IP Library Granted Patent US 8,402,743
Granted Patent B2
US 8,402,743 · App. 12/489,830 · Granted Mar 26, 2013

Actuating of a thrust reverser in a turbomachine

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Quick Facts
Patent No.
US 8,402,743
App. No.
12/489,830
Granted
Mar 26, 2013
Kind
B2
Abstract

A turbomachine including at least one thrust reverser and a device for actuating the thrust reverser, which includes at least one hydraulic engine supplied with pressurized fluid by a fuel circuit of the turbomachine, is disclosed.

Claims (8)

1. A turbomachine comprising:

at least one thrust reverser; and

means for actuating the thrust reverser including at least one hydraulic engine and at least one mechanical cylinder, said at least one hydraulic engine being supplied with pressurized fluid by a fuel circuit of the turbomachine, and said at least one mechanical cylinder having a first end which is connected to the thrust reverser and a second end which is driven in rotation by an output shaft of said at least one hydraulic engine,

wherein said at least one hydraulic engine is connected to the fuel circuit by a control unit controlling the difference in pressure between an inlet and an output of fluid of said at least one hydraulic engine, the flow of fuel delivered to said at least one hydraulic engine, and the direction of passage of the fuel in said at least one hydraulic engine.

2. The turbomachine set forth in claim 1 , wherein said actuating means further includes means of braking and/or of blocking in rotation at least one of the output shaft of said at least one hydraulic engine or the first end of said at least one mechanical cylinder, the means of braking or of blocking being connected to at least one of manual or electrical means of control.

3. The turbomachine set forth in claim 1 , wherein the control unit is connected to an inlet and to an outlet of a high-pressure pump or of a dosing unit of the fuel circuit of the turbomachine.

4. The turbomachine set forth in claim 1 , wherein the control unit is connected to means of pressurizing and of generating fuel flow.

5. The turbomachine set forth in claim 1 , wherein said second end of said at least one mechanical cylinder is driven by said output shaft either directly or by an intermediate shaft.

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 Jun 24, 2009
From: NOUHAUD, CHRISTOPHE CLAUDE PHILIPPE
To: SNECMA
Reel/Frame 022870/0617 →