Patent Description:
With the development of civil aviation, aircraft are increasingly chosen as a means of transportation for ordinary travel. In recent years, the number of flights and trips of civil aircraft has increased significantly. During the flight, the aircraft cabin is a closed space environment, and the health, safety and comfort of the people in the cabin are key concerns. An aircraft air conditioning system is an important mechanism system to provide a healthy and comfortable environment for aircraft passengers and crew by regulating the pressure, temperature, humidity and other parameters of the aircraft cabin environment.

A series of influenza viruses and coronaviruses have been rampant in recent years, such as the SARS virus in <NUM>, the H1N1 virus in <NUM>, and then the Ebola virus and <NUM>-nCov, etc. Related reports indicate that transmission in the means of transportation is also one of the ways in which the virus spreads. The high infectiousness and case fatality rates of these viruses have led to rejection and fear to public transportation during the epidemic. During the novel coronavirus epidemic in <NUM>, public transportation was almost paralyzed, including the civil air transportation system, which was severely affected. For civil aircraft, an aircraft cabin is a closed small space. From the economy, engine performance and other considerations, the aircraft air conditioning system contains part of circulated air in the cabin, so the air quality in the cabin involves safety and health of the passengers, and how to protect the public health security in the aircraft cabin during the epidemic is also one of the key concerns for the aircraft air conditioning system.

Currently, the airborne air conditioning system mainly used in civil airliners is a <NUM>/<NUM> mixed air ratio air supply system. In this air supply system, <NUM>% of the mixed gas comes from the fresh air outside the cabin (usually the engine bleed air), and the other <NUM>% is the recirculated air in the cabin. This part of recirculated air may contain viruses, bacteria and other harmful components exhaled by the carrier. The air conditioning system has complete filtering and cleaning components, but they are for the known viruses and bacteria. For novel viruses, especially unknown and highly infectious viruses, it is not a complete solution. During epidemics of some novel infectious viruses or bacteria, this is a great threat to the health and life safety of passengers. Therefore, there is an urgent need for a novel aircraft air conditioning system that can kill infectious viruses and bacteria to ensure the health and safety of people in the aircraft cabins, provide safe and reliable rapid transportation capacity for the prevention of large-scale infectious diseases and the national economy transportation guarantee during the epidemic, and ensure the normal operation of the national The prior art is illustrated by document <CIT>. This document proposes to remove pathogens from recirculated air by treating the recirculated air with ultraviolet rays.

In the present invention, by using the aircraft engine bleed air, a heater and compressor-turbine mechanism, ultra-high-temperature sterilization is performed on the infectious viruses and bacteria in the recirculated air of the aircraft cabin under certain high temperature conditions by means of front-end mixing, thereby enhancing the air quality of the aircraft cabin supply air, inhibiting the transmissibility of aircraft cabin viruses, and ensuring the health and safety of aircraft passengers and crew on board. An objective of the present invention as specified in any of claims <NUM> to <NUM> is to solve the problem that the traditional aircraft air conditioning system cannot kill <NUM>% of viruses and bacteria (especially some novel highly infectious viruses and bacteria) in the recirculated air, resulting in that the air quality of the aircraft cabin supply air cannot meet the requirement of non-infectiousness and solve the doubts of the passengers, and provide a novel aircraft air conditioning system, so that the recirculated air of the aircraft air conditioning system is subjected to ultra-high-temperature sterilization, thus ensuring the cleanliness of the aircraft cabin supply air and the hygiene safety of people on board (passengers and crew), and thereby achieving the effects of killing the infectious viruses (such as SARS, <NUM>-nCoV and the like) and inhibiting cross infection among people.

A first aspect of the invention is defined by an aircraft Ultra-High-Temperature Sterilization Air Conditioning System (UHTS-ACS) as specified in claim <NUM>.

A second aspect of the invention is defined by a method as specified in claim <NUM>.

Compared with existing system and technology, the technical solution adopted by the present invention has the following technical effects:
According to the aircraft UHTS-ACS of the present invention, with the ultra-high-temperature sterilization recirculated air line, while the aircraft air conditioning system meets certain economy, the recirculated air of the aircraft air conditioning system is subjected to ultra-high-temperature sterilization, thereby greatly reducing harmful components in the air, enhancing the air quality of the aircraft cabin supply air, and preventing the infectious viruses and bacteria from returning to the cabin through the recirculated air system and causing cross infection. Thereby, the transmissibility of aircraft cabin viruses is inhibited, the health and safety of aircraft passengers and crew on board are enhanced, and safety and reliability of civil air transportation under highly infectious epidemic conditions are ensured.

The present invention will be further described below in conjunction with the accompanying drawings:
<FIG> shows an aircraft UHTS-ACS of the present invention.

Names for reference numerals: I, engine bleed air; II, ram air; III, recirculated air; IV, cabin supply air; <NUM>, an engine bleed air main line (pipeline) ; <NUM>, an air conditioning system main line; <NUM>, a turbine outlet deicing bypass; <NUM>, a supply air temperature regulating bypass; <NUM>, a turbine outlet temperature regulating bypass; <NUM>, a compressor superheat regulating bypass; <NUM>, a water separation (water removal) branch; <NUM>, an ordinary recirculated air line; <NUM>, a ultra-high-temperature sterilization recirculated air line; <NUM>, a recirculated air main line; <NUM>, an engine bleed air one-way valve; <NUM>, a primary heat exchanger; <NUM>, a secondary heat exchanger; <NUM>, a water sprinkler; <NUM>, a compressor; <NUM>, a turbine; <NUM>, a compressor superheat regulating valve; <NUM>, a water separator; <NUM>, a temperature sensing and regulating device; <NUM>, a temperature regulating valve; <NUM>, a turbine outlet deicing valve; <NUM>, a supply air temperature regulating valve; <NUM>, an ordinary recirculated air line valve; <NUM>, a mixing chamber; <NUM>, a ultra-high-temperature sterilization recirculated air line valve; <NUM>, a heater; <NUM>, a high-temperature injection mixing chamber; <NUM>, an injector; <NUM>, a primary heat exchanger bypass valve; and <NUM>, a fan.

The solution of the aircraft UHTS-ACS of the present invention will be further described in detail below in conjunction with the accompanying drawings.

The traditional air conditioning system (traditional ACS) in aircraft includes the following parts:
The air source mainly includes: <NUM>, engine bleed air I; <NUM>, ram air II; and <NUM>, recirculated air III. The engine bleed air I has three lines: an air conditioning system main line <NUM>, a turbine outlet deicing bypass <NUM>, and a supply air temperature regulating bypass <NUM>. High-temperature gas from the engine passes through the air conditioning system main line <NUM>, and is subjected to heat exchange sequentially through a primary heat exchanger <NUM>, a compressor <NUM>, a secondary heat exchanger <NUM> and a turbine <NUM>. After free water is separated by a water separator <NUM>, the gas finally comes to a mixing chamber <NUM>, is mixed with the recirculated air III from an ordinary recirculated air line <NUM>, and is finally supplied to an aircraft cabin.

When the turbine outlet temperature is too low and icing occurs, a deicing valve <NUM> on the turbine outlet deicing bypass <NUM> is opened, and the high-temperature gas is led to the turbine outlet to deice the turbine.

The supply air temperature regulating bypass <NUM> is mainly configured to regulate the temperature supplied to the aircraft cabin to meet the design temperature requirement. The whole system includes air circulation and temperature regulation functions.

The ram air II is configured to cool the primary heat exchanger <NUM> and the secondary heat exchanger <NUM>.

A water separation (water removal) branch <NUM> is connected to the water separator <NUM>. The water separation (water removal) branch <NUM> brings the separated free water into a ram air II passage to further cool the primary heat exchanger <NUM> and the secondary heat exchanger <NUM>.

According to the existing aircraft air conditioning system, after the recirculated air III is mixed with fresh air in the mixing chamber <NUM>, the mixed gas is directly supplied to the aircraft cabin. If the recirculated air contains viruses, bacteria and the like, they cannot be effectively killed and inactivated, which is not beneficial to health and safety of people on board.

The aircraft UHTS-ACS of the present invention comprises a ultra-high-temperature sterilization recirculated air device. The ultra-high-temperature sterilization recirculated air device includes a ultra-high-temperature sterilization recirculated air line, a heater, a high-temperature injection mixing chamber, an injector and a primary heat exchanger bypass. The ultra-high-temperature sterilization recirculated air line is connected to a recirculated air main line in the traditional aircraft air conditioning system, and the ultra-high-temperature sterilization recirculated air line is connected to the high-temperature injection mixing chamber. After recirculated air is mixed with high-temperature engine bleed air under the injection action of the injector, the mixed high-temperature gas enters a compressor through the primary heat exchanger bypass to be compressed and heated, is regulated to a suitable temperature through cooling of the secondary heat exchanger and the turbine, and then is supplied to the aircraft cabin.

Further, the primary heat exchanger bypass includes a primary heat exchanger bypass valve. The ultra-high-temperature sterilization recirculated air line is provided with a one-way valve for controlling opening and closing of the branch and a heater.

As shown in <FIG>, the aircraft UHTS-ACS provided by the present invention mainly includes engine bleed air I, ram air II, recirculation air III, and cabin supply air IV; an engine bleed air main line (pipeline) <NUM>, an air conditioning system main line <NUM>, a turbine outlet deicing bypass <NUM>, a supply air temperature regulating bypass <NUM>, a turbine outlet temperature regulating bypass <NUM>, a compressor superheat regulating bypass <NUM>, a water separation (water removal) branch <NUM>, an ordinary recirculated air line <NUM>, the ultra-high-temperature sterilization recirculated air line <NUM>, and a recirculated air main line <NUM>; and an engine bleed air one-way valve <NUM>, a primary heat exchanger <NUM>, the secondary heat exchanger <NUM>, a water sprinkler <NUM>, the compressor <NUM>, the turbine <NUM>, a compressor superheat regulating valve <NUM>, a water separator <NUM>, a temperature sensing and regulating device <NUM>, a temperature regulating valve <NUM>, a turbine outlet deicing valve <NUM>, a supply air temperature regulating valve <NUM>, an ordinary recirculated air line valve <NUM>, a mixing chamber <NUM>, a ultra-high-temperature sterilization recirculated air line valve <NUM>, the heater <NUM>, the high-temperature injection mixing chamber <NUM>, the injector <NUM>, the primary heat exchanger bypass valve <NUM>, and a fan <NUM>.

The heater is connected to a main line of the ultra-high-temperature sterilization recirculated air line, and the recirculated air is heated by the heater, and then rapidly mixed with the engine bleed air in the ultra-high-temperature injection mixing chamber under the injection action of the injector.

During epidemics of some novel infectious viruses or bacteria, the ordinary recirculated air line valve is closed, the ultra-high-temperature sterilization recirculated air line valve is opened, and the primary heat exchanger bypass valve is opened. At this time, the ultra-high-temperature sterilization recirculated air line works, and the ordinary recirculated air line does not work. The recirculated air is heated by the heater for preliminary sterilization. Then, the recirculated air is thoroughly mixed with the engine bleed air from the engine bleed air main line in the high-temperature injection mixing chamber under the action of the injector, so that the mixed gas can be sterilized under the action of high temperature. The mixed gas enters the compressor through the primary heat exchanger bypass to be compressed by the compressor such that the temperature of the mixed gas further increases, thereby further performing sterilization. Finally, the mixed gas is subjected to the heat dissipation of the secondary heat exchanger and the cooling of the turbine, and is subjected to temperature regulation to reach a suitable temperature through the turbine outlet deicing bypass, the turbine outlet temperature regulating bypass, the compressor superheat regulating bypass and the supply air temperature regulating bypass , and then is supplied to the cabin. The free water is discharged out of the system through the water separation (water removal) branch.

The specific operation and implementation method of the system of the present invention is as follows.

Finally, the mixed gas is regulated to a suitable temperature through the heat dissipation of the secondary heat exchanger <NUM> and the cooling of the turbine <NUM>, and then becomes aircraft cabin supply air IV.

Claim 1:
An aircraft Ultra-High-Temperature Sterilization Air Conditioning System (UHTS-ACS), wherein the aircraft UHTS-ACS comprises an engine bleed air supply (I), a recirculated air main line (<NUM>), an air conditioning system main line (<NUM>), a primary heat exchanger (<NUM>), a secondary heat exchanger (<NUM>), a compressor (<NUM>), a turbine (<NUM>), a cabin air supply (IV), and an ultra-high-temperature sterilization recirculated air device, wherein the ultra-high-temperature sterilization recirculated air device comprises an ultra-high-temperature sterilization recirculated air line (<NUM>), a heater (<NUM>), a high-temperature injection mixing chamber (<NUM>) and a primary heat exchanger bypass;
wherein the ultra-high-temperature sterilization recirculated air line (<NUM>) is connected to the recirculated air main line (<NUM>), the ultra-high-temperature sterilization recirculated air line (<NUM>) is connected to the high-temperature injection mixing chamber (<NUM>), ultra-high-temperature sterilization recirculated air is preheated by the heater (<NUM>) and then mixed with high-temperature engine bleed air (I) in the high-temperature injection mixing chamber (<NUM>), and the mixed high-temperature gas enters the compressor (<NUM>) through the primary heat exchanger bypass to be compressed and heated, is regulated to a suitable temperature through cooling of the secondary heat exchanger (<NUM>) and the turbine (<NUM>), and then is supplied to an aircraft cabin;
wherein the primary heat exchanger bypass is provided with a primary heat exchanger bypass valve (<NUM>) for controlling opening and closing of the branch; and,
wherein the ultra-high-temperature sterilization recirculated air line (<NUM>) is provided with a one-way valve (<NUM>) for controlling opening and closing of the branch and the heater (<NUM>).