CN210634763U

CN210634763U - Three-mode aircraft air conditioning system

Info

Publication number: CN210634763U
Application number: CN201921657451.7U
Authority: CN
Inventors: 陈兴乔
Original assignee: Jiangsu Hongjihuandian Co Ltd
Current assignee: Jiangsu Hongjihuandian Co Ltd
Priority date: 2019-09-30
Filing date: 2019-09-30
Publication date: 2020-05-29
Anticipated expiration: 2029-09-30

Abstract

The utility model relates to a three mode aircraft air conditioning system, the left side of compound check valve UNICOM aircraft, right engine bleed, through pressure regulator level pressure, venturi is injectd the flow and is gone into air cycle machine processing, send into the main cabin at last, the output of venturi is connected with the first of interlocking respectively through the tee bend, two cold path valves, the output connection air cycle machine of first cold path valve, the output of second cold path valve is exported respectively to the front deck ejector through the cross, right side ejector and left side ejector, a branch road of air cycle machine output leads to the cockpit through the check valve subassembly, the output of front deck ejector leads to the cockpit through temperature relay subassembly and check valve subassembly in proper order, right side ejector exports the foot on main cabin right side and heats, left side ejector exports to the left foot in main cabin and heats. The system switches modes under different environmental temperatures, and meets the temperature requirement of the airplane.

Description

Three-mode aircraft air conditioning system

Technical Field

The utility model relates to an air conditioning field for the aircraft, concretely relates to three mode aircraft air conditioning system who possesses three kinds of mode.

Background

During the flight of the airplane, the cabin, the passenger cabin and the cab all need to be air-conditioned to adjust the temperature so as to improve the driving and riding comfort. The aircraft air conditioner is usually a full fresh air conditioner, the environmental temperature change is large, the output requirements of different areas on the aircraft air conditioner are also different, and the range of the output of the aircraft air conditioner is 2-80 ℃ under the general condition. Aircraft air conditioning requires different modes at different ambient temperatures to ensure that the output temperature requirements are met.

Disclosure of Invention

An object of the utility model is to provide an aircraft air conditioning system who possesses three kinds of mode switches the mode under the ambient temperature of difference, satisfies the temperature requirement of aircraft.

In order to achieve the above purpose, the utility model adopts the technical proposal that:

a three-mode aircraft air conditioning system comprises a power supply, a control system, a compound one-way valve, an absolute pressure regulator, a venturi and an air circulator, wherein the compound one-way valve, the absolute pressure regulator, the venturi and the air circulator are sequentially connected in series, the compound one-way valve is communicated with left and right engine bleed air of an aircraft, the left and right engine bleed air is subjected to constant pressure by the pressure regulator and limited flow by the venturi and then enters the air circulator for treatment, and finally is sent into a passenger cabin, the output end of the venturi is respectively connected with a first cold path valve and a second cold path valve which are interlocked through a tee joint, the output of the first cold path valve is connected with the air circulator, the output of the second cold path valve is respectively output to a front cabin ejector, a right side ejector and a left side ejector through the tee joint, one branch output by the air circulator leads to the cockpit through a one-way valve component, the output of the front cabin, the left ejector outputs the temperature to the left foot of the passenger cabin.

The air cycle machine comprises a cold path and a hot path, wherein the cold path comprises a heat exchanger, a cooler, a temperature sensor, a temperature relay and a water separator which are sequentially connected in series through a pipeline, the hot path is a hot path valve which is connected between the input end of the heat exchanger and the output end of the cooler in series, and air of the cold path and the hot path is mixed and then is output after absorbing water vapor through the water separator.

Further, the control system comprises a temperature selection indicator and a temperature controller, the temperature indicator is connected with the temperature controller and transmits an electric signal, and the temperature controller is connected with and controls the absolute pressure regulator, the first cold path valve, the second cold path valve, the heat exchange valve, the temperature sensor, the temperature relay and the temperature relay assembly.

Further, the temperature selection indicator includes a temperature display screen, a temperature mode button, and a temperature adjustment switch.

Still further, the power is aircraft DC power, and the power output end is connected with the switch to connect gradually temperature indicator, temperature controller, absolute pressure regulator, first cold way valve, second cold way valve, heat transfer valve, temperature sensor, temperature relay and temperature relay subassembly through the switch.

After taking above technical scheme, the beneficial effects of the utility model are that: when the cabin temperature is adjusted by only using the air circulating machine, the system can provide 600kg/h air supply for the cabin, the temperature range of the air is 2-80 ℃, the maximum refrigerating capacity is 4kW, and the maximum heating capacity is 10 kW. After the strong three-way ejector heating assembly is added, the system can provide 1200kg/h of air with the temperature of 80 ℃, and the maximum heating capacity is improved to 20 kW. Therefore, the whole set of system can select between three modes of refrigeration, heating and strong heating, so that the applicable temperature range of the airplane is greatly improved.

Drawings

FIG. 1 is an exploded view of an air conditioning system;

FIG. 2 is a schematic diagram of an air conditioning system;

FIG. 3 is a schematic view of a temperature selection indicator for the cooling mode of the air conditioner;

FIG. 4 is a schematic view of a temperature selection indicator for the air conditioning cooling mode;

fig. 5 is a schematic view of a temperature selection indicator for the air conditioning cooling mode.

In the figure: the device comprises a compound one-way valve 1, a venturi 2, an air circulator 3, an absolute pressure regulator 4, a temperature controller 5, a temperature selection indicator 6, an air circulator support 7, a front cabin ejector 8, a right side ejector 9, a left side ejector 10, a tee joint 11, a four-way joint 12, a Y-shaped pipe 13, a one-way valve assembly 14, a temperature relay assembly 15, a first cold path valve 16A, a second cold path valve 16, a joint 17, a joint 18, a joint 19, a gasket 20 and a gasket 21.

Detailed Description

The following detailed description of the embodiments of the present invention is made with reference to the accompanying drawings:

as shown in fig. 1, the left and right engine bleed air meet at the double check valve 1 through the joint 17, and if there is engine stall on one side, the double check valve 1 can ensure that the engine bleed air on the other side does not flow backwards. The merged engine bleed air enters an absolute pressure regulator 4, the outlet pressure of the absolute pressure regulator 4 is constant at 0.45MPa, the constant pressure bleed air passes through a venturi 2, and the flow is limited to 600 kg/h. The constant-pressure and constant-flow bleed air enters the tee joint 11, and the bleed air is divided into two paths of flow directions: one path is supplied to the air circulator 3, the other path is supplied to the strong warming component, the front ends of the two paths are respectively provided with a first cold path valve 16A and a second cold path valve 16, and the two cold path valves are interlocked, namely, one cold path valve is opened while the other cold path valve is closed.

Wherein the output of first cold road valve 16A is connected with air cycle machine 3 through joint 19 and gasket 21, and the bleed air gets into air cycle machine 3 through this first cold road valve 16A's bleed air, and air cycle machine 3 is through air cycle machine support 7 fixed mounting and aircraft in, and the bleed air is divided into two the tunnel in air cycle machine 3 inside: cold and hot circuits. The temperature of the cold path bleed air is reduced to 50 ℃ after passing through the heat exchanger 31, the temperature of the cold path bleed air enters the turbine cooler 32 and is reduced to-10 ℃, and then the cold path bleed air is converged with the hot path; the hot-path bleed air passes through the hot-path valve 33 and then joins the cold path, and the opening degree of the hot-path valve 33 determines the proportion of joining the two paths, so that the temperature of the outlet of the air cycle machine 3 is adjusted between 2 ℃ and 80 ℃. The work output from the turbo-cooler 32 drives the coaxial fan to draw ambient air, which is directly exhausted out of the engine after heat exchange with the engine bleed air by the heat exchanger. The air cycle machine 3 is provided with a temperature relay 15, and the temperature-adjusted mixed air enters a water separator 34 to be dehydrated and then supplied to the cabin.

The working principle of the cold path of the air cycle machine 3 is as follows: the bleed air of the engine enters the turbine after being preliminarily cooled by the radiator of the air conditioner, the temperature of the bleed air of the engine is reduced by expanding and doing work through the turbine, the air at the outlet of the turbine is the refrigerating air, and the refrigerating air is input into the cockpit and the passenger cabin.

The bleed air of the second cold path valve 16 on the pipeline where the bleed air passes through the reinforcing component respectively enters the cabin ejector 8 of the strong temperature-raising component through the four-way joint 12, the right ejector 9 and the left ejector 10 are respectively connected with the four-way joint 12 through the three connectors 18 and the gaskets 20, the bleed air flows out of the nozzles of the three ejectors at a high speed and enters the receiving chamber to form high-speed jet flow, a negative pressure area is formed by the high-speed jet flow flowing through the receiving chamber, ambient air is sucked into the receiving chamber, and the high-temperature bleed air and the normal-temperature air are mixed and then conveyed into the cockpit and the passenger cabin for heating. The gas from the ejector is respectively led to the cockpit and the passenger cabin.

The output of the cabin ejector 8 is controlled by the temperature relay assembly to enter the one-way valve assembly 14, the one-way valve assembly 14 is connected with the output port of the air circulator 3 in parallel, and the one-way valve assembly 14 is output to the cockpit.

The system control unit is powered by a 27V dc power supply on board the aircraft, and the mode and temperature requirements are sent by the temperature selection indicator 6 to the temperature controller 5, and the temperature controller 5 controls the absolute pressure regulator 4, the two

cold path valves

16A,16, the heat exchange valve 33, the temperature sensor 35, the temperature relay 22 and the temperature relay assembly 15.

The temperature selection indicator 6 is provided with a mode selection switch 23, a temperature selection knob 24 and a temperature display 25, and the mode selection switch 23 can select two modes: air conditioning and warming. When cooling is required, the mode selection switch 23 is set to the "air conditioner" position, and the temperature selection knob 24 is set to the "cold" zone, as shown in fig. 3; when the temperature selection knob 24 is pointed to the "cold" position, indicating a maximum cooling condition, the predetermined turbine outlet temperature is 2 ℃; when heating is needed, if the ambient temperature is about 0 ℃, the mode selection switch 23 is arranged at an air-conditioning position, the temperature selection knob 24 is arranged at a hot area, as shown in fig. 4, when the knob points to the hot position to show the maximum heating state, the preset turbine outlet temperature is 80 ℃; if the ambient temperature is below-10 deg.C, the mode select switch 23 is placed in the "warm" position, as shown in FIG. 5, and the system is in a maximum warm state. The mode selection switch 23 controls the opening and closing of the two cold path valves 16 through the temperature controller 5, and the temperature selection knob 24 controls the hot path valve 33 through the temperature controller 5.

Claims

1. A three-mode aircraft air conditioning system comprises a power supply, a control system, a compound one-way valve, an absolute pressure regulator, a venturi and an air circulator, wherein the compound one-way valve, the absolute pressure regulator, the venturi and the air circulator are sequentially connected in series, the compound one-way valve is communicated with left and right engine bleed air of an aircraft, the left and right engine bleed air is subjected to constant pressure by the pressure regulator and limited flow by the venturi, enters the air circulator for treatment and is finally sent into a passenger cabin, the three-mode aircraft air conditioning system is characterized in that the output end of the venturi is respectively connected with a first cold path valve and a second cold path valve which are interlocked through a tee joint, the output of the first cold path valve is connected with the air circulator, the output of the second cold path valve is respectively output to a front cabin ejector, a right side ejector and a left side ejector through the tee joint, one branch output by the air circulator is led to the passenger cabin through a one-way valve component, the left ejector outputs the temperature to the left foot of the passenger cabin.

2. The tri-mode aircraft air conditioning system of claim 1, wherein the air cycle machine comprises a cold path and a hot path, the cold path comprises a heat exchanger, a cooler, a temperature sensor, a temperature relay and a water separator which are connected in series in sequence by a pipeline, the hot path is a hot path valve connected in series between an input end of the heat exchanger and an output end of the cooler, and air in the cold path and air in the hot path are mixed and then output after absorbing water vapor by the water separator.

3. A three-mode aircraft air conditioning system as claimed in claim 2, wherein said control system includes a temperature selection indicator connected to and delivering an electrical signal to a temperature controller that controls the absolute pressure regulator, the first cold-way valve, the second cold-way valve, the heat-exchange valve, the temperature sensor, the temperature relay and the temperature relay assembly.

4. A three-mode aircraft air conditioning system according to claim 3, wherein said temperature selection indicators comprise a temperature display screen, a temperature mode button and a temperature adjustment switch.

5. A three-mode aircraft air conditioning system according to any one of claims 1 to 4, wherein the power supply is an aircraft DC power supply, and a switch is connected to the power supply output and connected via the switch to the temperature indicator, the temperature controller, the absolute pressure regulator, the first cold path valve, the second cold path valve, the heat exchange valve, the temperature sensor, the temperature relay and the temperature relay assembly in that order.