IP Library Granted Patent US 7,351,174
Granted Patent B2
US 7,351,174 · App. 11/333,506 · Granted Apr 1, 2008

Twin turbo-shaft engine with accessory gearbox drive means

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Quick Facts
Patent No.
US 7,351,174
App. No.
11/333,506
Granted
Apr 1, 2008
Kind
B2
Abstract

The twin turbo-shaft engine according to the invention comprises a high pressure rotor and a low pressure rotor, at least one accessory gearbox driven by mechanical transmission means, main drive pinion means, on each rotor, driving power transmission means each associated with an input to a differential, the output of which drives a drive shaft of the accessory gearbox. It is characterised by the fact that the power transmission means extend in two different structural arms, the power transmission means of one of the rotors being connected to a power transfer box fulfilling two functions, firstly transmission of power to an input to the differential, and secondly modification of the transmission speed. The required space in each arm is thus reduced and the efficiency of the accessory gearbox is high.

Claims (6)

1. Twin turbo-shaft engine comprising a high pressure rotor and a low pressure rotor, at least one accessory gearbox driven by mechanical transmission means, main drive pinion means, on each rotor, driving power transmission means each associated with an input to a differential, the output of which drives a drive shaft of the accessory gearbox, characterised wherein the power transmission means extend in two different structural arms, the power transmission means of one of the rotors being connected to a power transfer box fulfilling two functions, firstly transmission of power to an input to the differential, and secondly modification of the transmission speed.

2. Turbo-shaft engine according to claim 1 , wherein modification of the transmission speed is a speed increase.

3. Turbo-shaft engine according to claim 1 , wherein the power transmission means connected to the power transmission box are the power transmission means associated with the low pressure rotor.

4. Turbo-shaft engine according to claim 1 , wherein inputs to the differential are concentric.

5. Turbo-shaft engine according to one of claims 3 and 4 , wherein the power transmission means associated with the high pressure rotor are connected to a bevel gearbox, for which the output shaft forms an input shaft to the differential, the power transmission means associated with the low pressure rotor are connected to a bevel gearbox for which the output shaft forms the input shaft to the power transfer box, for which the output shaft forms a second input shaft to the differential, extending concentrically around the other input shaft to the differential.

6. Turbo-shaft engine according to claim 1 , wherein the differential comprises a planet gear, a cage and satellites, the planet gear being connected to an input to the differential, the cage being connected to the other input to the differential, and the satellites being connected to the input shaft to the accessory gearbox.

Assignments (3)
CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Recorded Aug 24, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046939/0336 →
CHANGE OF NAME Recorded May 23, 2018
From: SNECMA
To: SAFRAN AIRCRAFT ENGINES
Reel/Frame 046479/0807 →
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Jan 18, 2006
From: BEUTIN, BRUNO; FERT, JEREMY
To: SNECMA
Reel/Frame 017487/0657 →