CN-121993267-A - Aviation refrigeration power generation system, aircraft and control method

CN121993267ACN 121993267 ACN121993267 ACN 121993267ACN-121993267-A

Abstract

The invention relates to the technical field of aviation refrigeration, in particular to an aviation refrigeration power generation system, an aircraft and a control method. An aviation refrigeration power generation system comprises a power component, a refrigeration component and a pipeline component. The power assembly comprises a compressor, a driving turbine and a motor unit, the refrigerating assembly comprises a cooling turbine, the cooling turbine is in coaxial transmission connection with the power assembly, the pipeline assembly comprises a refrigerating pipeline unit and an air inlet pipeline unit, an outlet of the compressor is communicated with an inlet of the refrigerating pipeline unit, the refrigerating assembly is connected with the refrigerating pipeline unit and used for refrigerating gas in the refrigerating pipeline unit, the air inlet pipeline unit comprises a gas transmission pipeline and an air suction pipeline, the inlet of the compressor is communicated with an outlet of the driving turbine through the gas transmission pipeline, and the air suction pipeline is communicated with an inlet of the driving turbine. Thus, the problem that the energy efficiency of the power generation system is low due to the fact that the motor unit provides driving force is solved.

Inventors

ZHOU YUNAN
ZHOU YANZHANG
ZHANG LIUYANG
Kuang Pan
YAO YEMING

Assignees

中国航空工业集团公司金城南京机电液压工程研究中心

Dates

Publication Date: 20260508
Application Date: 20260409

Claims (13)

1. An aviation refrigeration power generation system, characterized in that it comprises: the power assembly comprises a gas compressor, a driving turbine and a motor unit, wherein the gas compressor, the driving turbine and the motor unit are in coaxial transmission connection; the cooling turbine is coaxially connected with the power assembly in a transmission way; The pipeline assembly comprises a refrigeration pipeline unit and an air inlet pipeline unit, an outlet of the air compressor is communicated with an inlet of the refrigeration pipeline unit, the refrigeration assembly is connected with the refrigeration pipeline unit and used for refrigerating gas in the refrigeration pipeline unit, the air inlet pipeline unit comprises an air transmission pipeline and an air suction pipeline, the inlet of the air compressor is communicated with an outlet of the driving turbine through the air transmission pipeline, and the air suction pipeline is communicated with an inlet of the driving turbine.
2. An aviation refrigeration and power generation system according to claim 1, wherein the air suction pipeline comprises a natural air suction branch, an air supply valve, an engine bleed air branch and a bleed air valve, wherein the natural air suction branch and the engine bleed air branch are respectively communicated with an inlet of the driving turbine, the air supply valve is connected with the natural air suction branch, and the bleed air valve is connected with the engine bleed air branch.
3. The aircraft refrigeration power generation system of claim 2, further comprising an equipment heat sink assembly, the equipment heat sink assembly comprising an equipment heat sink and a shut-off valve; The pipeline assembly further comprises a return pipeline unit, an inlet of the return pipeline unit is communicated with the refrigerating pipeline unit, the inlet of the return pipeline unit is located in the outlet direction of the cooling turbine, an outlet of the return pipeline unit is communicated with the inlet of the air compressor, the equipment heat dissipation assembly is connected with the return pipeline unit, and the shutoff valve is located between the inlet of the equipment heat radiator and the refrigerating pipeline unit.
4. An aviation refrigeration power generation system according to claim 3, further comprising an ejector assembly, wherein the ejector assembly comprises an ejector and a driving pipeline, the outlet of the return pipeline unit and the outlet of the gas transmission pipeline are respectively communicated with the inlet of the ejector, the outlet of the ejector is communicated with the inlet of the gas compressor, the inlet of the driving pipeline is communicated with the outlet of the gas compressor, and the outlet of the driving pipeline is communicated with the driving fluid inlet of the ejector.
5. An aviation refrigeration power generation system according to claim 3, wherein said refrigeration assembly further comprises an intake air regulating valve and a restrictor valve, said intake air regulating valve being connected between an inlet of said cooling turbine and an outlet of said compressor, an inlet of said return line unit being located between said restrictor valve and an outlet of said cooling turbine.
6. The aircraft refrigeration and power generation system of claim 5, wherein the piping assembly further comprises a heating piping unit, the heating piping unit comprises a heating branch and a temperature regulating valve, an inlet of the heating branch is communicated with an outlet of the compressor, an outlet of the heating branch is communicated with an outlet of the refrigeration piping unit, the temperature regulating valve is connected with the heating branch, and the flow limiting valve is located between an outlet of the heating branch and an inlet of the return piping unit.
7. An aviation refrigeration and power generation system according to claim 2, wherein said motor unit is an integral starter motor; the pipeline assembly further comprises an exhaust pipeline unit, wherein the exhaust pipeline unit comprises an exhaust branch and an air vent valve, an inlet of the exhaust branch is communicated with the gas transmission pipeline, and the air vent valve is connected with the exhaust branch.
8. An aircraft characterized in that it comprises an aviation refrigeration and power generation system according to any one of claims 1-7.
9. An aviation refrigeration power generation control method applied to the aviation refrigeration power generation system of any one of claims 1-7, and is characterized in that the aviation refrigeration power generation control method comprises the following steps: Responding to a system starting instruction, controlling the power assembly to work, and enabling the air compressor to enter air through the air inlet pipeline unit; when the power assembly is in a working state, acquiring the refrigerating requirement of the system and the rotating speed of the power assembly in real time; And adjusting the rotating speed of the power assembly according to the refrigerating requirement of the system.
10. The aviation refrigeration power generation control method according to claim 9, characterized in that the aviation refrigeration power generation control method further comprises: When the power assembly is in a working state, acquiring the flying speed of the aircraft in real time; when the flying speed is higher than a speed threshold value, opening an engine air-entraining branch, and closing a natural air-sucking branch; And when the flying speed is lower than the speed threshold value, opening the natural air suction branch, and closing the engine air entraining branch.
11. The aviation refrigeration power generation control method according to claim 9, characterized in that the aviation refrigeration power generation control method further comprises: Acquiring the mechanical running state of an aviation refrigeration power generation system in real time; when the power assembly is in a mechanical failure state, the engine air-entraining branch and the heating pipeline unit are opened, the natural air-suction branch is closed, the refrigeration pipeline unit is closed, the return pipeline unit is closed, and the exhaust pipeline unit is closed.
12. The aviation refrigeration power generation control method according to claim 9, characterized in that the aviation refrigeration power generation control method further comprises: responding to an emergency power supply instruction of the aircraft, switching the motor unit into a power generation state, and acquiring target power supply of the aircraft; when the target power supply power is higher than a power threshold value, an engine air-entraining branch and an exhaust pipeline unit are opened, a natural air-suction branch is closed, a refrigeration pipeline unit is closed, a return pipeline unit is closed, and a heating pipeline unit is closed.
13. The aviation refrigeration power generation control method according to claim 12, characterized in that the aviation refrigeration power generation control method further comprises: When the target power supply power is lower than the power threshold, an engine air-entraining branch and a refrigerating pipeline unit are started, a natural air-sucking branch is closed, a return pipeline unit is closed, a heating pipeline unit is closed, and an exhaust pipeline unit is closed.

Description

Aviation refrigeration power generation system, aircraft and control method Technical Field The invention relates to the technical field of aviation refrigeration, in particular to an aviation refrigeration power generation system, an aircraft and a control method. Background The core of aviation refrigeration is to provide environment control and high heat flux density heat management for an aircraft, wherein the environment control comprises regulation and control of temperature, humidity, pressure and the like of a cabin and an equipment cabin, and the high heat flux density heat management is a heat management technology for realizing rapid heat dissipation in a narrow space. The main stream aviation refrigeration technology at present is divided into two major categories, namely air circulation refrigeration and evaporation circulation refrigeration, wherein the air circulation refrigeration is a main stream refrigeration scheme of a main line civil aviation passenger plane and an airplane, and the evaporation circulation refrigeration is widely applied to the fields of turboprop aircrafts, helicopters and general aviation. Refrigeration and power generation systems for aircraft typically rely on a motor unit to provide the driving force or on bleed air from an engine to provide the driving force, the energy efficiency of the system being further improved. Disclosure of Invention The invention provides an aviation refrigeration power generation system, an aircraft and a control method, which aim to solve the problem that the refrigeration power generation system provides driving force by means of a motor unit and has low energy efficiency. In a first aspect, the present invention provides an aviation refrigeration power generation system comprising: the power assembly comprises a gas compressor, a driving turbine and a motor unit, wherein the gas compressor, the driving turbine and the motor unit are in coaxial transmission connection; the cooling turbine is coaxially connected with the power assembly in a transmission way; The pipeline assembly comprises a refrigeration pipeline unit and an air inlet pipeline unit, an outlet of the air compressor is communicated with an inlet of the refrigeration pipeline unit, the refrigeration assembly is connected with the refrigeration pipeline unit and used for refrigerating gas in the refrigeration pipeline unit, the air inlet pipeline unit comprises an air transmission pipeline and an air suction pipeline, the inlet of the air compressor is communicated with an outlet of the driving turbine through the air transmission pipeline, and the air suction pipeline is communicated with an inlet of the driving turbine. Optionally, the air suction pipeline comprises a natural air suction branch, an air supply valve, an engine air-entraining branch and an air-entraining valve, wherein the natural air suction branch and the engine air-entraining branch are respectively communicated with an inlet of the driving turbine, the air supply valve is connected with the natural air suction branch, and the air-entraining valve is connected with the engine air-entraining branch. Optionally, the aviation refrigeration power generation system further comprises an equipment heat dissipation assembly, wherein the equipment heat dissipation assembly comprises an equipment radiator and a shut-off valve; The pipeline assembly further comprises a return pipeline unit, an inlet of the return pipeline unit is communicated with the refrigerating pipeline unit, the inlet of the return pipeline unit is located in the outlet direction of the cooling turbine, an outlet of the return pipeline unit is communicated with the inlet of the air compressor, the equipment heat dissipation assembly is connected with the return pipeline unit, and the shutoff valve is located between the inlet of the equipment heat radiator and the refrigerating pipeline unit. Optionally, the aviation refrigeration power generation system further comprises an injection assembly; the injection assembly comprises an injector and a driving pipeline, wherein an outlet of the return pipeline unit and an outlet of the gas transmission pipeline are respectively communicated with an inlet of the injector, an outlet of the injector is communicated with an inlet of the gas compressor, an inlet of the driving pipeline is communicated with an outlet of the gas compressor, and an outlet of the driving pipeline is communicated with a driving fluid inlet of the injector. Optionally, the refrigeration assembly further comprises an air inlet regulating valve and a flow limiting valve, wherein the air inlet regulating valve is connected between the inlet of the cooling turbine and the outlet of the compressor, and the inlet of the return pipeline unit is positioned between the flow limiting valve and the outlet of the cooling turbine. Optionally, the pipeline assembly further comprises a heating pipeline unit, the heating pipeline unit comprise