JP2003185278A - Air conditioning system for airplane - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide an air conditioning system for an airplane which feeds a prescribed amount of air to a cabin even if reducing an engine bleed air flow and lowering a penalty to the engine. <P>SOLUTION: A turbine 13 is driven by engine bleeding, the turbine power is mechanically transmitted to a compressor 15, and the compressor 15 feeds a recalculation air from an air conditioning object such as the cabin 14 to the turbine 13 after compression and drives the turbine 13 along with the engine bleeding. When the engine bleeding and the recalculation air after passing the turbine 13 is fed to the cabin 14, etc., the power is applied to the compressor 15 by an assist motor 17. <P>COPYRIGHT: (C)2003,JPO

Description

Description: BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an air conditioning system mounted on an aircraft or the like. 2. Description of the Related Art In a conventional air conditioning system for an aircraft shown in FIG. 2, an air bleed from an engine 51 is cooled by ram air in a primary heat exchanger 52 and a cabin 5 is provided.
4 is compressed by the compressor 55 and the air cooled by the ram air in the secondary heat exchanger 56 is adiabatically expanded by the turbine 53, so that the air that has been subjected to thermal work and has become low in temperature is separated by the water separator 58. To separate the water and supply it to the cabin 54. [0003] The recirculation air flowing out of the cabin 54 and the like is compressed by a compressor 55 driven via a shaft 59 by the turbine power generated by the thermal work in the turbine 53, and cooled by a ram air in a secondary heat exchanger 56. Then, it is supplied to the turbine 53 again together with the engine bleed air. However, in such a conventional air conditioning system for an aircraft, the driving force of the turbine 53 depends on the amount of engine bleed air as a power source in the turbine 53. Reducing the amount of engine bleed air in order to reduce the penalty for reducing the amount of recirculated air from the cabin 54 reduces the amount of air to be supplied to the cabin 54 and the like again. . In particular, an airframe with many passengers, such as a passenger airplane, requires a very large amount of ventilation air. Therefore, there is a limit in reducing the amount of engine bleed air, and there is a problem that the efficiency of the aircraft is greatly reduced. Accordingly, an object of the present invention is to provide an air conditioning system for an aircraft that can supply a predetermined amount of air to a cabin or the like even if the amount of engine bleed air is reduced and the penalty for the engine is reduced. An air conditioning system for an aircraft according to the present invention drives a turbine by bleeding an engine and mechanically transmits the turbine power to a compressor. Compressing the circulation air before sending it to the turbine, driving the turbine together with the engine bleed air, and applying power to the compressor by the assist motor when supplying the engine bleed air and recirculation air after passing the turbine to the air-conditioned object. Features. FIG. 1 shows an air conditioning system for an aircraft according to an embodiment of the present invention. The engine bleed air from the engine 11 is configured to be cooled by the ram air in the primary heat exchanger 12 and then introduced into the turbine 13. On the other hand, air discharged from an area to be air-conditioned such as a cabin 14 or a cockpit is introduced into the turbine 13 after being compressed by the compressor 15 and cooled by the ram air in the secondary heat exchanger 16. Be composed. The turbine 13 is driven by thermal work by adiabatic expansion of the introduced engine bleed air and air from the cabin and the like, and the compressor 1
5 is configured such that its turbine power is transmitted mechanically via a shaft 19. Further, the shaft 19 is provided with an assist motor 17 for applying power to the turbine power. For example, the assist motor 17 is
9 is provided with a magnet rotor at least in part and a motor in which a coil is arranged in the vicinity of the magnet rotor. In this embodiment, the assist motor 17 is disposed between the turbine 13 and the compressor 15 on the shaft 19,
The shaft 19 is extended on at least one side of the turbine 13 or the compressor.
May be arranged. The air cooled by passing through the turbine 13 is configured to be supplied to the cabin 14 and the like after excess water is removed by the water separator 18. On the other hand, the recirculated air flowing out of the cabin 14 and the like is compressed, and the secondary heat exchanger 1
At 6, it is configured to be cooled by the ram air and supplied to the turbine 13 together with the engine bleed air. It should be noted that the compressor 1
5. The path of the air that passes through the secondary heat exchanger 16 and reaches the turbine 13 is defined as the first air path in the claims, and the path of the air that passes from the turbine 13 through the water separator 18 to the cabin 14 is claimed. The second air path in the range. Next, the operation of the aircraft air conditioning system of the present embodiment will be described with reference to FIG. The air obtained by cooling the engine bleed air from the engine 11 by the ram air in the primary heat exchanger 12 and the air obtained by compressing the recirculation air from the cabin 14 or the cockpit with the compressor 15 are combined, and adiabatically expanded by the turbine 13.
Air that has become low temperature due to hot work is separated into water separator 1
After passing through 8, water is separated and supplied to the cabin 14. At this time, the recirculated air flowing out of the cabin 14 and the like is compressed by the compressor 15 driven through the shaft 19 by the turbine power generated by the thermal work in the turbine 13, and cooled by the ram air in the secondary heat exchanger 16. After that, the fuel gas passes through the water separator 18 together with the engine bleed air and is supplied to the turbine 13 again. In this embodiment, the assist motor 17 for applying power to the shaft 19 is provided. Even if the amount of engine bleed air as a power source in the turbine 53 is reduced, the recirculated air is supplied to a portion required for air conditioning. Since a fixed amount can be obtained, sufficient air can be supplied to the cabin 14 and the like. Therefore, necessary air conditioning can be performed while maintaining the performance of the engine during flight. During the stable flight of the aircraft, the amount of engine bleed air can be increased to the extent of the conventional art so as not to hinder the flight. Therefore, it is possible to reduce the power supplied to the assist motor 17 to save energy. According to the present invention, since the power is applied to the compressor by the assist motor, a power source for the compressor which is dependent only on the engine bleed can be newly obtained. Even if the penalty for the engine is reduced, the required amount of air for air conditioning can be supplied to the cabin and the like.

[Brief description of the drawings] FIG. 1 is a schematic configuration diagram of an aircraft air conditioning system of the present invention. FIG. 2 is a schematic configuration diagram of a conventional aircraft air conditioning system. [Explanation of symbols] 13 Turbine 14 cabins 15 Compressor 17 Assist motor

Claims (1)

Claims: 1. A turbine driven by engine bleed air, a compressor to which the turbine power is transmitted mechanically, and the compressor takes in recirculated air from an object to be air-conditioned and compresses the recirculated air. A second air provided to drive the turbine by a first air path provided to the turbine and recirculated air sent to the turbine and the engine bleed air, and thereafter to be supplied to the air-conditioned object; An air conditioning system for an aircraft, comprising: a route; and an assist motor for applying power to the compressor.