JPS5941438B2 - Air conditioner in aircraft - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an apparatus for air conditioning a cabin, that is, a passenger cabin, and a cockpit in an aircraft.

BACKGROUND ART Conventionally, aircraft, particularly jet passenger planes, have employed air conditioners of the industrial cycle type, and two to three systems of air conditioners are installed.

Normally, at least two systems are required to ensure maximum cooling capacity and ventilation during cruising, but three systems are usually installed so that there will be no problem even if one system breaks down. .

However, it is extremely rare that all three systems need to be used.

Therefore, in consideration of extremely rare situations like this, current jet airliners are equipped with the same backup air conditioning system as the normally used air conditioning system.
It is extremely disadvantageous both in terms of weight and price.

In addition, maintenance of the system is required, which is not only time-consuming but also disadvantageous in that it requires more maintenance personnel.

By the way, when one of the normally used systems breaks down and the backup air conditioning system is required to operate, this is because when a malfunction occurs in the air conditioning system during flight, especially during cruising, flight regulations are required depending on conditions such as cabin prepressure. This is because the altitude must be lowered, and the backup air conditioning system is activated to prevent the altitude from decreasing.

However, if the above-mentioned accident occurs during flight, the air conditioning system is functioning within the range required for preload and ventilation, unlike the flight situation near the ground, so temperature adjustment is not necessary. Looking at the heat exchange section, it is in a state where it can be fully achieved.

This invention has been made in view of this point, and is designed to simplify the preliminary air conditioning system as much as possible without causing any problems with preloading and ventilation, thereby reducing the price, cost and man-hours required for maintenance and servicing, and improving reliability. The aim is to provide an air conditioner that is maintained and improved.

The present invention will be explained below according to an embodiment shown in the drawings.

In the figure, 2, 3, and 4 are the supply system lines for introducing and supplying the air bled from the engine section E to the cabin C; the air bleed path 1
and cabin C.

However, the air (high-temperature, high-pressure air) bled from the engine section E is introduced from the right side to the left side of the drawing, and as described later, the air is conditioned and supplied to the left cabin C.

28.29.30 is a control unit that controls the amount of air introduced, which is installed on the oil air path side of each supply line 2, 3.4, and controls the amount of air introduced appropriately based on the pressure of air extracted from the engine and other conditions. do.

Reference numerals 28', 29', and 31 are on-off valves for opening and closing air introduction, which are activated by an abnormality signal from each supply system, as will be described later.

An air conditioning mechanism having the same function is provided in the supply lines 2 and 3, including control units 28 and 29.

That is, heat exchangers 24 and 25 are installed behind the control units 28 and 29 via flow path switching valves 26 and 27, and this heat exchanger 24 and 25 converts high-temperature and high-pressure air into ram air 22.
23.

The air is lowered to a certain temperature by the heat exchangers 24 and 25 and sent in the direction of the arrow, but it is not sufficient and is introduced into the cooling turbine sections 7 and 8.

Here, the air is adiabatically compressed and raised to a constant temperature, but is cooled again by ram air 5 in an intermediate heat exchanger 6.

The cooled air is then adiabatically expanded and mixed with high temperature air to adjust the temperature and pressure to predetermined values.

9.10 and 11.12 are dehumidifiers.

17゜18, 19, 20 are check valves, 15゜1
6 is a butterfly valve that controls opening of the flow path.

The butterfly valves 15, 16 are operated by control signals from controllers 40, 41 which operate in response to signals from temperature sensors Sc and Sp installed in the can C and the supply lines 2, 3.

The actuation of these valves 15, 16 causes the hot air to be mixed.

Air is transferred to supply line 2 by the operation of butterfly valves 15 and 16.
, 3 are also supplied from the bypass passages 13, 14.

21 is a mixing channel ζ for merging the respective supply lines 2.degree. 3, and 43, 44.degree. 45 is a fan.

Reference numeral 26' denotes a drive section for the flow path switching valve 26, which is operated by a signal from the controller 40 to switch the flow of air.

As explained above, the two supply lines 2 and 3 have air conditioning mechanisms having the same function, and this is a legally required configuration that is implemented in conventional aircraft.

The basic feature of this invention is that a third new supply system is provided in parallel to the first and second supply systems 2 and 3.

4 is the thread path of the new supply system, and this supply system path 4
In this case, an air conditioning mechanism as shown in the first and second supply systems is not provided, and only the above-mentioned air introduction amount control section 30 and a heat exchange section behind it are provided.

As mentioned above, this supply system is a preliminary air conditioning system, and is equipped with an air conditioning mechanism that is as simple as possible, and this is its greatest feature.

In other words, 32 is a flow path switching valve that is operated by its drive section 32' to switch the flow of air that has passed through the control section 30 between introducing it into a heat exchanger 38 to be described later or directly supplying it to the cabin C. It is something.

A heat exchanger 38 cools the high-temperature, high-pressure air from the control unit 30 with the ram air 33, and has the same function as the heat exchangers 24 and 25 in the first and second supply lines.

Reference numeral 34 denotes a ram air introduction amount control valve installed on the ram air introduction side and is operated by a drive section 35 thereof.

36 is a ram air amount control valve installed at the rear of the drive unit 37.
activated by

The amount of ram air is controlled by these control valves 34, 36, and as a result, the cooling function of the heat exchanger 38 is adjusted.

On the other hand, Rc is a temperature sensor that detects the cabin temperature, and lR
p is a temperature sensor that detects the temperature of the supply path 4, and both sensors R
The signals of c and Rp are input to the controller 39.

Then, a control signal output from the controller 39 causes one drive section of the flow path switching valve 32 and the ram air control valve 3 to
The drive units 35 and 37 of 4.36 are controlled and operated to properly condition the air supplied to the cabin C.

By the way, such a third supply system is a backup supply system that operates in place of the first and second supply systems when an abnormal situation such as a failure occurs in the air conditioning system. Normally, the on-off valve 31 is closed.

Then, the circuit is opened and activated by the abnormality occurrence signal of the first and second supply systems.

Detection of an abnormal situation in the first and second supply systems is performed by a sensor ES, and its signal is input to the controller 42.

The controller 42 then controls the supply yarn path opening/closing valve 28'.

Control signals are output to 29' and 31. For example, if an abnormal situation occurs in the first supply line 2, the sensor ES detects it and the controller 42 outputs a control signal to the on-off valves 28' and 31. A control signal is input.

Then, at the same time as the first supply line 2 is closed, the third supply line 4 is opened, and the preliminary air conditioning system starts operating.

It operates together with the second supply system to provide air conditioning within the range required for pre-pressure and ventilation.

This invention characterized by the above content may include various modified embodiments other than the illustrated examples.

First, although the configuration of the first and second supply systems that have been conventionally permanently installed is shown, the illustrated example is only one example thereof, and it is also possible to add various elements other than those shown in the figures, especially regarding the air conditioning mechanism.

Further, the same applies to the configuration of the third supply system 4, which is the gist of the present invention.

For example, in the case of the illustrated example, the air that has passed through the control unit 30 is configured to have two paths, one through which it flows through the heat exchanger 38 and the other through which it flows without passing through the heat exchanger 38, by the flow path switching valve 32. The installation of this flow path switching valve 32 is omitted, and the heat exchanger 38
It is also possible to use one thread path with a thread interposed therebetween.

In the case of the first device provided by this invention, the heat exchanger 3
The cooling capacity adjustment mechanism in No. 8 is not an essential requirement.

The present invention encompasses all of these modified embodiments.

Since this invention is as detailed above, the number of air conditioning systems that are normally used is two, and the other system is an air conditioning system that is as light as possible, and is simplified to facilitate maintenance, inspection, and maintenance. It has advantages such as cost reduction and man-hour reduction.

Moreover, the present invention maintains and improves the precision of air conditioning, and provides an excellent device for air conditioning of aircraft.

[Brief explanation of drawings]

The drawings are block diagrams showing an air conditioner according to the present invention. 2...First supply line, 3...Second supply line, 4...Third supply line, 5, 22, 23,
33... Ram air, 6, 7, 8, 24, 25,
38...Heat exchanger, 26, 27, 32...
...Flow path switching valve, 28゜29.30...Control unit, 31...Supply path opening/closing valve, 9.10,11
, 12...Dehumidifier, 39,40°4L42...
...Feed control device, E...Engine part, C...
...Cabin, Se, Sp, Re, Rp...
Temperature sensor, ES... Abnormality detection sensor, 34
, 36... Ram air control valve.

Claims (1)

[Scope of Claims] 1. The system includes two supply systems, a first and a second supply system, which introduce air from the engine section and supply it to the cabin.
, an introduction amount control section that controls the amount of air introduced into each of the second systems, and a heat exchange section that cools the introduced air with ram air;
The air that has passed through this heat exchange section is adiabatically compressed and expanded by a cooling turbine, and then cooled by ram air in an intermediate heat exchange section.
Air conditioning in the cabin of an aircraft is performed by interposing an air conditioning mechanism consisting of a pressure/temperature adjustment section that mixes and adjusts this and high-temperature air, and a dehumidification section that dehumidifies the air that is pumped into the cabin. In the apparatus, a third supply system is provided in parallel with the first and second supply systems, and the third supply system includes an introduction amount control section that controls the amount of air introduced, and the introduced air is cooled with ram air. An air conditioning mechanism consisting only of a heat exchanger and a heat exchanger is provided, and a supply abnormality detection mechanism is provided in the first and second supply systems, and the third supply system is actuated by a signal from the detection mechanism. An air conditioner for an aircraft, characterized by: 2. It has two supply systems, a first and a second supply system, which introduce air from the engine section and supply it to the cabin.
, a second introduction amount control section that controls the amount of air introduced into each system, a heat exchange section that cools the introduced air with ram air, and a cooling turbine that adiabatically compresses and expands the air that has passed through this heat exchange section. A pressure/temperature adjustment section that cools with ram air in a heat exchange section in the middle and adjusts it by mixing high temperature air with it;
In a device that performs air conditioning in the cabin of an aircraft by interposing an air conditioning system consisting of a dehumidifying section for dehumidifying the air being pumped into the cabin, an introduction amount control section that controls the amount of air introduced and an air conditioning section that controls the amount of air introduced. A third supply system equipped with an air conditioning mechanism consisting solely of a heat exchanger cooled by ram air is provided in parallel with the first and second supply systems, and when an abnormality occurs in the first and second supply systems, The third supply system is configured to operate, and includes a temperature detection mechanism that detects the temperature of the cabin, and a heat exchanger that adjusts the cooling capacity of the heat exchange section in the third supply system based on an output signal from the temperature detection mechanism. An air conditioner for an aircraft, characterized by being provided with an adjustment mechanism.