Aero-engine, engine control method and aircraft

An aero engine and engine technology, applied in the direction of machines/engines, mechanical equipment, gas turbine devices, etc., can solve the problems of heavy aircraft structure, difficulty in meeting aviation requirements, major safety accidents, etc.

Inactive Publication Date: 2021-06-25
AERO ENGINE ACAD OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, in the prior art, the nuclear engine is in the ground take-off state, once a nuclear leak occurs, it will cause a major safety accident
In order to avoid nuclear leakage when the nuclear engine takes off from the ground, it is necessary to install heavy protective layers such as lead, steel and concrete outside the nuclear reactor like a nuclear power plant, which will cause the aircraft's structural weight to be too heavy to meet the aviation requirements

Method used

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  • Aero-engine, engine control method and aircraft
  • Aero-engine, engine control method and aircraft

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] refer to figure 1 As shown, an aeroengine includes an engine body A, and the engine body exemplary includes a fan 1, a booster stage 2, a high-pressure compressor 3, a combustion chamber 7, a high-pressure turbine 8, and The low-pressure turbine 9 and the tail nozzle 10 are driven by the low-pressure turbine 9 and the high-pressure compressor 3 is driven by the high-pressure turbine 8 .

[0034] The engine body is connected with a fuel driving unit B, and the fuel driving unit B can use fuel to drive the engine to perform work. The engine body is also connected to a nuclear energy drive unit C, which can use nuclear energy to drive the engine to do work; the fuel drive unit B and the nuclear energy drive unit C are also connected to the power control unit D, and the power control unit D can monitor the aircraft In the flight state, when the aircraft is in the take-off state or climbing state, the fuel drive unit B is controlled to drive the engine body A to do work, an...

Embodiment 2

[0040] refer to figure 2 As shown, a control method of the above-mentioned aero-engine includes: monitoring the flight state of the aircraft,

[0041] When the aircraft is in the ground take-off or climbing state, the fuel drive unit B inputs fuel into the engine body A to burn and drive the engine body A to do work, generate thrust, and propel the aircraft;

[0042] When the aircraft is in the cruising state, the nuclear power drive unit C ignites the nuclear reactor 5, and the nuclear reactor 5 transfers energy to the engine body A to drive the engine body A to do work and generate thrust. The cruising altitude of the cruising state is generally above 11KM.

[0043] When the aircraft has just switched to the cruising state, the nuclear energy drive unit C drives the engine body A to gradually generate thrust, and the fuel drive unit B generates thrust as a supplement. Reduce until it is completely closed, and the engine body is all driven by the nuclear energy drive unit ...

Embodiment 3

[0046] An aircraft includes the aero-engine in Embodiment 1. The aero-engine is used as the power to drive the aircraft to fly. When the aircraft is in the ground take-off state or climbing state, the nuclear drive unit does not work, and the fuel drive unit ignites aviation kerosene to heat the compressed air, push the turbine to do work, and complete the thermal cycle to generate thrust. Thereby realize the take-off and climb of aircraft. In the cruising state of the aircraft, start the nuclear energy drive unit, and the nuclear energy drive unit will heat the compressed air behind the high-pressure compressor to complete the thermal cycle to generate thrust, thereby realizing the ultra-long range and ultra-long-endurance cruise of the aircraft. The combustion chamber does not work in the cruising state. Does not consume aviation kerosene. Therefore, the safety protection device of the nuclear reactor is designed according to the unmanned state, which can reduce the weight ...

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Abstract

The invention discloses an aero-engine, an engine control method and an aircraft. The aero-engine comprises an engine body, a fuel driving unit connected with the engine body and a nuclear energy driving unit connected with the engine body, wherein a power control unit is connected with the fuel driving unit and the nuclear energy driving unit, so that the flight state of the aircraft can be monitored; and when the aircraft is in a take-off state, the fuel driving unit is controlled to drive the engine body to do work, and when the aircraft is in a cruise state, the nuclear energy driving unit is controlled to drive the engine body to do work. According to the aero-engine, the engine control method and the aircraft, due to the adoption of a nuclear energy and chemical energy mixed thermodynamic cycle mode, a nuclear reactor only works in an unmanned aerial vehicle high-altitude state, so that the safety protection device of the nuclear reactor is subjected to protection design according to an unmanned state, and the weight of a protection device can be reduced.

Description

technical field [0001] The disclosure belongs to the field of aeroengines, and in particular relates to an aeroengine, an engine control method, and an aircraft. Background technique [0002] Nuclear aero-engines are engines that use the huge energy generated by nuclear fuel fission to power aircraft. Aircraft equipped with nuclear aero-engines have the advantages of ultra-long range and long flight time, and can fly to any place on the surface of the earth without refueling in the air. places, the stay in the air can exceed 1 month. [0003] However, in the prior art, in the state of take-off of the nuclear power engine on the ground, once a nuclear leak occurs, a major safety accident will be caused. In order to avoid nuclear leakage when the nuclear engine takes off from the ground, it is necessary to install heavy protective layers such as lead, steel and concrete outside the nuclear reactor like a nuclear power plant, which will cause the aircraft's structural weight t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C3/04F02C3/20F02C7/00F02C6/00
CPCF02C3/04F02C3/20F02C6/00F02C7/00
Inventor 张峻峰刘金龙王佰智孙培培
Owner AERO ENGINE ACAD OF CHINA
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