CN113202576A - Nuclear power propeller type aircraft engine - Google Patents
Nuclear power propeller type aircraft engine Download PDFInfo
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- CN113202576A CN113202576A CN202110660025.4A CN202110660025A CN113202576A CN 113202576 A CN113202576 A CN 113202576A CN 202110660025 A CN202110660025 A CN 202110660025A CN 113202576 A CN113202576 A CN 113202576A
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- 239000002826 coolant Substances 0.000 claims abstract description 60
- 238000006243 chemical reaction Methods 0.000 claims abstract description 35
- 230000005540 biological transmission Effects 0.000 claims abstract description 25
- 239000003638 chemical reducing agent Substances 0.000 claims abstract description 24
- 239000007789 gas Substances 0.000 claims description 27
- 238000001816 cooling Methods 0.000 claims description 8
- 239000000446 fuel Substances 0.000 claims description 8
- AFAUWLCCQOEICZ-UHFFFAOYSA-N helium xenon Chemical compound [He].[Xe] AFAUWLCCQOEICZ-UHFFFAOYSA-N 0.000 claims description 8
- 239000003570 air Substances 0.000 claims description 6
- 230000007246 mechanism Effects 0.000 claims description 6
- 230000009347 mechanical transmission Effects 0.000 claims description 5
- 239000012080 ambient air Substances 0.000 claims description 4
- 239000003758 nuclear fuel Substances 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 239000000919 ceramic Substances 0.000 claims description 2
- 230000004992 fission Effects 0.000 abstract description 6
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
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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
- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
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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
- F01K21/00—Steam engine plants not otherwise provided for
-
- 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
- F01K27/00—Plants for converting heat or fluid energy into mechanical energy, not otherwise provided for
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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
- F01K9/00—Plants characterised by condensers arranged or modified to co-operate with the engines
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a nuclear power propeller type aircraft engine.A gas coolant absorbs heat in a reactor, then enters a turbine to do work, then enters a heat regenerator at a high temperature side to release heat, fully exchanges heat with a coolant at a low temperature side, then flows out of the heat regenerator to enter a cooler, continues to release heat in the cooler, then enters a compressor to be compressed, most of the coolant enters the heat regenerator again after being compressed, and flows back to a reactor core after absorbing heat. The rotation of the compressor drives the clutch to move, the clutch is connected with the speed reducer through the transmission shaft, and after the clutch and the speed reducer jointly complete torque adjustment, the speed reducer drives the propeller engine to rotate. The nuclear power propeller type aircraft engine realizes the high-efficiency conversion of reactor fission energy and heat energy and mechanical energy through a simple and direct power transmission process.
Description
Technical Field
The invention relates to a nuclear power engine device, in particular to a nuclear power propeller type aircraft engine, and belongs to the field of nuclear reactor engineering technology and power device design.
Background
A nuclear reactor is a device that converts nuclear fission energy into thermal energy. Reactor types can be broadly classified into water-cooled reactors, gas-cooled reactors, and liquid metal-cooled reactors, depending on the coolant type. The gas-cooled fast reactor can realize higher reactor core outlet temperature, and has high reactor efficiency and smaller weight and volume. The helium-xenon mixed gas has excellent thermodynamic performance and high heat transfer capacity, can obtain better gas compression performance when being mixed according to a proper proportion, and is suitable for being used as a coolant of gas-cooled fast reactors.
The brayton cycle is a thermodynamic cycle that relies on moving parts to effect the conversion of thermal energy to other forms of energy. In the complete ideal Brayton cycle process, low-temperature and low-pressure gas is adiabatically compressed in a compressor, enters a reactor after being preheated by high-temperature side fluid of a heat regenerator, enters a turbine for adiabatic expansion to do work after isobaric heat absorption and temperature rise, drives a generator to generate electricity, and after a high-temperature gas coolant which does work is isobaric heat release and cooling by the low-pressure side fluid of the heat regenerator, the high-temperature gas coolant is isobaric heat release and cooling by a cooler to the required inlet temperature of the compressor and enters the compressor to form closed cycle. Generally, the Brayton cycle device has the advantages of simple structure, small volume and cycle efficiency obviously higher than that of static energy conversion, and is suitable for carrying mobile equipment.
Most of the traditional general airplanes adopt propellers as power devices, the force generated by the rotation of the propellers is used as the advancing propelling force of the airplane, and the traditional general airplanes have the advantages of low oil consumption, easy operation, high efficiency, good pneumatic performance and the like. The method can achieve stronger flight performance after pertinently optimizing and designing the characteristics of the propeller and the type of the airplane wing, and achieves excellent engine cost benefit.
Currently, aircraft propellers are typically combined with piston engines or gas turbine engines. The piston engine realizes power output by means of reciprocating motion of the piston, has the characteristics of direct principle, simple structure, low cost and the like, is limited by the number of cylinders and the capacity of the cylinders, generally limits the power to below four thousand horsepower, and is generally only suitable for small airplanes. Compared with a piston engine, the gas turbine engine reduces reciprocating parts, improves the operation stability, reduces the noise level, has the maximum power exceeding ten thousand horsepower, and can be suitable for large and medium-sized airplanes. However, due to the limitation of self fuel oil carrying weight, the long-time dead space capability of the aircraft is relatively common, the applicability to long-range tasks is defective, and the time, type and capability of the aircraft for executing the tasks are greatly limited.
Disclosure of Invention
The invention aims to provide a nuclear power propeller type aircraft engine which is light, small, compact, high in applicability, safe and reliable, and can overcome the problems that a piston power device is low in operation power and a gas turbine power device is limited in endurance mileage.
The purpose of the invention is realized as follows: the direct Brayton cycle reactor comprises a fixed base, and a reactor system, an energy conversion system and a power output system which are arranged on the fixed base, wherein the reactor system is connected with the energy conversion system through a pipeline to form a direct Brayton cycle; the energy conversion system transmits power to the power output system in a mechanical transmission mode; the reactor system comprises a reactor body and a connecting pipeline, wherein the reactor body comprises a pressure vessel, a reactor core, control rods, a control rod driving mechanism and an in-reactor component; the energy conversion system comprises two energy conversion systems which comprise a turbine, a heat regenerator, a cooler, a compressor and a connecting pipeline, wherein the two energy conversion systems share one heat regenerator and one cooler, the turbine is connected with the pressure vessel through a core outlet heat pipe section connecting pipe, the heat regenerator is a surface type heat regenerator, the high-temperature side of the heat regenerator is connected with the outlet of the turbine and the inlet of the cooler, the low-temperature side of the heat regenerator is connected with the outlet of a reactor cold pipe section and the outlet of the compressor, and the flowing directions of working mediums at two sides are opposite; the cooler is a surface cooler, the coolant flows in a pipeline inside the cooler, the ambient air flows outside the pipeline, and the external air and the coolant in the pipeline flow in opposite directions; the power output system comprises a transmission shaft, a clutch, a speed reducer and a propeller, wherein the clutch is a friction clutch, the power input end of the clutch is connected with the compressor, and the power output end of the clutch is connected with the transmission shaft of the transmission device; the speed reducer is a gear speed reducer, the transmission shaft is used as a power input end, and the output end is connected with the propeller.
The invention also includes such structural features:
1. selecting high-enrichment ceramic UO2 fuel or UN fuel for reactor fuel; the cooling agent uses helium-xenon mixed gas, and the molar mass of the cooling agent is 10-45 g/mol.
2. The turbine is a helium xenon mixed gas turbine, and a multi-stage axial flow type or a single-stage centrifugal type can be used for the turbine.
3. The compressor can select an axial compressor or a centrifugal compressor according to specific design indexes, and the system uses a single compressor or a plurality of compressors to complete gas compression.
4. The turbine, compressor and clutch are arranged in a horizontal coaxial manner.
5. When the engine runs, the coolant passing through the compressor and the heat regenerator flows into the reactor core through the connecting pipe of the cold pipe section at the inlet of the reactor, flows out of the reactor core through the heat pipe section after being heated by the fuel of the reactor, and enters the energy conversion system; the coolant flows out from the heat pipe section of the reactor and then enters the turbine to expand and do work, the work is done and then enters the high-temperature side of the heat regenerator through a pipeline from the outlet of the turbine, the heat is fully exchanged with the coolant which flows back to the reactor from the compressor in the heat regenerator, the heat is transferred from the high-temperature gas coolant to the low-temperature coolant which is cooled and compressed, and the cooling of the high-temperature gas coolant and the heating of the coolant which flows back to the reactor core are realized; the heat-exchanged coolant flows into the cooler through a heat regenerator outlet connecting pipe, the cooler is directly connected with the atmosphere through a pipeline, and the atmosphere is used as a final heat sink to cool the coolant; the cooled coolant enters the compressor through a cooler outlet connecting pipe, flows out of the compressor outlet connecting pipe after being compressed in the compressor, enters the low-temperature side of the heat regenerator again, is heated by the turbine outlet high-temperature gas coolant in the heat regenerator, and then flows back to the reactor core through the reactor cold pipe section to complete the whole Brayton cycle; when the engine works, the coaxially arranged compressor drives the clutch through the compressor-clutch transmission shaft, the clutch transmits the power of the energy conversion system to the clutch-reducer transmission shaft with proper torque, and the reducer drives the propeller engine to rotate through the reducer-propeller transmission shaft after further torque adjustment is realized, so that the aircraft is driven to move.
Compared with the prior art, the invention has the beneficial effects that: the invention realizes the conversion from reactor fission energy to heat energy to mechanical energy through the Brayton energy conversion system, and directly transmits the energy to the propeller through the power output system consisting of the clutch, the transmission shaft and the speed reducer, and the energy utilization process of the system is simple and direct. The mechanical transmission structure is completely used, the maturity of each subsystem is high, and the whole system is simple and reliable; in the running process of the engine, the rotating speed of the propeller can be maintained in an optimal speed range through the matching of the clutch and the speed reducer, the power of the reactor is not greatly adjusted, the characteristic can reduce the requirement of the reactor on load tracking capacity under the condition of ensuring the response speed of the system, the action frequency of a reactor control system is greatly reduced, and thermal shock brought to structural materials by frequent temperature change is reduced, so that the service life of the reactor system is prolonged; the helium-xenon mixed gas is adopted as the circulating working medium of the Brayton energy conversion system, so that the thermodynamic property is excellent, the compressibility is good, a higher temperature parameter at the outlet of the reactor is ensured, the limitation on the number of stages of a compressor is effectively reduced, the energy conversion system of the nuclear power engine is integrally compact, and the good adaptability of the system in an aircraft is ensured; according to specific engineering requirements, a single or a plurality of Brayton circulation loops can drive a single propeller, so that even if one Brayton circulation loop breaks down, the engine still can not lose power, and the operation safety of the system is ensured.
Drawings
FIG. 1 is a front view of a nuclear powered engine system configuration of the present invention;
FIG. 2 is a top view of the nuclear power engine system configuration of the present invention;
fig. 3 is a schematic diagram of the system.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
With reference to fig. 1-2, the invention provides a nuclear power propeller type aircraft engine, which comprises a reactor system, an energy conversion system, a power output system and a connecting pipeline. The reactor system is connected with the energy conversion system through a pipeline to form a direct Brayton cycle; the energy conversion system transmits power to the power output system in a mechanical transmission manner. The reactor comprises a pressure vessel 1, reactor core fuel 2, control rods and a driving mechanism 3 thereof, a reactor core inlet cold pipe section connecting pipe 15 and two reactor core outlet hot pipe section connecting pipes 8. The pressure vessel 1 is connected with the core outlet side of the heat regenerator 5 through a core inlet cold pipe section connecting pipe 15, and is connected with the inlet of the turbine 4 through a reactor outlet hot pipe section connecting pipe 8. The control rod and the control rod driving mechanism 3 are positioned at the end part of the reactor pressure vessel 1, the driving mechanism drives the control rod to move through electric power during working, the reactor power is adjusted, the fuel rod 2 is positioned in the pressure vessel, and heat released by fission of nuclear fuel is taken away by coolant during normal working. When the engine is running, the coolant passing through the compressor and the heat regenerator flows into the reactor core through the reactor inlet cold pipe section connecting pipe 15, flows out of the reactor core through the heat pipe section 8 after being heated by the reactor fuel, and enters the energy conversion system. The two reactor core outlet heat pipe section connecting pipes 8 are respectively connected with two sets of independent energy conversion systems, any one independent system fails in the operation process, and the other system can still ensure normal operation to complete energy conversion.
The single energy conversion system comprises a turbine 4, a regenerator 5, a cooler 6, a compressor 7, a turbine-compressor drive shaft 16 and connecting piping. The turbine is a helium-xenon mixed gas turbine, the turbine is horizontally arranged, and the coolant heated by the reactor core directly flows into the turbine to do work through expansion; the regenerator is a surface regenerator, the high-temperature side of the regenerator is connected with a turbine outlet and a cooler inlet, the low-temperature side of the regenerator is connected with a reactor cold pipe section and a compressor outlet, and the flow directions of working media on the two sides are opposite; the cooler is a surface cooler, the coolant flows in a pipeline inside the cooler, the ambient air flows outside the pipeline, and the external air and the coolant in the pipeline flow in opposite directions; wherein, two energy conversion systems share one regenerator 5 and one cooler 6. The coolant flows out from the heat pipe section of the reactor and then enters the turbine 4 to expand and do work, the work is done and then enters the high-temperature side of the heat regenerator from the outlet of the turbine through the pipeline 9, the heat is fully exchanged with the coolant which flows back to the reactor from the compressor in the heat regenerator, the heat is transferred from the high-temperature gas coolant to the low-temperature coolant which is cooled and compressed, and the cooling of the high-temperature gas coolant and the heating of the coolant which flows back to the reactor core are realized. The cold and hot coolants in the surface type regenerator are physically isolated from each other, and the flow directions of the cold and hot coolants are opposite to each other so as to realize high-efficiency heat exchange. The heat-exchanged coolant flows into the cooler 6 through a regenerator outlet connecting pipe 10, the cooler is directly connected with the atmosphere through pipelines 11 and 12, and the atmosphere is used as a final heat sink to cool the coolant. The cooler is a surface heat exchanger, air enters through an inlet connecting pipe 11, the air is discharged through an outlet connecting pipe 12 after cooling the coolant, heat is transferred to ambient air with lower temperature through high-temperature coolant needing cooling, and the flowing direction of external cooling air is opposite to that of internal coolant, so that a good heat exchange effect is achieved. The cooled coolant enters the compressor 7 through the cooler outlet connecting pipe 13, flows out through the compressor outlet connecting pipe 14 after being compressed in the compressor, enters the low-temperature side of the heat regenerator again, is heated by the turbine outlet high-temperature gas coolant in the heat regenerator, and then flows back to the reactor core through the reactor cold pipe section 15, so that the whole Brayton cycle is completed.
The power take-off system comprises a clutch 18, a retarder 20, a propeller engine 22, a compressor-clutch drive shaft 17, a clutch-retarder drive shaft 19 and a retarder-propeller drive shaft 21. The clutch is a friction clutch, the power input end of the clutch is connected with the compressor, and the power output end of the clutch is connected with the transmission shaft of the transmission device; the speed reducer is a gear speed reducer, the transmission shaft is used as a power input end, and the output end is connected with the propeller. The reactor is used as an energy source of an engine system, and the mechanical energy required by the system operation is converted from the nuclear fission energy of the reactor. The difference between the work done by the turbine and the work consumed by the compressor is used as the output work of the system, and the propeller engine is driven to work in a mechanical transmission mode. When the engine works, the coaxially arranged compressor 7 drives the clutch 18 through the compressor-clutch transmission shaft 17, the clutch 18 transmits the power of the energy conversion system to the clutch-reducer transmission shaft 19 with proper torque, and the reducer 20 drives the propeller engine 22 to rotate through the reducer-propeller transmission shaft 21 after further adjustment of the torque is realized, so that the aircraft is driven to move.
With reference to fig. 3, the system operating principle is: the gas coolant absorbs heat in the reactor, then enters the turbine to do work, then enters the high-temperature side of the heat regenerator to release heat, fully exchanges heat with the coolant at the low-temperature side, flows out of the heat regenerator to enter the cooler, continues to release heat in the cooler, then enters the compressor to be compressed, most of the coolant enters the heat regenerator again after being compressed, and flows back to the reactor core after absorbing heat. The rotation of the compressor drives the clutch to move, the clutch is connected with the speed reducer through the transmission shaft, and after the clutch and the speed reducer jointly complete torque adjustment, the speed reducer drives the propeller engine to rotate.
The nuclear power propeller type aircraft engine realizes the high-efficiency conversion of reactor fission energy and heat energy and mechanical energy through a simple and direct power transmission process. The power output system composed of the clutch, the reducer and the like is meshed with each other through gears with different gear ratios according to different operation conditions, so that the aircraft can be guaranteed to transmit proper driving force and torque to the engine under different motion conditions; the dual torque regulation provided by the clutch and the reducer can ensure the load tracking accuracy and sensitivity of the system under various working conditions, avoid the adverse effect of frequent actions of a reactor control system on the service life of a driving mechanism, and simultaneously reduce the thermal shock on a reactor loop material; the energy conversion system adopts helium-xenon mixed gas with excellent heat exchange performance and work-doing capacity as a working medium, has good thermodynamic performance and strong compressibility, ensures that the energy conversion system has small volume, light weight, high compactness and strong adaptability on different aircrafts; the two loops are arranged to provide higher redundancy for the system, and the two loops respectively have independent working capacity, so that the risk of failure of a single system is avoided, and the safety and the stability of system operation are greatly improved.
Claims (6)
1. A nuclear powered propeller type aircraft engine characterized in that: the direct Brayton cycle reactor comprises a fixed base, and a reactor system, an energy conversion system and a power output system which are arranged on the fixed base, wherein the reactor system is connected with the energy conversion system through a pipeline to form a direct Brayton cycle; the energy conversion system transmits power to the power output system in a mechanical transmission mode; the reactor system comprises a reactor body and a connecting pipeline, wherein the reactor body comprises a pressure vessel, a reactor core, control rods, a control rod driving mechanism and an in-reactor component; the energy conversion system comprises two energy conversion systems which comprise a turbine, a heat regenerator, a cooler, a compressor and a connecting pipeline, wherein the two energy conversion systems share one heat regenerator and one cooler, the turbine is connected with the pressure vessel through a core outlet heat pipe section connecting pipe, the heat regenerator is a surface type heat regenerator, the high-temperature side of the heat regenerator is connected with the outlet of the turbine and the inlet of the cooler, the low-temperature side of the heat regenerator is connected with the outlet of a reactor cold pipe section and the outlet of the compressor, and the flowing directions of working mediums at two sides are opposite; the cooler is a surface cooler, the coolant flows in a pipeline inside the cooler, the ambient air flows outside the pipeline, and the external air and the coolant in the pipeline flow in opposite directions; the power output system comprises a transmission shaft, a clutch, a speed reducer and a propeller, wherein the clutch is a friction clutch, the power input end of the clutch is connected with the compressor, and the power output end of the clutch is connected with the transmission shaft of the transmission device; the speed reducer is a gear speed reducer, the transmission shaft is used as a power input end, and the output end is connected with the propeller.
2. A nuclear powered propeller type aircraft engine according to claim 1, characterised in that: selecting high-enrichment ceramic UO2 fuel or UN fuel for reactor fuel; the cooling agent uses helium-xenon mixed gas, and the molar mass of the cooling agent is 10-45 g/mol.
3. A nuclear powered propeller type aircraft engine according to claim 1, characterised in that: the turbine is a helium xenon mixed gas turbine, and a multi-stage axial flow type or a single-stage centrifugal type can be used for the turbine.
4. A nuclear powered propeller type aircraft engine according to claim 1, characterised in that: the compressor can select an axial compressor or a centrifugal compressor according to specific design indexes, and the system uses a single compressor or a plurality of compressors to complete gas compression.
5. A nuclear powered propeller type aircraft engine according to claim 1, characterised in that: the turbine, compressor and clutch are arranged in a horizontal coaxial manner.
6. A nuclear powered propeller type aircraft engine according to any of claims 1 to 5, characterised in that: when the engine runs, the coolant passing through the compressor and the heat regenerator flows into the reactor core through the connecting pipe of the cold pipe section at the inlet of the reactor, flows out of the reactor core through the heat pipe section after being heated by the fuel of the reactor, and enters the energy conversion system; the coolant flows out from the heat pipe section of the reactor and then enters the turbine to expand and do work, the work is done and then enters the high-temperature side of the heat regenerator through a pipeline from the outlet of the turbine, the heat is fully exchanged with the coolant which flows back to the reactor from the compressor in the heat regenerator, the heat is transferred from the high-temperature gas coolant to the low-temperature coolant which is cooled and compressed, and the cooling of the high-temperature gas coolant and the heating of the coolant which flows back to the reactor core are realized; the heat-exchanged coolant flows into the cooler through a heat regenerator outlet connecting pipe, the cooler is directly connected with the atmosphere through a pipeline, and the atmosphere is used as a final heat sink to cool the coolant; the cooled coolant enters the compressor through a cooler outlet connecting pipe, flows out of the compressor outlet connecting pipe after being compressed in the compressor, enters the low-temperature side of the heat regenerator again, is heated by the turbine outlet high-temperature gas coolant in the heat regenerator, and then flows back to the reactor core through the reactor cold pipe section to complete the whole Brayton cycle; when the engine works, the coaxially arranged compressor drives the clutch through the compressor-clutch transmission shaft, the clutch transmits the power of the energy conversion system to the clutch-reducer transmission shaft with proper torque, and the reducer drives the propeller engine to rotate through the reducer-propeller transmission shaft after further torque adjustment is realized, so that the aircraft is driven to move.
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| CN202110660025.4A CN113202576B (en) | 2021-06-15 | 2021-06-15 | Nuclear power propeller type aircraft engine |
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