RU2111152C1 - Air-conditioning system for cabin and equipment compartments of aerobatic aeroplane - Google Patents

Abstract

FIELD: aviation. SUBSTANCE: air-conditioning system includes main for taking air from engine, cold and hot air lines provided with respective adjusting dampers and connected with main feeding the mixed air to cabin compartment; air-conditioning system contains also cooling turbine. Cold air line after cooling turbine is brought in communication with pipe line feeding the cold air to equipment compartments fitted with shut-off damper operated from altitude sensor and cross-connected with throttle valve by means of bypass line. EFFECT: enhanced efficiency. 1 dwg

Description

 The invention relates to aircraft construction, and in particular to systems for heating and cooling crew cabins and compartments of electronic equipment.

 A known system of pressurization of the cabin, comprising a line for taking air from the engine, a cold air line with an air-air radiator, a turbo-cooler, a hot air line, a mixed air supply line to the cabin, an air pressure regulator in the cabin.

 The known system provides pressurization, ventilation and air temperature control in the cockpit of a fighter aircraft, while the cooling of the instrument compartments of the electronic equipment located in the nose and phonon parts of the aircraft is carried out by outboard air supplied under pressure of the high-pressure head to the air intake channel and air blown out cabs to the trans-phonon compartment through a pressure regulator, which is quite enough for equipment with low heat transfer and low density blowing in the compartments.

 However, this system does not provide efficient cooling of the instrument compartments of the electronic equipment with high heat transfer and high saturation of the compartments of the equipment of a maneuverable aircraft.

 Effective cooling of the equipment requires a certain amount of air to be supplied to the compartments, which can be done either by increasing the air intake from the engine, which will lead to a decrease in its power, or by introducing a second additional cooling stage, which may not be possible for layout reasons.

 The invention solves the problem of increasing the reliability of the air conditioning system of the cockpit and instrument compartments of a maneuverable aircraft with one stage of air cooling and increasing the cooling efficiency of instrument compartments with electronic equipment with high heat dissipation without increasing air intake from the engine.

 The problem is solved by maintaining the necessary distribution of air between cabin and instrument compartments at various heights to create comfortable conditions in the compartments.

 The problem is solved due to the fact that the air conditioning system of the cockpit and instrument compartments of a maneuverable aircraft, comprising a line for taking air from the engine, a cold air line with a turbo-cooler placed with it, and a hot air line equipped with appropriate control dampers and connected to the mixed air supply line to cabin compartment, equipped with a cold air line connecting the turbo-cooler to the instrument compartments, a cold air supply pipe plenum compartments, in which a shutter damper controlled by a height sensor is installed, looped by a bypass line with a throttle.

 The invention is illustrated by the schematic diagram of the air conditioning system of the cabin and instrument compartments.

 The air conditioning system of the cabin and instrument compartments contains a highway 1 for taking air from the engine, a hot air line 2, a cold air line 3, and a mixed air supply line 4 to the cabin compartment 5.

 In the hot air line, a control flap 6 is installed, controlled from the control unit of the cabin air temperature controller 7, to which the cabin compartment power switch 8, the air temperature adjuster 9 in the cabin compartment and the air temperature sensor 10 in the cabin compartment are connected.

 The air conditioning system of the cabin and instrument compartments has one air cooling stage, in the cold air line 3 of which an air-air heat exchanger 11, a moisture separator 12, and a turbo-cooler 13 are installed. A control damper 14 is installed in the cold air line 3 and controlled from the control unit 7 of the air temperature regulator in the cabin compartment. The control flap 14 of the cold air line 3 is provided with a bypass line 15 with a throttle 16.

 The hot air line 2 and the cold air line 3 through check valves 17 are connected to the mixed air supply line 4 to the cabin compartment, in which the cockpit cock 18 is installed, connected to the cockpit cock cocktail control sector 19.

 The system provides automatic and manual air regulation by means of control flaps 6 and 14.

 The air pressure regulation in the cabin compartment is automatic according to the set program depending on the flight altitude and is provided by the pressure regulator 20 through the exhaust valve 21.

 To ensure the normal functioning of the electronic equipment located in the bow 22 and the phonon 23 compartments, the system is equipped with a pipe 24 for supplying cold air to the instrument compartments. The pipe 24 is in communication with the cold air line 3 behind the pipe cooler 13. In the pipe 24 for supplying cold air to the instrument compartments, a shut-off valve 25 is installed, controlled from the height sensor 26. The shutter damper 25 is bewitched by the bypass line 27 with the throttle 28 installed therein.

 The air conditioning system of the cabin and instrument compartments operates as follows.

 The air taken from the engine compressor 29, through the overpressure regulator 30 enters the hot air line 2 and the cold air line 3.

 The control flaps 6 and 14 are the actuators of the system, automatically controlled from the setpoint 9 of the air temperature in the cabin compartment, the switch 8 power cabin compartment and the sensor 10 of the air temperature in the cabin compartment or manually using the crane 18 power cabin.

 The temperature regime in the instrument compartments with electronic equipment is supported by the supply of cold air through line 24, and also, for compartments located in the bow, using intake air under pressure of a high-pressure head entering the air intake channel, for instrument compartments located in the phonon part aircraft, additional equipment cooling is carried out by the air leaving the exhaust valve of the cabin compartment.

 An overlapping shutter 25 is introduced into the cold air supply line 24 to the instrument compartments, which ensures the distribution of air between the cabin and instrument compartments required for creating comfortable conditions at all altitude flight modes.

 Up to a height of 4 km, the pressure in the cab and instrument compartments is approximately equal. The air flow taken from the engine is distributed in proportion to the heat loads between the cabin and instrument compartments. At these heights there is a cooling of the electronic equipment of the instrument compartments, since a sufficient amount of cold air is supplied to the instrument compartments.

 With an increase in the flight altitude, excess pressure should increase in the cabin compartment, and from a height of more than 9 km there should be a constant excess pressure, which is ensured by the supply of a large amount of air, therefore, to exclude an increase in air intake from the engine, using the effect of cooling the equipment, from heights of more than 4 km the shutter damper 25, controlled from the height sensor 26, completely closes the pipeline 24 and the minimum dosed amount of cold air enters the instrument compartments along the bypass line 27, and basically th air flow goes to the cabin compartment.

 Thus, for a maneuverable aircraft having one stage of air cooling, comfortable conditions are provided in the cabin and instrument compartments by regulating the distribution of air between us without increasing the amount of air drawn from the engine.

Claims (1)

 The air conditioning system of the cabin and instrument compartments of a maneuverable aircraft, comprising an air intake line from the engine, a cold air line with a turbo-cooler located in it, and a hot air line equipped with appropriate control dampers and connected to the mixed air supply line to the cabin compartment, characterized in that it equipped with a cold air supply line connected to the cold air line behind the turbo-cooler to the instrument compartments, in which the control yaemaya from height sensor shut-off valve, a bypass line electrically connected with the throttle.