CN112392597A - Nuclear power engine device - Google Patents
Nuclear power engine device Download PDFInfo
- Publication number
- CN112392597A CN112392597A CN202011282798.5A CN202011282798A CN112392597A CN 112392597 A CN112392597 A CN 112392597A CN 202011282798 A CN202011282798 A CN 202011282798A CN 112392597 A CN112392597 A CN 112392597A
- Authority
- CN
- China
- Prior art keywords
- heat exchanger
- reactor
- compressor
- coolant
- air
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000002826 coolant Substances 0.000 claims abstract description 37
- 230000006835 compression Effects 0.000 claims abstract description 24
- 238000007906 compression Methods 0.000 claims abstract description 24
- 239000000446 fuel Substances 0.000 claims description 13
- 230000006978 adaptation Effects 0.000 abstract 1
- 238000006243 chemical reaction Methods 0.000 description 6
- 230000004992 fission Effects 0.000 description 3
- 239000000941 radioactive substance Substances 0.000 description 3
- 238000011109 contamination Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000002285 radioactive effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003758 nuclear fuel Substances 0.000 description 1
- 239000012857 radioactive material Substances 0.000 description 1
- 238000003904 radioactive pollution Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Images
Classifications
-
- 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
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
- F02C1/04—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
- F02C1/05—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy
-
- G—PHYSICS
- G21—NUCLEAR PHYSICS; NUCLEAR ENGINEERING
- G21D—NUCLEAR POWER PLANT
- G21D5/00—Arrangements of reactor and engine in which reactor-produced heat is converted into mechanical energy
- G21D5/02—Reactor and engine structurally combined, e.g. portable
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Engineering & Computer Science (AREA)
- High Energy & Nuclear Physics (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Plasma & Fusion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
本发明提供一种核动力发动机装置，包括固定基座以及安装在固定基座上的反应堆系统、换热器、一体化发动机以及连接管路；所述一体化发动机包括进气口、压缩机、换热器二次侧换热室、涡轮、排气口；所述换热器由互相隔离的两部分组成，换热器一次侧换热室通过管道连接反应堆系统出口和一体化发动机入口，换热器二次侧换热室连接一体化发动机压缩机空气出口和涡轮；所述压缩机由相互隔离的两部分构成，前端为一回路冷却剂压缩段，后端为空气压缩段。本发明一体化设计缩小反应堆系统体积，免去了一回路压缩机，使核动力发动机系统整体紧凑，能够更好实现核动力发动机与飞行器适配，系统运行更加简单方便。
The invention provides a nuclear power engine device, comprising a fixed base, a reactor system mounted on the fixed base, a heat exchanger, an integrated engine and a connecting pipeline; the integrated engine includes an air inlet, a compressor, The heat exchange chamber on the secondary side of the heat exchanger, the turbine, and the exhaust port; the heat exchanger is composed of two parts isolated from each other, and the heat exchange chamber on the primary side of the heat exchanger is connected to the reactor system outlet and the integrated engine inlet through pipes, and the The heat exchange chamber on the secondary side of the heat exchanger is connected to the air outlet of the integrated engine compressor and the turbine; the compressor is composed of two parts isolated from each other, the front end is the primary circuit coolant compression section, and the rear end is the air compression section. The integrated design of the invention reduces the volume of the reactor system, eliminates the primary circuit compressor, makes the nuclear power engine system compact as a whole, can better realize the adaptation of the nuclear power engine and the aircraft, and the system operation is simpler and more convenient.
Description
Technical Field
The invention relates to the field of nuclear reactor engineering technology and power plant design, in particular to a nuclear power engine device.
Background
The peaceful utilization of nuclear energy can be realized by artificially controlling the speed of the chain fission reaction. A great deal of heat can be released in the fission reaction, the atomic energy generated in the fission process is converted into heat energy by the reactor, the heat energy is carried away by the coolant and is transmitted to the power device through the energy conversion device, and finally the heat energy is converted into mechanical energy to generate thrust to drive the aircraft to fly.
Conventional aircraft engines use jet fuel as the fuel, and aircraft are limited by fuel carrying capacity, typically only hundreds to thousands of kilometers. The nuclear power engine has extremely high energy density, a reactor with hundreds of megawatts of power only needs a space of a few cubic meters, and the demonstration shows that the parameters of the nuclear power engine, such as weight, volume and the like, can meet the bearing requirements of the aircraft, so that the nuclear power engine can be well adapted to the aircraft. And the nuclear fuel has long service life, and can maintain the output power for several months or even years through reasonable design, which endows the reactor with long-time and great energy output capability, so that the aircraft using the nuclear power engine can realize extremely long voyage.
At present, for nuclear power engine devices adapted to ground and ship gas turbines, aviation turbofan engines, turbojet engines, turboprop engines and turboshaft engines, two schemes of direct circulation and indirect circulation are available through experimental verification. The direct-circulation nuclear power engine has the characteristics of direct principle, simple circulation and convenience in installation. However, direct cycle engines inject radioactive material directly into the atmosphere, causing severe radioactive contamination in the flight zone. The indirect cycle engine separates the reactor system from the propulsion system, overcoming the problem of radioactive contamination, but in order to pressurize the primary coolant, the primary side generally requires a separate compressor. This design results in a reactor system that is relatively heavy overall and the arrangement of the nuclear power engine installation in the aircraft cabin cannot be made compact. In addition, the increase of the pipelines means that the leakage probability is increased and the possibility of the occurrence of a breach accident is increased, once the pipelines connected with the main pump are damaged, the operation of the nuclear power system is seriously influenced, even a serious accident of power loss is caused, and the serious accident can cause the great potential safety hazard of the whole power device.
Disclosure of Invention
The invention aims to solve the technical problems and provides an integrated nuclear power engine device which is efficient, indirect-circulating, safe, reliable, efficient and compact, and can overcome the problems that the conventional power device has limited endurance mileage, a direct-circulating nuclear power engine causes radioactive pollution, and an indirect-circulating scheme has large weight and volume and insufficient compactness.
The purpose of the invention is realized as follows:
a nuclear power engine device comprises a fixed base, a reactor system, a heat exchanger, an integrated engine and a connecting pipeline, wherein the reactor system, the heat exchanger, the integrated engine and the connecting pipeline are installed on the fixed base; the reactor system comprises a reactor, a heat exchanger primary side heat exchange chamber and a connecting pipeline, wherein the reactor comprises a pressure vessel, a reactor core surrounding cylinder, a control rod driving mechanism, a reflecting layer, an in-reactor instrument and an instrument support, and the reactor core comprises a fuel rod, a fuel limiting device, a control rod and a supporting structure; the integrated engine comprises an air inlet, a compressor, a heat exchanger secondary side heat exchange chamber, a turbine and an air outlet;
the heat exchanger consists of two parts which are isolated from each other, a primary side heat exchange chamber of the heat exchanger is connected with an outlet of a reactor system and an inlet of the integrated engine through a pipeline, and a secondary side heat exchange chamber of the heat exchanger is connected with an air outlet of a compressor of the integrated engine and a turbine;
the coolant in the primary loop of the reactor is pressurized and accelerated by a compressor of an integrated engine, the outlet of a heat exchange chamber at the primary side of the heat exchanger is connected with the coolant inlet at the front section of the compressor, and the coolant outlet at the front end of the compressor is connected with the inlet of a reactor pressure vessel;
the compressor is composed of two parts which are mutually isolated, the front end is a primary loop coolant compression section, the number of stages is small, the rear end is an air compression section, the number of stages is large, the front end primary loop coolant compression section compresses coolant, and the rear end air compression section compresses air.
The invention also includes such features:
a printed circuit board type heat exchange tube or a shell-and-tube heat exchanger is arranged in the heat exchanger;
reactor coolant flows in the primary side heat exchange chamber part of the heat exchanger, air for pushing an engine to do work flows in the secondary side heat exchange chamber part of the heat exchanger, and the air are isolated from each other;
the front end of the compressor is connected with the front end of the compressor through a primary loop coolant compression section blade and a rear end air compression section blade in a coaxial or non-coaxial mode.
Compared with the prior art, the invention has the beneficial effects that:
the invention realizes the containment of radioactive substances through the two loops of the reactor which are isolated from each other, thereby avoiding the radioactive substances from being sprayed into the air in a large scale; the design of the high-energy density reactor core achieves higher reactor parameters, and high-efficiency power output and high-energy conversion efficiency are ensured; the simultaneous compression of the primary loop coolant and the secondary side air is realized through the integrated engine design, and the compression positions are mutually isolated, so that the containment of radioactive substances is ensured; the reactor system volume is reduced in the integrated design, a primary loop compressor is omitted, the nuclear power engine system is compact integrally, the nuclear power engine and the aircraft can be matched well, and the system is simpler and more convenient to operate.
Drawings
FIG. 1 is a schematic illustration of a nuclear powered engine system of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
The invention relates to a nuclear power engine device, which is characterized in that: the reactor comprises a fixed base, and a reactor system, a heat exchanger, an integrated engine and a connecting pipeline which are arranged on the fixed base.
The reactor system comprises a reactor, a heat exchanger primary side and a connecting pipeline, wherein the reactor comprises a reactor pressure vessel, a reactor core surrounding cylinder, a control rod driving mechanism, a reflecting layer, an in-reactor instrument, an instrument support and other structures, and the reactor core comprises fuel rods, a fuel limiting device, control rods, a supporting structure and the like; the engine comprises an air inlet, a compressor, a heat exchange chamber on the secondary side of the heat exchanger, a turbine and an air outlet.
The heat exchanger is composed of two parts which are isolated from each other, the primary side of the heat exchanger is connected with the outlet of the reactor system and the inlet of the integrated engine through a pipeline, and the secondary side of the heat exchanger is connected with the air outlet of the compressor of the integrated engine and the turbine.
A compressor is not arranged on the primary side of the compact nuclear power engine independently, the coolant in a reactor primary loop is pressurized and accelerated by the compressor of the integrated engine, the outlet of the primary side of the heat exchanger is connected with the coolant inlet at the front section of the compressor, and the coolant outlet at the front end of the compressor is connected with the inlet of a reactor pressure container.
The compressor is composed of two parts which are mutually isolated, the front end is a primary loop coolant compression section with fewer stages, and the rear end is an air compression section with more stages. The front end compresses the coolant and the rear end compresses the air.
The present invention may further comprise:
1. built-in printed circuit board type heat exchange tube or shell-and-tube heat exchanger in heat exchanger
2. The reactor coolant flows in the primary side part of the heat exchanger, and the air for pushing the engine to do work flows in the secondary side part of the heat exchanger, and the primary side part and the secondary side part are isolated from each other.
3. The coolant of the primary circuit and the air of the secondary side which are mutually isolated are simultaneously compressed by the same compressor.
4. The front end of the compressor is connected with the front end of the compressor through a primary circuit coolant compression section blade and a rear end air compression section blade in a coaxial or non-coaxial mode.
The invention provides a compact high-efficiency indirect circulation nuclear power engine device which comprises a reactor system, a heat exchanger, an integrated engine and a connecting pipeline. The reactor system comprises a reactor, a heat exchanger primary side and a connecting pipeline, wherein the reactor comprises a pressure vessel 7, a reflecting layer, a reactor core surrounding cylinder 10, fuel rods 9, a fuel limiting device 11, a control rod driving mechanism 6, in-reactor instruments, an instrument supporting structure and other in-reactor components, a reactor inlet cold pipe section connecting pipe 8 and a reactor outlet heat pipe section connecting pipe 5. The reactor pressure vessel 7 is connected with an engine compressor through an inlet cold pipe section connecting pipe 8 and is connected with the heat exchanger primary side heat exchange chamber 3 through a reactor outlet hot pipe section connecting pipe 5. The reflecting layer is located in the core active area outside the pressure vessel 7 and reflects neutrons escaping from the core. The control rods and the control rod driving mechanism 6 are positioned at the end part of the reactor pressure vessel 7, and the driving mechanism drives the control rods to move through electric power during normal operation. The fuel rods 9 are located inside the pressure vessel and their position is fixed by a core shroud 10 and a stop device 11. When the H power engine operates normally, the compressed coolant flows into the reactor core through the reactor inlet cold pipe section connecting pipe 8, flows out of the reactor core after being heated by the fuel element, and enters the primary side of the energy conversion system. The energy conversion system includes a primary side passage and a secondary side air passage, the air and the coolant being isolated from each other and flowing in opposite directions. An outlet connecting pipe 2 of a primary side heat exchange chamber of the heat exchanger is connected to a primary loop coolant compression section at the front end of the compressor, the heat-exchanged coolant is compressed in the primary loop coolant compression section, and then the compressed coolant flows into the reactor through a reactor inlet connecting pipe to complete primary loop circulation. The engine comprises a compressor 1, a heat exchange chamber 12 at the secondary side of a heat exchanger and a turbine 4. The compressor sucks air, the air is compressed by the rear-end air compression section 13, high-pressure air flows into the secondary side heat exchange chamber of the heat exchanger to exchange heat with a primary coolant, the high-pressure air flows into the turbine to do work after being heated to a certain temperature, the high-pressure air expands to generate thrust, and the thrust is sprayed out through the exhaust port to push the aircraft to move forward.
The compact nuclear power engine omits a primary circuit compressor, and completes double simultaneous compression of air and coolant only through the compressor of the engine, thereby greatly reducing the size of a primary circuit, reducing the weight of the system and facilitating the arrangement in an aircraft cabin.
Claims (4)
1. A nuclear powered engine apparatus, characterized by: the reactor comprises a fixed base, and a reactor system, a heat exchanger, an integrated engine and a connecting pipeline which are arranged on the fixed base; the reactor system comprises a reactor, a heat exchanger primary side heat exchange chamber and a connecting pipeline, wherein the reactor comprises a pressure vessel, a reactor core surrounding cylinder, a control rod driving mechanism, a reflecting layer, an in-reactor instrument and an instrument support, and the reactor core comprises a fuel rod, a fuel limiting device, a control rod and a supporting structure; the integrated engine comprises an air inlet, a compressor, a heat exchanger secondary side heat exchange chamber, a turbine and an air outlet;
the heat exchanger consists of two parts which are isolated from each other, a primary side heat exchange chamber of the heat exchanger is connected with an outlet of a reactor system and an inlet of the integrated engine through a pipeline, and a secondary side heat exchange chamber of the heat exchanger is connected with an air outlet of a compressor of the integrated engine and a turbine;
the coolant in the primary loop of the reactor is pressurized and accelerated by a compressor of an integrated engine, the outlet of a heat exchange chamber at the primary side of the heat exchanger is connected with the coolant inlet at the front section of the compressor, and the coolant outlet at the front end of the compressor is connected with the inlet of a reactor pressure vessel;
the compressor is composed of two parts which are mutually isolated, the front end is a primary loop coolant compression section, the number of stages is small, the rear end is an air compression section, the number of stages is large, the front end primary loop coolant compression section compresses coolant, and the rear end air compression section compresses air.
2. The nuclear powered engine assembly of claim 1 wherein: a printed circuit board type heat exchange tube or a shell-and-tube heat exchanger is arranged in the heat exchanger.
3. The nuclear powered engine assembly of claim 1 wherein: reactor coolant flows in the heat exchange chamber part on the primary side of the heat exchanger, air for pushing an engine to do work flows in the heat exchange chamber part on the secondary side of the heat exchanger, and the reactor coolant and the air are isolated from each other.
4. The nuclear powered engine assembly of claim 1 wherein: the front end of the compressor is connected with the front end of the compressor through a primary loop coolant compression section blade and a rear end air compression section blade in a coaxial or non-coaxial mode.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011282798.5A CN112392597A (en) | 2020-11-17 | 2020-11-17 | Nuclear power engine device |
| CN202110916820.5A CN113494358B (en) | 2020-11-17 | 2021-08-11 | A nuclear power engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011282798.5A CN112392597A (en) | 2020-11-17 | 2020-11-17 | Nuclear power engine device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112392597A true CN112392597A (en) | 2021-02-23 |
Family
ID=74599973
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011282798.5A Pending CN112392597A (en) | 2020-11-17 | 2020-11-17 | Nuclear power engine device |
| CN202110916820.5A Active CN113494358B (en) | 2020-11-17 | 2021-08-11 | A nuclear power engine |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110916820.5A Active CN113494358B (en) | 2020-11-17 | 2021-08-11 | A nuclear power engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN112392597A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113027610A (en) * | 2021-05-06 | 2021-06-25 | 中国航空发动机研究院 | Aeroengine, engine control method and aircraft |
| CN113090387A (en) * | 2021-05-06 | 2021-07-09 | 中国航空发动机研究院 | Nuclear energy aircraft engine and aircraft |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114038599B (en) * | 2021-10-25 | 2023-09-19 | 哈尔滨工程大学 | A direct cycle controlled drum nuclear power engine |
| CN114753925A (en) * | 2022-05-12 | 2022-07-15 | 沈阳漠南动力科技有限公司 | Electric energy turbine engine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101673583A (en) * | 2009-09-23 | 2010-03-17 | 李胜 | Method for acquiring and converting energy for catalyzing nuclear fusion at normal temperature |
| CN102870165A (en) * | 2010-02-24 | 2013-01-09 | 原子能和代替能源委员会 | Facility for producing energy using a gas-cooled fast reactor |
| CN103928061A (en) * | 2013-01-14 | 2014-07-16 | 上海核工程研究设计院 | Reverse pushing type reactor pressure vessel and reactor internals thereof |
| CN107045827A (en) * | 2017-01-20 | 2017-08-15 | 佛山市三水区希望火炬教育科技有限公司 | A kind of special nuclear-powered bomber model of teenager's research in defense-related science and technology |
| CN207670673U (en) * | 2017-12-20 | 2018-07-31 | 中国科学院工程热物理研究所 | A kind of aircraft mixed power plant |
| CN110660497A (en) * | 2019-08-22 | 2020-01-07 | 北京精密机电控制设备研究所 | Power supply system for generating power by utilizing moon in-situ energy |
| CN111779576A (en) * | 2020-07-13 | 2020-10-16 | 中国航空发动机研究院 | A combined propulsion device, system and control method |
Family Cites Families (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3210254A (en) * | 1961-02-10 | 1965-10-05 | Gen Dynamics Corp | Heat extraction system for a nuclear reactor |
| CH476205A (en) * | 1967-07-27 | 1969-07-31 | Sulzer Ag | Gas turbine system with CO2 as the working medium |
| CH497643A (en) * | 1968-10-01 | 1970-10-15 | Sulzer Ag | Method for operating a closed gas turbine plant |
| CH629022A5 (en) * | 1978-06-13 | 1982-03-31 | Sulzer Ag | CORE REACTOR SYSTEM FOR GENERATING PROCESS HEAT. |
| US5406786A (en) * | 1993-07-16 | 1995-04-18 | Air Products And Chemicals, Inc. | Integrated air separation - gas turbine electrical generation process |
| FR2838555B1 (en) * | 2002-04-12 | 2006-01-06 | Framatome Anp | METHOD AND DEVICE FOR PRODUCING ELECTRICITY FROM HEAT PRODUCED IN THE HEART OF AT LEAST ONE HIGH TEMPERATURE NUCLEAR REACTOR |
| JP2005233148A (en) * | 2004-02-23 | 2005-09-02 | Mitsubishi Heavy Ind Ltd | Gas turbine plant |
| US7961835B2 (en) * | 2005-08-26 | 2011-06-14 | Keller Michael F | Hybrid integrated energy production process |
| JP4724848B2 (en) * | 2006-04-21 | 2011-07-13 | 独立行政法人 日本原子力研究開発機構 | Combined Brayton cycle power generation system using nuclear heat |
| US7739864B2 (en) * | 2006-11-07 | 2010-06-22 | General Electric Company | Systems and methods for power generation with carbon dioxide isolation |
| JP4962956B2 (en) * | 2007-05-22 | 2012-06-27 | 独立行政法人日本原子力研究開発機構 | Nuclear heat utilization equipment |
| US10119414B2 (en) * | 2012-05-08 | 2018-11-06 | David J. Podrog | Hafnium turbine engine and method of operation |
| US10233838B2 (en) * | 2014-09-09 | 2019-03-19 | The United States Of America, As Represented By The Secretary Of The Navy | Recuperated gas turbine engine |
| CN104791098A (en) * | 2015-04-01 | 2015-07-22 | 怡能绿色（北京）动力科技有限公司 | High-efficiency simple cycle gas turbine and operation method thereof |
| CN105869685B (en) * | 2016-04-06 | 2017-10-03 | 哈尔滨工程大学 | A kind of control method of the simulation nuclear reactor neutron reaction feedback procedure of the thermal-hydraulic experiment device based on simulation nuclear reactor neutron reaction feedback procedure |
| US10755826B2 (en) * | 2017-11-10 | 2020-08-25 | Nugen, Llc | Integrated system for converting nuclear energy into electrical, rotational, and thermal energy |
| CN111120100A (en) * | 2019-12-31 | 2020-05-08 | 中国核动力研究设计院 | Heat pipe reactor adopting open type gas Brayton cycle and operation method thereof |
-
2020
- 2020-11-17 CN CN202011282798.5A patent/CN112392597A/en active Pending
-
2021
- 2021-08-11 CN CN202110916820.5A patent/CN113494358B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101673583A (en) * | 2009-09-23 | 2010-03-17 | 李胜 | Method for acquiring and converting energy for catalyzing nuclear fusion at normal temperature |
| CN102870165A (en) * | 2010-02-24 | 2013-01-09 | 原子能和代替能源委员会 | Facility for producing energy using a gas-cooled fast reactor |
| CN103928061A (en) * | 2013-01-14 | 2014-07-16 | 上海核工程研究设计院 | Reverse pushing type reactor pressure vessel and reactor internals thereof |
| CN107045827A (en) * | 2017-01-20 | 2017-08-15 | 佛山市三水区希望火炬教育科技有限公司 | A kind of special nuclear-powered bomber model of teenager's research in defense-related science and technology |
| CN207670673U (en) * | 2017-12-20 | 2018-07-31 | 中国科学院工程热物理研究所 | A kind of aircraft mixed power plant |
| CN110660497A (en) * | 2019-08-22 | 2020-01-07 | 北京精密机电控制设备研究所 | Power supply system for generating power by utilizing moon in-situ energy |
| CN111779576A (en) * | 2020-07-13 | 2020-10-16 | 中国航空发动机研究院 | A combined propulsion device, system and control method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113027610A (en) * | 2021-05-06 | 2021-06-25 | 中国航空发动机研究院 | Aeroengine, engine control method and aircraft |
| CN113090387A (en) * | 2021-05-06 | 2021-07-09 | 中国航空发动机研究院 | Nuclear energy aircraft engine and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113494358A (en) | 2021-10-12 |
| CN113494358B (en) | 2022-07-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112392597A (en) | Nuclear power engine device | |
| US20250218613A1 (en) | Mobile heat pipe cooled fast reactor system | |
| CN104595032B (en) | A kind of multi-fan super large bypass ratio turbine push system | |
| CN104110326B (en) | A kind of new ideas high-speed aircraft propulsion system layout method | |
| CN106742075B (en) | Distributed propulsion system | |
| US3547379A (en) | Aircraft nuclear propulsion system having an alternative power source | |
| CN105257428A (en) | Distributed compression and cyclone ramjet engine | |
| US20240133343A1 (en) | Gas turbine engine fuel system | |
| US3383858A (en) | Nuclear rocket engine | |
| CN108757218B (en) | A Novel Thermoelectric Cycle Combined Engine | |
| US5255509A (en) | Particle bed reactor-powered turbine engine | |
| GUNN | Development of nuclear rocket engine technology | |
| CN112855344B (en) | Nuclear power turbine engine | |
| CN114038599B (en) | A direct cycle controlled drum nuclear power engine | |
| CN221144616U (en) | Nuclear aeroengine structure | |
| GB870265A (en) | Jet propulsion unit with cooling means | |
| RU2392461C1 (en) | Power plant of nuclear gas turbine locomotive | |
| CN118622512A (en) | A pulse detonation driven distributed propulsion system | |
| CN118836095A (en) | Nuclear energy-chemical energy hybrid propulsion system based on afterburning combustion and aircraft | |
| Wang | Analysis and Possible Improvements of Scramjet Engines: The Effective Thrust and the Combustion Stability Problems | |
| CN118775061A (en) | A horizontal take-off and landing aerospace power system and aircraft suitable for single-stage orbit entry and orbit transfer | |
| Ganley | Concorde propulsion-did we get it right? the rolls-royce/snecma olympus 593 engine reviewed | |
| Reynolds | The Pluto Program | |
| NARABAYASHI et al. | ICONE15-10865 Total Energy Supply-System for Manned Spaceship using Nuclear Reactor | |
| CN116025485A (en) | Attitude control power system of launch vehicle based on electric pump and its application method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20210223 |
|
| WD01 | Invention patent application deemed withdrawn after publication |