pressure side of low temperature regenerator;
    a low pressure turbine for driving a second generator to generate electricity, the inlet of the low pressure turbine being in communication with the second exhaust of the high pressure turbine, the outlet of the low pressure turbine being in communication with the carbon dioxide inlet of the oxygen preheater;
    a second separator for separating the moisture carried in the carbon dioxide working medium output from the oxygen preheater, the inlet of the second separator is communicated with the carbon dioxide outlet of the oxygen preheater, and the outlet of the second separator is communicated with the carbon dioxide inlet of the liquid oxygen gasifier.
  2. 2. The power cycle system for an air independent propulsion device as claimed in claim 1, further comprising a fuel pump for delivering fuel in the fuel tank to the fuel preheater for preheating, the fuel inlet of the fuel pump being in communication with the fuel outlet of the fuel tank, the fuel outlet of the fuel pump being in communication with the fuel inlet of the fuel preheater.
  3. 3. The kind of power cycle system for air independent propulsion device, as claimed in claim 1, further comprising liquid oxygen pump for delivering liquid oxygen in liquid oxygen tank to the liquid oxygen gasifier for gasification, wherein the oxygen inlet of the liquid oxygen pump is connected to the oxygen outlet of the liquid oxygen tank, and the oxygen outlet of the liquid oxygen pump is connected to the oxygen inlet of the liquid oxygen gasifier.
  4. 4. The kind of power cycle system for air-independent propulsion unit as claimed in claim 1, further comprising a carbon dioxide pump for delivering the liquid cooled and liquefied by the condenser to the low-temperature regenerator for low-temperature heating, wherein the liquid inlet of the carbon dioxide pump is connected to the liquid outlet of the condenser, and the liquid outlet of the carbon dioxide pump is connected to the high-pressure side inlet of the low-temperature regenerator;
    second carbon dioxide pumps are arranged between the carbon dioxide outlet of the liquid oxygen gasifier and the liquid inlet of the carbon dioxide pump, the inlet of each second carbon dioxide pump is communicated with the carbon dioxide outlet of the liquid oxygen gasifier, and the outlet of each second carbon dioxide pump is communicated with the liquid inlet of the carbon dioxide pump.
CN201911233619.6A 2019-12-05 2019-12-05 power cycle system for independent air propulsion device Pending CN110735678A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201911233619.6A CN110735678A (en) 2019-12-05 2019-12-05 power cycle system for independent air propulsion device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201911233619.6A CN110735678A (en) 2019-12-05 2019-12-05 power cycle system for independent air propulsion device

Publications (1)

Publication Number Publication Date
CN110735678A true CN110735678A (en) 2020-01-31

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN201911233619.6A Pending CN110735678A (en) 2019-12-05 2019-12-05 power cycle system for independent air propulsion device

Country Status (1)

Country Link
CN (1) CN110735678A (en)

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