JPS5831236A - Air conditioner for aircraft - Google Patents

Abstract

PURPOSE:To decrease the quantity of cooling air to be taken in, and to economize combustion by disposing heat pipes into an introducing pipe to the primary heat exchanger of high-pressure high-temperature air extracted from an engine and a cabin air exhaust pipe and giving the potential heat of high-temperature air to exhausted air. CONSTITUTION:One part of the potential heat of the high-pressure high-temperature air of the engine 1 is discharged to the exhaust 11 of a cabin 10 through the heat absorbing section 22 andheat radiating section 23 of the heat pipe 21 and the temperature is dropped, and the air flows into the primary heat exchanger 3, and is cooled by cooling air taken in through a valve 14. The air is compressed adiabatically by means of a compressor 5. The potential heat of the air is radiated to the exhaust 11 through the heat absorbing section 26 and heat radiating section 27 of the heat pipe 25, and the air is forwarded to the cabin 10 through a secondary heat exchanger 7, an expander 6 and a mixing chamber 9. Accordingly, the quantity of cooling air being taken in is decreased by dropping the temperature of air flowing into the primary and secondary heat exchangers 3, 7, while the airframe resistance is reduced, and fuel consumption can be economized.

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to an improvement in an aircraft air conditioner.

Air conditioning equipment used in aircraft is a device that adjusts air to an appropriate temperature and sends it into the control room and passenger cabin (hereinafter collectively referred to as the cabin). It is also used in conjunction with a pressure regulating valve to reduce the pressure of high-temperature, high-pressure air extracted from the engine, known as bleed air.

The mainstream is now the air cycle system, which uses heat exchangers, cooling turbines, etc. to adjust the temperature appropriately before supplying it to the cabin.

In this conventional air cycle system, cooling in the heat exchanger is performed by using cold air taken in from the atmosphere via a ram air scoop during flight; This creates resistance to the aircraft and increases fuel consumption accordingly.

As a means of suppressing this increase in fuel consumption, before the bleed air is introduced into the heat exchanger, a portion of the heat contained in the bleed air is transferred from the cabin to maintain a constant pressurization and ventilate the air. Since the load on the heat exchanger can be reduced, the amount of cooling air required can be reduced.
Accordingly, the resistance of the aircraft during flight can be reduced. -By adding heat to the cabin exhaust air, it increases its temperature and expands its volume, resulting in an increase in its exhaust speed and a thrust effect on the aircraft. Therefore, both of these can improve the fuel efficiency of the aircraft compared to the conventional method.

The present invention is based on the concept described above, and is an object of the present invention to provide a device that eliminates the above-mentioned drawbacks of conventional aircraft air conditioners and makes it possible to further reduce fuel consumption.

High-temperature, high-pressure air extracted from the engine is cooled by a primary heat exchanger, further boosted in pressure by a compressor, cooled again by a secondary heat exchanger, and then supplied to an expansion turbine that rotationally drives the compressor. Adiabatically expanded and cooled air is sent into the cabin through a mixing chamber, and a portion of the cabin air is sent back from the cabin to the mixing chamber for circulation, and the same amount of air as the amount of air sent is sent to the cabin. In the apparatus, the air conditioning and pressure adjustment of the cabin is performed by discharging the air from the air to the outside air through an air discharge pipe, at least the high temperature and high pressure air intake pipe of the fire heat exchanger and the air discharge pipe of the cabin. Aircraft air, characterized in that a heat pipe is disposed between the air and the heat pipe, and a part of the heat held by the high-temperature, high-pressure air is imparted to exhaust air discharged from the cabin to the outside of the aircraft. It depends on the harmonization device.

DESCRIPTION OF THE PREFERRED EMBODIMENTS An example device according to the present invention will be described below with reference to the drawings. The figure is a schematic explanatory diagram of the main parts constituting this device. In the figure, (1) is the engine, (
2) From then on, high temperature and high pressure, e.g. 260℃, 7 kg
/cm2abs of air (bleed air), (3) is a fire heat exchanger, and (4) is a bleed air intake pipe from the bleed pipe (2) to the fire heat exchanger (3).

(5) is the compressor (turbo blower), f6) is the expansion turbine (cooling turbine) that rotates it,
+71 is a secondary heat exchanger, (8) is a high pressure water separator, (9
) is the mixing chamber (Blenheim), Qlll is the cabin (pressurized room), fill is the air exhaust pipe, (12
is the temperature sensor, (131 Haram valve controller, (+41.
171 is each actuator.

In addition, (181 is a plenum (
9) A flow rate adjustment valve that adjusts the temperature of the air entering the O
9 is its actuator, and ■ is a valve controller that outputs an output signal from the actuator (1) based on the input signal from the temperature sensor (1i) of the cabin (1).

on, w is heat pipe c! 1)
- High temperature and high pressure air intake pipe (4) to the fire heat exchanger (3)
and the air exhaust pipe 111, and a heat pipe (to) is arranged side by side between the high temperature and high pressure air intake pipe to the secondary heat exchanger (7) and the air exhaust pipe (11). ing. Prisoner, (
2Iil is heat pipe CI! 11. (251 fidgets,
(2) and (5) are heat pipes B1).

(To) Now, it's the heat dissipation part. Heat pipe bu C!
1+, (251) is installed inside the fuselage of an aircraft that assumes various postures during flight, so it is sealed in a pipe in the air and has a means for circulating the working fluid (for example, capillary action) A working fluid (for example, water or a diphenyl-based heat medium) compatible with the operating temperature is sealed.

Next, the operation of this device will be explained.

Assume that an aircraft equipped with this device is flying at high altitude and high speed. Extracted from engine (1) 1. The high temperature and high pressure air (bleed air) passes from the bleed pipe (2) to the air intake pipe (4) before entering the primary heat exchanger (3).
A part of the heat held in the heat pipe inserted into the air intake pipe (4) is absorbed and removed by the heat absorption zone, thereby lowering the temperature. ). -For the fire heat exchanger (3).

□ Intake via ram air scoop (not shown)
Since the flow rate of the cold air is adjusted by the flow rate regulating valve (141) and sent, the bleed air is cooled and its temperature is further lowered before it flows into the compressor (5). - Resolute exchanger (3) The bleed air cooled by The bleed air is sent to the secondary heat exchanger (7).

Well, before inserting it into the bleed air intake pipe.

A part of the heat held by the heated heat pipe (25) is absorbed in the heat absorption part (25) in the same manner as described above, and the temperature is lowered by removing it.
), the flow rate is adjusted by the flow rate adjustment valve 09, and the cold air is further cooled in the secondary heat exchanger (7), and the temperature is lowered to near the outside air temperature.

Water is removed by passing through a high pressure water separator (8).

12. If the temperature drops to near the outside temperature. The bleed air from which moisture has been removed flows into the expansion turbine (6).

Due to adiabatic expansion, it is cooled to a temperature below 0°C, for example, about -10°C, and then sent to the mixing chamber (9). When the temperature of the cold air cooled by the expansion turbine (6) falls below a predetermined temperature (for example, -10°C), the ram valve controller 1, which has received the signal from the temperature sensor O2, activates the actuator (161, ( 171
Heson n, zo n-i issue, flow rate adjustment valve (141, +
151 (7) Decrease the opening degree, -secondary heat exchanger (3
) Control to reduce cooling air to both J71. On the other hand, when the cold air temperature exceeds the predetermined temperature, the ram valve controller αJ operates the flow rate adjustment valve (141,
Increase the opening degree of 151 and create 1 heat exchanger + 31. (Control to increase cooling air to 71. Mixing chamber (9).

1. The expansion turbine (6) mixes cold air that has been cooled to a predetermined temperature with hot air that has bypassed the turbine (6) to supply air that has been made to an appropriate temperature.1. Along with.

Approximately the same amount of air is sent back from the cabin and mixed uniformly in the mixing chamber (9).1.1
Let's put them together and send them off to the cabin.

Ru. The cabin temperature is determined by receiving a signal from temperature sensor d and outputting an output signal to actuator 0 (g).
/F':ff This is done by controlling the flow rate of hot air through the flow rate adjustment valve. In this way, cabin α is maintained at an appropriate temperature by the air flowing in and out of it, and a pressurization device (not explained) pumps out excess air to maintain the pressure at roughly the same level as atmospheric pressure on the ground. It is discharged from the aircraft from the discharge pipe.

By the way, in this device, the heat pipes are
(To) is the endothermic part (branch) of Sowa, Zon, (in 281,
Bleed air or primary heat exchanger (3), compressor (5)
), the bleed air is once cooled, and then the pressure is increased to raise the temperature.The bleed air constantly absorbs part of its heat as the latent heat of vaporization of the working fluid. Primary heat is constantly radiated as latent heat of liquefaction when the working fluid condenses in the heat radiating section (a(8)).

Before high-temperature, high-pressure air is taken into the secondary heat exchanger (31, +71), a part of the heat held in it is continuously transported, and the air exhausted from the cabin αG is passed through the air exhaust pipe 0. It emits water to heat it.

This means that the -order, secondary heat exchanger +31. Regarding +71, the load on it will be reduced by the amount of heat removed through the heat pipe c+u (251),
This reduces the amount of cooling air that the plant requires.

The resistance of the aircraft during flight can be reduced depending on the stiffness,
In addition, heat is added to the cabin exhaust air, which causes its temperature to rise and its volume to expand, resulting in an increase in its exhaust speed, which gives the aircraft a thrust I effect. can do. Therefore, both of these can improve the fuel efficiency of the aircraft compared to the conventional method.

As is clear from the above description, in the aircraft air conditioner according to the present invention, a heat pipe is arranged between at least the high-temperature, high-pressure air intake pipe of the primary heat exchanger and the air exhaust pipe of the cabin. ,.

A part of the heat held by the high-temperature, high-pressure air is imparted to the exhaust air discharged from the cabin to the outside of the aircraft through this heat pipe.1. The load on the heat exchanger can be reduced by the amount of heat that is removed via the heat pipe, and the amount of cooling air taken into the fuselage via the ram air scoop can accordingly be reduced. Therefore, the resistance of the aircraft during flight can be reduced accordingly.

By adding more heat to the cabin exhaust air, it is possible to raise its temperature and expand its volume, thereby increasing its exhaust speed and imparting a plasto effect to the aircraft.

A heat vibrator should also be installed between the high-temperature, high-pressure air intake pipe of the secondary heat exchanger and the cabin air exhaust pipe.
．． Furthermore, the above effects can be further enhanced.

Therefore, the present invention provides an aircraft system that reduces the resistance of the aircraft body during flight and actively applies thrust to one aircraft body compared to conventional devices, thereby making it possible to further save fuel consumption. It was possible to provide an air conditioner.

[Brief explanation of the drawing]

The figure is a schematic explanatory diagram showing the main part of the configuration of the embodiment device according to this description. (1)...Engine, (3)...--Determined exchanger, (4)...High-temperature, high-pressure air intake l, pipe, (5)... ... Compressor, (6) ... Expansion turbine, (7) ... Secondary heat exchanger, (9) ...
...Mixing chamber, 00...Cabin, 01j...Air exhaust pipe, cause), (c)
... Heat pipe, aZ, ■ ... Heat absorption part. (c), □... Heat dissipation part.

Claims (1)

[Claims] High-temperature, high-pressure air extracted from the engine is cooled by a primary heat exchanger, further boosted in pressure by a compressor, cooled again by a secondary heat exchanger, and then supplied to an expansion turbine that rotationally drives the compressor, Air that has been adiabatically expanded and cooled by this turbine is sent into the cabin via a mixing chamber, and at the same time, in order to circulate a part of the cabin air, air is sent back from the cabin to the mixing chamber, and the same amount of air as the amount of air sent in is sent back to the mixing chamber. In the device for air conditioning and pressure adjustment of the cabin by discharging air from the cabin to the outside air via an air exhaust pipe, at least the high-temperature and high-pressure air intake pipe of the secondary heat exchanger and the A heat pipe is disposed between the air exhaust pipe of the cabin and a part of the heat held by the high-temperature, high-pressure air is imparted to the exhaust air discharged from the cabin to the outside of the aircraft through the heat pipe. An aircraft air conditioner characterized by: