Energy efficient pump system

Patent metadata

Field	Value
Publication number	US-9657643-B2
Application number	US-201414183966-A
Country	US
Kind code	B2
Filing date	Feb 19, 2014
Priority date	Oct 16, 2013
Publication date	May 23, 2017
Grant date	May 23, 2017

Abstract

A fuel system for a gas turbine engine, which includes a combustor section and an actuator, includes a fuel source, a combustor system, and an actuation system. The combustor system includes a combustor pump that is fluidly connected to the fuel source and to the combustor section, with the combustor pump being mechanically connected to and powered by an electric motor. The actuation system includes an actuator pump that is fluidly connected to the fuel source and to the actuator, with the actuator pump being mechanically connected to and powered by a gearbox or an electric motor.

First claim

The invention claimed is:

1. A fuel system for a gas turbine engine that includes a combustor section and an actuator, the fuel system comprising:
a fuel source;
a combustor system including a combustor pump that is fluidly connected to the fuel source and to the combustor section, the combustor pump being mechanically connected to and powered by a first electric motor;
an actuation system including an actuation pump that is fluidly connected to the fuel source and to the actuator, the actuation pump being mechanically connected to and powered by a first force source;
a fail selector that is fluidly connected to the combustor pump, the actuator pump, the combustor section, and the actuator, the fail selector having three settings comprising:
a first setting that allows no flow through the fail selector;
a second setting that allows flow from the combustor pump to both the combustor section and the actuator through the fail selector; and
a third setting that allows flow from the actuator pump to both the combustor section and the actuator through the fail selector;

an afterburner system including an afterburner pump that is fluidly connected to the fuel source and to an afterburner, the afterburner pump being mechanically connected to and powered by a turbomachine or a third electric motor; and
a pump selector that is fluidly connected to the afterburner system and is fluidly connected between the fuel source and the combustor system, the pump selector having two settings comprising:
a first setting that allows flow from the fuel source to the combustor section; and
a second setting that allows flow from the afterburner system to the combustor system.

2. The fuel system of claim 1 , wherein the first force source is a gearbox.

3. The fuel system of claim 1 , wherein the first force source is a second electric motor.

4. The fuel system of claim 1 , wherein the second force source is a turbomachine.

5. The fuel system of claim 1 , wherein the second force source is a third electric motor.

6. The gas turbine engine of claim 5 , and further comprising:
a boost pump fluidly connected between the fuel source and the combustor and actuator pumps;
wherein the boost pump is mechanically connected to and powered by the first force source.

7. The fuel system of claim 1 , and further comprising:
a boost pump fluidly connected between the fuel source and the combustor and actuator pumps.

8. A gas turbine engine including the fuel system of claim 1 , the gas turbine engine further comprising:
a compressor upstream of the combustor section;
a turbine downstream of the combustor section; and
a shaft that couples the turbine to the compressor.

9. The gas turbine engine of claim 8 , wherein the first force source is a gearbox that is connected to the shaft.

10. A method of operating a fuel system for a gas turbine engine that includes a combustor section, an afterburner, and an actuator, the method comprising:
powering a combustor pump with an electric motor;
flowing fuel from a fuel source to the combustor section using the combustor pump;
powering an actuator pump with a gearbox or an electric motor;
flowing fuel from the fuel source to the actuator using the actuator pump;
powering an afterburner pump with a turbomachine;
flowing fuel from the fuel source to the afterburner using the afterburner pump;
flowing fuel from the fuel source to the combustor pump using the afterburner pump; and
flowing fuel from the fuel source to both the combustor section and the actuator using the combustor pump after a failure of the actuator pump.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Veilleux Jr Leo J

Classifications

• F02C7/236 Primary

  Fuel delivery systems comprising two or more pumps · CPC title