IP Library Granted Patent US 7,895,819
Granted Patent B2
US 7,895,819 · App. 12/181,567 · Granted Mar 1, 2011

Assistance and emergency backup for the electrical drive of a fuel pump in a turbine engine

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Quick Facts
Patent No.
US 7,895,819
App. No.
12/181,567
Granted
Mar 1, 2011
Kind
B2
Abstract

A system for driving a fuel pump in a turbine engine is disclosed. The system includes an electric motor and a fluid flow assistance unit controlled by a control valve. In the system, the control valve is a regulator valve the opening of which is controlled as a function of information representative of the speed of the pump, and/or the speed of the turbine engine, and/or the flow rate of fuel delivered to the turbine engine. As a result, operating safety of the turbine engine can be increased in the event of the electric motor failing or of its electricity generator failing, and the weight/size/cost ratios of the drive system are improved.

Claims (14)

1. A system for driving a fuel pump in a turbine engine, said system comprising:

an electric motor;

an electronic control unit; and

fluid flow assistance means controlled by a control valve, said fluid flow assistance means including additional motor means driven by a flow of fluid and suitable for at least one of assisting or replacing the electric motor,

wherein the control valve is a regulator valve, with a progressively variable opening thereof being controlled by the electronic control unit as a function of information representative of at least one of a speed of rotation of the pump, a speed of rotation of a shaft of the turbine engine, or a flow rate of fuel delivered to the turbine engine.

2. The drive system according to claim 1 , wherein the assistance means comprise an air turbine.

3. The drive system according to claim 2 , wherein the air turbine can be operated together with the electric motor for driving the fuel pump.

4. The drive system according to claim 2 , wherein the air turbine is suitable for driving the fuel pump in the event of an electricity power supply failing or in the event of said electric motor failing.

5. The drive system according to claim 2 , wherein said regulator valve is situated on the fluid feed to the air turbine.

6. The drive system according to claim 1 , wherein a maximum power of the electric motor is less than a maximum power that can be drawn by the pump.

7. The drive system according to claim 6 , wherein the maximum power of the electric motor is less than 50% of the maximum power that can be drawn by the pump.

8. A turbine engine including a drive system according to claim 1 .

9. The drive system according to claim 1 , wherein the regulator valve is a two-port valve.

10. The drive system according to claim 1 , wherein the electronic control unit receives the flow rate of fuel delivered to the turbine engine from a flow meter.

Assignments (2)
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 →