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Transmission assembly for an aircraft and a helicopter

By designing a transmission component with two degrees of freedom and using a controllable electric regulator machine and an electric balancing machine, the problem of inappropriate speed of the gas turbine engine in traditional helicopters is solved, saving fuel consumption and improving performance.

Active Publication Date: 2017-02-22
SAFRAN HELICOPTER ENGINES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this solution is limited in that it cannot vary the rotational speed outside a narrow range that does not affect flight safety

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0046] In order to make the present invention more specific, various implementations of the helicopter transmission assembly will be described in detail below with reference to the accompanying drawings. It is understood that the present invention is not limited to these embodiments.

[0047] figure 1 , figure 2 , image 3 A first embodiment of a helicopter is shown with rotors 90 driven in rotation by a gas turbine engine 10 via a main gearbox (MGB) 60 . On a helicopter, the MGB60 is a mechanical device used to transmit power from the engine 10 to the rotor 90 after deceleration; the MGB also provides an angular transmission between the drive shaft and the rotor shaft, and can also be used to drive various Accessories, such as pumps or alternators.

[0048] The rotational speed Nr of the rotor 90 is imposed according to the requirements of the flight: this rotational speed Nr is then also applied to the rotational speed Nt of the turbine engine 10 through the transmissio...

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PUM

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Abstract

A transmission assembly for an aircraft and a helicopter comprising such an assembly for independently adjusting the speed of rotation of an engine and a torque receiver. According to the invention, the assembly comprises a first input shaft (10a), configured to receive mechanical torque from a first engine (10), an output shaft (60a), configured to transmit mechanical torque to a torque receiver (60), a first transmission member (20) having at least two degrees of mobility comprising first, second and third movable parts, a first regulating reversible electric machine (30), and a first balancing reversible electric machine (40), in which the input shaft (10a) is coupled to the first movable part, the output shaft (60a) is coupled to the second movable part, the first regulating electric machine (30) is coupled to the third movable part, and the first balancing electric machine (40) is coupled in series to the input shaft or the output shaft (60a).

Description

technical field [0001] This description relates to the transmission assembly of an aircraft and also to a helicopter incorporating such an assembly. [0002] This transmission assembly can be used to control the speed of the engine and the speed of the torque receiver independently to optimize each speed. Such a device is particularly useful in the field of aviation, more particularly in the field of helicopters. Background technique [0003] On conventional helicopters, the aircraft's gas turbine engine is usually connected to means for extracting mechanical power, such as a main gearbox (MGB), an alternator, or even a load compressor. In this case, the rotational speed of the gas turbine engine is imposed by the equipment to which it is connected: this is problematic because the imposed rotational speed is not necessarily suitable for energy optimization of the entire system (gas turbine engine or torque receiver) . [0004] In particular, in the case of an auxiliary po...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16H3/72B64C27/12
CPCB64C27/12F16H3/724B60K6/08F16H3/72B64C27/14F16H3/725
Owner SAFRAN HELICOPTER ENGINES