RU2542842C2 - Aircraft electromechanical power plant - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to hybrid aircraft power plant designs. Aircraft electromechanical power plant consists of group of screws each one of which is rotated via reducing gear from electric motors being fed from high=power electrical power plant with one internal combustion engine. The power plant is made with possibility of accumulator charging and feeding cruise screw electric motors by generators powered by horizontal air screws rotating in autorotation mode under incoming high-speed air flow.

EFFECT: higher flight safety, lower expenditures connected with aircraft equipment operation.

6 dwg

Description

The technical field to which the invention relates.

The invention relates to a power propulsion system of aircraft with propulsion of the propellers in rotational motion, creating thrust for the movement of aircraft, helicopters.

State of the art

An analogue of the invention is the propeller drive of the TU114 aircraft, MI12.26 helicopter, gyroplanes.

Disclosure of invention

The invention is economically advantageous for aircraft with a take-off weight of over 100 tons and using two or more propellers from electric motors for takeoff to drive the propellers into rotational motion.

The essence of the invention consists in the following and is aimed at solving a specific technical problem: a) combined use for moving forward, take-off from take-off and landing of mid-flight and horizontal propellers, and for vertical take-off and landing of horizontal large-diameter screws of 28 m, creating a pulling force upwards, rotationally driven by high-power electric motors powered by: GTU6 electric power plant operating from one drive electric motor or from onboard generators, each rotor of which is mounted on a common motor shaft and rotates from autorotation of horizontal screws under the influence of an incoming air stream; b) the use of an electric power plant as a fuel for a driving engine, feeding electric motors of electromechanical screw drives, liquefied gas, its mixture with hydrogen (produced directly on the sea by airborne seaplane installations); c) reducing the weight of the aircraft due to the use of electric motors to drive screws having less weight compared to internal combustion engines, and, accordingly, an increase in carrying capacity; d) the creation of high reliability of the drive due to the separate rotation of the axes of the planetary gear reducer sustainers. Since if one gearbox line fails, the other will provide traction for movement e) ensure flight safety, landing and take-off of the aircraft by using, if necessary, marching and horizontal propellers or marching propellers with simultaneous free rotation of horizontal propellers in autorotation mode from incoming air flow or spin up to 200 rpm before takeoff.

As a result of solving this technical problem, it will be significant: a) the cost of building aircraft is reduced, since the cost of electric motors is lower than aircraft engines (the cost of valve jet electric motors is 40-60% lower than similar collector or asynchronous electric motors); b) the cost of transporting and operating aircraft with a take-off weight of 100 tons or more, using 2 or more propellers driven by electric motors, has been reduced due to the use of the GTU 4 or GTU 6 electric power plant with one D30 drive motor for powering electric motors or the use of onboard electric generators; c) increased traffic safety in flight mode, since during acceleration for take-off and landing, the propulsion engine and take-off propulsion system will be used with horizontal propellers, while horizontal propellers rotating with autorotation from the air stream will provide a planning landing when the motors stop.

To confirm the correctness of the possible replacement of internal combustion engines by an electric motor in the propeller drive, we carry out the following calculation: we determine the engine torque for the known propulsion system of the TU-114 aircraft (take-off weight of 170 tons) and the engine of the MI-26 helicopter (take-off weight of 56 tons). According to these torques, we determine an electric motor with a similar torque: 1) as an analogue of a power marching propulsion system, we take the propulsion system of a TU-114 aircraft with a four-blade propeller with a diameter of 5.6 m, with a flight speed of 736 rpm (vertical plane of rotation) engine of 15,000 hp, 8300 rpm. 2) As a power propulsion system for vertical take-off of an aircraft, we take the propulsion system from a MI 26 helicopter with an eight-blade horizontal rotor rotor with a diameter of 28 m, engine power of 8500 kW, 8300 rpm. The determination of the torque is made from the power formula for uniform rotational motion (see the appendix).

Calculations and formulas.

1) We determine the torque on the axis of the TU114 engine according to the formula Mkr. = N: w (N is power, w is the angular speed, n is the number of engine revolutions in min), while w = (P × p): 30, where p = 8300 rpm, then w = (3.14 × 8300): 30 = 868.7 rpm. N = 15000 l.c., Mcp. = (15000 × 75 kg m / s): 868.7 rpm = 1295 kg m. The front engine screw takes 54.4% of the power N, the rear 45.6% of the power N, then for the front screw M = 8160 hp, the rear screw N = 6840 hp, then for the front screw Mkr. = (8160 × 75 kg · m / s): 868.7 r / s = 704.5 kg · m, for Micr. = (6840 × 75 kg · m / s): 868.7 r / s = 590 kg · m. We approximately determine the gear ratio of the gearbox from the engine to the TU-114 screw, 8300 rpm: 736 rpm = 11, MKR. at the output from the gearbox to the screw, we obtain so by multiplying Mkr. dv. gear ratio: 1295 kg · m × 11 = 14603 kg · m, then for the front screw MKR = 704.5 × 11 = 7749.5 kg · m, for the rear screw MKR = 590 kg · m × 11 = 6490 kg Using the selection method according to the catalog, we select a direct current motor DA30 4-400, U = 6000 V, N = 250 kW, n = 600 rpm, MKR = 6000 kg · m, which separately ensures rotation of each screw through a planetary gearbox. It is also possible to use an electric motor Мкр. = 10,000 kg · m with high torque, but these electric motors are not suitable for revolutions.

2) We determine the torque of the drive motor for the eight-blade propeller gearbox with a diameter of 28 m of the MI26 helicopter, according to the formula Mcp. = N: w, with w = (P × p): 30, where p = 8300 rpm, w = (3 , 14 × 8300): 30 = 868.7 hp, N = 11400 hp, then MKR = (11400 × 75 kg · m): 868.7 r / s = 984 kg · m. Gear ratio from email. motor to propeller with gearbox is 62.5. Then, at the outlet from the gearbox, Mkr. = 984 kgm × 62.5 = 61537.5 kgm. To replace the MI-26 drive motor with email. the engine is applicable electric motor DA30 4-400, U = 6000 V, N = 250 kW, n = 500 rpm, MKR. = 10000 kg · m, the gear ratio between the moments is 61537.5: 10000 = 6, we define MKR. at the exit from the gearbox, MKR. = 0.85 × 10000 kg · m × 7.1 = 60350 kg · m, the number of revolutions of the screw from this el. engine 500 rpm: 7.1 = 70 rpm. In terms of email. the engine does not match, but if its supply voltage is increased to 10,000 V, then its characteristics will be close to those required. To ensure only autorotation mode and MKR. suitable motor N = 500 kW, n = 1800 rpm, U = 660 V, MKR. = 4807 nm Through a gearbox with a gear ratio of 12.5, we determine the revolutions on the screw axis 1800 rpm: 12.5 = 144 rpm and MKR = 0.85 × 4807 × 12.5 = 51074 n.m = 5107 kg m

The implementation of the invention.

As electric motors for mid-flight propellers and vertical take-off propellers, it is more expedient to use valve reactive electric motors of the required power with a speed of up to 10,000 rpm (abroad they are produced with a power of 250 kW). Power supply of electric motors is provided from a gas turbine power plant GTU-4 or GTU-6 through voltage converters, if necessary. In this case, fuel is required only for the D-30 drive motor. This ensures the economic operation of aircraft of this type. It is also possible to modernize domestic electric motors using power semiconductors to turn them into valve jet electric motors. The design of the aircraft allows you to place liquefied gas in pipes of composite materials with a volume of up to 15,000 m ³ . For storage of liquefied gas, it is possible to use gas tankers used on Russian railways. Hydrogen obtained from water by electrolysis must also be used as fuel; it is possible to replenish its reserves directly into the sea. For this, hydrogen production facilities must be installed in the aircraft hull. Their type and the required amount can be determined during the design of the aircraft. After take-off, the horizontal rotation screws are switched to autorotation (free rotation from the incoming air flow) and from them the rotation of the generator rotor, made according to the type of jet reactive, which will produce electricity for the main propeller motors and in this case there will be no fuel consumption by the electric power drive installation. The autorotation mode of the propellers will provide a safe flight for landing in case of disabling the propeller propeller drives in an emergency.

Blueprints

FIG. 1 on three sheets (left, middle, right) top view of the aircraft with the arrangement of vertical and horizontal propeller propellers. 2) FIG. 2 on three sheets is a side view of an aircraft with propulsion system propellers. In FIG. 1, 2 it is indicated: an aircraft with dimensions 96 × 40 × 20 m, draft 1.5 m, deck area 3240 m ² , displacement 1170 tons, weight 80 tons, 1 - hull, 2 - front wing, 3 - rear wing, 4 - air control wheels, 5 - marching engines with vertical screws, 6 - engines with horizontal screws (vertical take-off), 7 - autorotation screws.

Appendix (reference materials): 1) Calculation of power for rotational motion according to the reference book “Technical Mechanics” NN Pashkova, 2) kinematic diagram of a single-stage gear reducer, 3) extract from the catalog of electric motors, 4) extract from the catalog of electric power plants.

Claims (1)

Electromechanical power plant of an aircraft, consisting of a group of propellers with each rotationally driven through a gearbox from electric motors powered by a large-capacity electric power plant with one internal combustion engine, characterized in that it is capable of charging batteries and powering the propeller motors from marching generators working from rotating in the autorotation mode of horizontal propellers with an oncoming high-speed air stream.

Images