Propulsion system for a single-engine helicopter

Patent metadata

Field	Value
Publication number	US-2019352001-A1
Application number	US-201816484428-A
Country	US
Kind code	A1
Filing date	Feb 5, 2018
Priority date	Feb 15, 2017
Publication date	Nov 21, 2019
Grant date	—

Abstract

Propulsion system (8) for a single-engine helicopter (1), comprising: a main engine (9) connected to a front drive shaft (5) and a rear drive shaft (7), respectively, suitable for driving a main gearbox (4) referred to as MGB (4) and a tail gearbox (6) referred to as TGB (6); ⋅ an assistance device (10) attached to the main engine (9); characterised in that said propulsion system (8) is designed in order that the assistance device (10) can mechanically drive the TGB and MGB (6, 4) by introducing power to the rear drive shaft (7).

First claim

1 . Propulsion system for a single-engine helicopter comprising:
a main engine connected to a front drive shaft and a rear drive shaft, respectively able to drive a main gearbox referred to as MGB ( 4 ) and a rear gearbox referred to as RGB; an assistance device secured to the main engine; wherein said propulsion system is configured so that the assistance device can mechanically drive said ROB and MGB by introducing power on said rear drive shaft.

2 . System according to claim 1 , wherein said assistance device comprises a propulsion device comprising pyrotechnical and/or electro-technical and/or electric and/or hydraulic and/or pneumatic means.

3 . System according to claim 1 , wherein the propulsion device is mechanically connected to the rear drive shaft by means of a gearbox.

4 . System according to claim 3 , wherein said gearbox comprises a first reduction gear and/or a first freewheel configured to transmit the power generated by said propulsion device to said rear drive shaft.

5 . System according to claim 3 , wherein said gearbox comprises means to measure the rotational speed of said propulsion device and/or of said rear drive shaft.

6 . System according to claim 3 , wherein said gearbox comprises the following interfaces:
a first interface coupled to the propulsion device; a second interface coupled to a first portion of said rear drive shaft, said first portion being mechanically connected to the main engine; a third interface coupled to a second portion of said rear drive shaft, said second portion being mechanically connected to said RGB.

7 . System according to claim 6 , wherein said first portion of said rear drive shaft is connected to a second freewheel connected to a second reduction gear, said second reduction gear being mechanically connected to said main engine.

8 . System according to claim 1 , wherein the main engine is an internal combustion engine, and preferably a turboshaft engine.

9 . Helicopter comprising a propulsion system according to claim 1 .

Assignees

• Safran Helicopter Engines

Inventors

• Thiriet Romain
• Serghine Camel
• Puerto Alphonse
• Sarrat Christian

Classifications

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F05D2270/09

  to cope with emergencies · CPC title

• F05D2220/329

  in helicopters · CPC title

• B64C27/12 Primary

  Rotor drives · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title