RU2714090C1 - Rotorcraft - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: invention relates to the field of aviation, particularly to the rotorcrafts designs. Rotorcraft comprises fuselage with bottom, rotor on shaft connected via reduction gear with gas turbine engine with air intake, compressor, combustion chamber, turbine and nozzle. Gas turbine engine nozzle is made rotary in vertical plane with possibility of its installation in vertical position in emergency mode. Afterburner chamber is arranged between turbine and nozzle. On the fuselage bottom there is a safety platform having a vertical hole for placing the nozzle in emergency mode, the inner cavity of the safety platform is filled with a damping material. Damping material used is honeycomb structure or metal rubber.EFFECT: safe landing at rotor destruction.5 cl, 8 dwg

Description

The invention relates to aviation, and more particularly to rotary-wing aircraft, and is aimed at improving the safety of their flight.

Known safe helicopter according to the patent of the Russian Federation for the invention No. 2333135, IPC ВСС 27/04, publ. September 10, 2008

This helicopter contains a traction engine and a rotor with a vertical axis, on top of which there is an even number, but not less than four blades. The helicopter also contains a connecting device that plays the role of a transmission in the operating mode of the traction engine, and in the operating mode of the starting engines - the role of the overrunning clutch mechanism. Each second rotor blade has a calculated shortened dimension of overall length and includes in its device one or more elementary starting engines, for example, operating on solid fuel. The invention improves safety during emergency landing of a helicopter.

Disadvantage:

Known helicopter according to the patent of the Russian Federation for the invention No. 2335432, IPC ВСС 27/04, publ. 10/10/2008

This helicopter includes a fuselage and coaxial screws, and the screws can be two or more and they can be of different diameters. At least one of the screws is controllable with a variable pitch, and the rest with a fixed pitch. In the second embodiment, the helicopter has a tail boom with an elastic pneumatic chamber at the end, and when the beam is raised, thrust reduction is blocked. In the third embodiment, the engine and gearbox are located in a separate engine nacelle) located above the fuselage on the pylons and / or elastic inserts. The invention improves the efficiency of the rotor.

The disadvantage is the low reliability of the helicopter due to the fact that when one propeller is broken, the thrust of the other is not enough for it to land and, in addition, the occurrence of an imbalance disrupts the operation of the second propeller.

Known helicopter according to the patent of the Russian Federation for the invention No. 2148537, IPC ВСС 7/20, publ. 05/10/2002, the prototype.

This helicopter contains a housing, an air-jet engine for generating thrust for horizontal flight, rotors that are located inside the housing and serve as a compressor for an air-jet engine, an engine that is designed to rotate these rotors, and the cockpit.

A protective net is provided under which the rotors are located. Sashes are located below the net and are designed for take-off and landing.

Disadvantage: poor flight safety due to the fact that when the propeller is destroyed, helicopter landing will almost always lead to catastrophic consequences.

The task of creating the invention: improving the reliability and safety of flight.

Effect: ensuring a safe landing when the screw is destroyed.

The solution to this problem was achieved in a safe helicopter containing a fuselage with a bottom, a rotor on a shaft connected through a gearbox to a gas turbine engine having an air intake, compressor, combustion chamber, turbine and nozzle, so that the nozzle of the gas turbine engine is rotatable in a vertical plane with the possibility its installation in a vertical position in emergency mode.

An afterburner may be provided between the turbine and the nozzle.

On the bottom of the fuselage, a safety platform can be made having vertical openings for accommodating the nozzle in emergency mode, the internal cavity of the safety platform is filled with damping material.

As the damping material, a honeycomb structure may be used.

As the damping material, metal rubber may be used.

The essence of the group of inventions is illustrated in the drawings (Fig. 1 ... 8), where:

- in FIG. 1 shows a diagram of a safe helicopter,

- in FIG. 2 is a view A of FIG. 1,

- in FIG. 3 shows the design of the gas turbine engine of a safe helicopter, the first option in the working position,

- in FIG. 4 shows the design of the gas turbine engine of a safe helicopter, the first option is in an emergency position,

- in FIG. 5 shows the design of the gas turbine engine of a safe helicopter, the second option is in the working position,

- in FIG. Figure 6 shows the design of a safe helicopter gas turbine engine, in a variant in working position

- in FIG. 7 shows the security platform,

- in FIG. Figure 8 shows section B - B.

The safe helicopter (Figs. 1 and 2) contains the fuselage 1, the main rotor 2, the tail 3, the control screw 4, the shaft 5 connecting the screw 2 through the gearbox 6 to the power take-off shaft 7 from the gas turbine engine 8.

A safety platform 10 is fixed on the bottom 9 of the fuselage 1, the cavity 11 of which is filled with a damping material 12. A honeycomb filler or metal rubber can be used as the damping material 12. In the safety platform 10, a central hole 13 is made 13. Landing bearings 14 are attached to the bottom 9.

The gas turbine engine 8 (GTE) contains (Fig. 3 and 4) an air intake 15, a compressor 16, a combustion chamber 17 with nozzles 18, a turbine 19 and a nozzle 20. The nozzle 20 is mounted on a hinge 21 and has a rotation drive 22. The nozzle 20 of the gas turbine engine 8 made rotatable in a vertical plane with the possibility of its installation in a vertical position in emergency mode (Fig. 1 and 3). The rotation drive 22 must ensure the rotation of the nozzle 20 by an angle from 0 to 95 °.

A second option is possible with the execution between the turbine 19 and the nozzle 20 of the afterburner 23 (Fig. 3). The use of afterburners in gas turbine engines on supersonic aircraft is known. They allow you to briefly increase the speed of the aircraft at the cost of high fuel consumption.

In helicopters, gas turbine engines with afterburner have never been used.

The gas turbine engine 8 according to the first embodiment (Fig. 2) has one main fuel system 24.

The main fuel system 21 comprises a fuel line 25 in which a fuel pump 26 is connected to the drive 27.

According to the second option (Fig. 3 and 4), the gas turbine engine 8 has two fuel systems: the main 24 and afterburner 28.

The afterburning fuel system 28 (FIG. 3) comprises a fuel line 29 in which an afterburning fuel pump 30 is connected to the afterburner drive 31 and afterburning manifold 32.

The gas turbine engine 8 is mounted horizontally in the center of mass of the fuselage 1 of the helicopter (Fig. 1).

The safety platform 10, as mentioned previously, has a central hole 13 made vertically on an axis passing through the center of mass of the helicopter. The diameter of the central hole 13 D _{0 is} larger than the cut-off diameter of the nozzle 20 - D _c .

D ₀ ≥D _c .

In addition, the slice of the nozzle 20 in the working position goes into the expanding channel 33 (Fig. 2).

WORK OF THE RUNWING AIRCRAFT IN NORMAL

MODE, 1 option

Using a starter (not shown), unscrew the rotor (not shown) of the gas turbine engine 8 and start the drive 27, which spins the fuel pump 26, fuel (aviation kerosene) is fed through the fuel pipe 25 to the nozzles 18 of the combustion chamber 17, where it is ignited using a pilot light (not shown). The combustion products pass through the turbine 19. The power from the turbine 19 is transmitted to the compressor 16, which compresses the air flowing through the air intake 15. Compressed air is supplied to the combustion chamber 17 to maintain the combustion process. In the main modes (in flight), a stream of exhaust gases from the nozzle 20 flows into the channel 33 (Fig. 2).

The jet thrust of the gas turbine engine 8 is transmitted to the fuselage 1, which, together with the thrust of the propeller 2, ensures the flight of the rotorcraft and its landing in normal mode. The thrust ratio of the screw 2 is 1.1 ... 1.2.

HELICOPTER OPERATION IN EMERGENCY MODE, first option

When the screw 2 is broken, the nozzle 20 is turned in the vertical plane by means of the drive 22 until it is installed in the vertical position (Figs. 3 and 4). The nozzle 20 is installed with its cut in the Central hole 13 of the safety platform 13 strictly vertically (Fig. 4).

The thrust generated by the nozzle 20 is sufficient for a soft landing of the helicopter.

HELICOPTER AIRCRAFT OPERATION IN EMERGENCY MODE, second option

If necessary, the afterburning fuel system 28 is activated (Figs. 5 and 6), for this, an afterburner drive 28 is launched, which spins the fuel pump 27, fuel (aviation kerosene) is supplied through the fuel line 26 to the afterburner manifold 29 of the afterburner 21, where it is ignited by igniter (not shown). The combustion products through the nozzle 20 expire vertically downward.

The thrust generated by the nozzle 20 increases by 75% compared to the afterburner mode, which compensates for the absence of screw 2.

The use of afterburner allows you to design a gas turbine engine of smaller dimensions and weight.

The application of the invention allowed:

- to ensure a safe landing when the screw is destroyed,

- save the life of the crew and passengers.

Claims (5)

1. A rotorcraft containing a fuselage with a bottom, a rotor on a shaft connected through a gearbox to a gas turbine engine having an air intake, a compressor, a combustion chamber, a turbine and a nozzle, characterized in that the nozzle of the gas turbine engine is rotatable in a vertical plane with the possibility of it vertical installation in emergency mode. 2. The rotorcraft according to claim 1, characterized in that an afterburner is made between the turbine and the nozzle. 3. A rotary-wing aircraft according to claim 1, characterized in that a safety platform is made on the bottom of the fuselage, having a vertical hole for placing the nozzle in emergency mode, the internal cavity of the safety platform is filled with damping material. 4. The rotorcraft according to claim 3, characterized in that the honeycomb structure is used as a damping material. 5. The rotorcraft according to claim 3, characterized in that metal rubber is used as the damping material.

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