SK50142011U1 - Auxiliary power unit of helicopters - Google Patents

Abstract

The technical solution relates to auxiliary power unit and connect it to the air conditioner inside of the helicopter. Auxiliary power unit in accordance with the present invention is formed as a single-board power source working independently from the main engines of the helicopter.

Description

Helicopter auxiliary power unit

Technical field

The technical solution concerns the auxiliary power unit and the air conditioning unit of the helicopter interior.

BACKGROUND OF THE INVENTION

Known auxiliary power units serve as a source of compressed air for starting the main engines of aircraft on the ground and in flight, supplying the on-board power supply for checking electrical and radio equipment on the ground, supplying the on-board power supply in flight in case of disengaged power supplies. Various means and air conditioning systems independent of the auxiliary power unit are used to adjust the air temperature in the helicopter cabs.

In a multipurpose twin-engine helicopter of a conventional configuration with a five-blade carrier and a three-blade balancing rotor, it is known to use a combination of an auxiliary power unit and air heating in the helicopter cockpit and cargo compartment using an air heater.

This system has the disadvantages that due to the rescue of the auxiliary power unit (durability and overall reliability) the number of starts of the main helicopter engines is limited; the starting of the main engines is only possible at a limited height, ie when the helicopter lands at a height higher than 3000 m above sea level. (eg in mountainous conditions), it is often not possible to shut off the engines for safety reasons and to load and load cargo or persons under the rotating rotor when the main engines are on; in the cockpit and helicopter cargo compartment (passenger compartment), air can be heated by the air heater and maintained at a ventilated temperature. Cooling of air in helicopter cabins against the surrounding environment is not possible, only in flight it is possible to open the air vents or doors, reduce the temperature in the helicopter, ie. when flying a helicopter in a high-temperature environment, the air heater becomes an unnecessary or unnecessary device; before the helicopter takes off at higher temperatures it is not possible to adjust (reduce) the air temperature in the helicopter cabins to the standard (comfort) value by the on-board system.

Aircraft air conditioning systems are also known to maintain a constant environment in the pilot or cargo compartment of aircraft or helicopters. All systems are designed for a specific airplane to suit the main aircraft engine, which serves as a source of compressed air, ie. compressed air taken from the main engine compressor is used to supply the air conditioning.

Separate electric air conditioning units are also used.

The aim of the technical solution is to create an embodiment of the auxiliary power unit and its associated air conditioning system, which would eliminate the above mentioned disadvantages.

The essence of the technical solution

The above-mentioned disadvantages are overcome by the auxiliary power unit according to the present invention, which is designed as an autonomous (autonomous) on-board power source, operating independently of the main helicopter engines. The unit allows the helicopter to operate independently of ground equipment (start engines and airplane systems), provides all functions even when the main engines are off, even in extreme conditions, and allows its use as a source of compressed air to supply compressed air to the air conditioning system.

The unit is primarily intended for supplying compressed air to the helicopter main engine launch system on the ground and in flight and for supplying compressed air for air conditioning. The air conditioning system operates, either in flight or on the ground, even when the main engines are switched off, on the principle of air extraction from the auxiliary power unit and regulates the temperature of the air to reach the required temperature in the cabins. . In the event of a helicopter's on-board mains power failure in flight, it provides electrical power supply as a substitute source (to enhance flight safety) and also on the ground with the main engines off, as required by the crew. Due to the unit's resursion, an unlimited number of main engine starts, main engine starts at high altitudes (eg mountain conditions), and helicopter flight operations are possible.

Replacing the air heater with the air conditioning system will significantly improve the conditions on board the helicopter both before the helicopter itself and during the flight.

The auxiliary power unit consists of a separate airborne combined energy source, the air outlet of which is connected to the main engines and the helicopter air-conditioning unit via a change-over valve, the auxiliary power unit being connected to the on-board fuel system of the helicopter.

The air conditioning unit is connected to a pressure indicator, a signaling board and a starter, further connected to a temperature selector and connected to a cabin thermostat and a changeover valve to which the individual pilot and cargo cabins are connected.

The auxiliary power unit includes an oil pump, oil cleaner, block of filters and servomechanisms, a fuel filter, a fuel pump, an ignition box connected to the spark plugs, a speed sensor and an exhaust gas temperature sensor, the auxiliary power unit connected to the signaling board fuel filter, signaling board oil and signaling valve and further to a control box which is connected to the status signaling box, the temperature indicator, the signaling panel on / off and the starter control unit.

Unlike the original power unit, whose resurs are limited by the low number of working hours and the number of engine starts, which is due to its design, the auxiliary power unit according to the invention allows operation concurrently with prescribed dragon or helicopter engine resursions. The auxiliary power unit serves as a source of compressed air, electrical energy and for driving the hydraulic system.

BRIEF DESCRIPTION OF THE DRAWINGS

Fig. 1 shows an example of deployment of the auxiliary power unit and air conditioning unit in the helicopter. In FIG. 2 shows a block wiring of the auxiliary power unit. In FIG. 3 shows a block wiring of the air conditioning unit.

EXAMPLES

Figure 1 shows in plan and elevation the layout of the new auxiliary power unit i SAFIR 5K7G MIS and air conditioning unit 2 ECS-MI in a multipurpose twin-engined helicopter of the classic Mi-17 and 171 series with TV3-117 series engines . This new installation is a substitution of the original installation of the auxiliary power unit type AI-9V and air heater KO-50, the new installation is located where the original power unit and air heater.

For this purpose, it was only necessary to make some technical adjustments to the fuel and electrical installation, air distribution, and to supplement (or modify) the controls and controls that would enable this replacement (installation) to be carried out in accordance with the applicable legislation.

In the present case, the center control panel 3, the power distribution box 4, the right-hand electrical panel 5 and the right-hand control panel 6 have been modified.

The figure also shows the location of the status signaling box 7 of the auxiliary power unit I, the control unit 8 of the LUN 5271.80 / CONA of the auxiliary power unit 1, the two-starter control unit 9 D25-800 and the hermetic passage 10 for the wiring harness of the auxiliary power unit 1.

Figure 2 shows the wiring of the auxiliary power unit.

The auxiliary power unit i SAFIR 5K / G MIS consists of a separate airborne combined energy source, such as compressed air and electrical power, which is connected to the helicopter main engines 12 and helicopter air conditioner 13 via a change-over valve 11 and the auxiliary power unit 1 is connected to the onboard fuel system 14 of the helicopter. Change-over valve U is connected to control 11 '.

The i unit is designed for reliability and overall service life. Both of these characteristics can be expressed by the time of failure-free operation of the unit and its parts under specified conditions, the time between unit overhauls and total life. The auxiliary power unit 1 of the SAFÍR K / G series includes an oil pump 15 LUN 6320.02, an oil cleaner 16 LUN 7627.02x, a filter block and servo 17 B1-048810276, a fuel filter 18 B3-0488-10791, a fuel pump 19 B2-0488-10381 , ignition box 20 9049800-4 connected to spark plugs 21 CH34630, speed sensor 22 LUN 1308-8 and exhaust gas temperature sensor 23 LUN 1385.81. The auxiliary power unit 1 is connected to the signaling panel fuel filter 24, the signaling panel oil 25 and the signaling panel 26 610200A and further to the control box 27 LUN 5271-80, which is connected to the status signaling box 28, temperature indicator 29 LUN 1386-01 signaling panel on / off 30 (ON / OFFJ and start / stop unit 31) This is connected to the accumulator bus 32 + 27VDC. From the picture it is clear that the resistor 33 25 tn as well as backup generator is connected to this bus. 34 and control 35, which are connected to control unit 36 D25-500. Resistor 33 is connected to starter generator 37 THALES 5155

340 and this to V A meter 38 and control unit 36. A differential relay 40 DMR-400 is connected to the accumulator bus 32.

Figure 3 shows the block wiring of the ECS air conditioner 13.

The air conditioning unit 13 is connected to a pressure indicator 42 LUN 1491.22, a signaling board 43 CS STOP and a switch 44 CS STOP, CS START, further connected to a temperature selector 45 LUN 5886.2 and connected to the cabin thermostat 46 LUN 5889.2. Further, the unit 13 is connected to a changeover valve 47, which is connected via air distributions 0 - 100 ^° C (heated, cooled) to the individual cockpits 48,49 of the upper and lower and the cargo cabin 50,51 of the upper and lower. Compressed air from the auxiliary power unit 1 is supplied to the air-conditioning unit 13 via a change-over valve with control 11 '.

Claims (3)

Protection claims A helicopter auxiliary power unit, characterized in that it comprises a separate airborne combined power source which is connected to the helicopter's fuel system (14) and comprises a compressed air source whose outlet (52) is through a controlled bypass valve (14). 11) connected to a main engine starting system (12) and an air conditioning unit (13) for controlling the air temperature in the individual helicopter cabins (49 to 51). A unit according to claim 1, characterized in that the air conditioning unit (13) is connected to a pressure indicator (42), a signaling board (43) and a starter (44), further connected to a temperature selector (45) and connected to a cabin thermostat (46) and a controlled changeover valve (47) to which the individual upper and lower (48) and (49) pilot cabins and the upper and lower (50) and (51) cargo cabins are connected via air distributions. Unit according to one of the preceding claims, characterized in that the auxiliary power unit (1) comprises an oil pump (15), an oil cleaner (16), a filter and servomechanism block (17), a fuel filter (18), a fuel pump (15). 19), the ignition housing (20) connected to the spark plugs (21), the speed sensor (22) and the exhaust gas temperature sensor (23), the auxiliary power unit (1) being connected to the signaling panel of the fuel filter (24), oil (25) and signaling valve (26) and further to a control box (8) connected to the status signaling box (7), temperature indicator (29), signaling panel (30) and start / stop unit (31) which is connected to the accumulator bus (32).