Systems and methods for purging a fuel manifold of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11525410-B2
Application number	US-202017061856-A
Country	US
Kind code	B2
Filing date	Oct 2, 2020
Priority date	Oct 10, 2019
Publication date	Dec 13, 2022
Grant date	Dec 13, 2022

Abstract

Fuel systems of gas turbine engines of aircraft, and associated methods are provided. The fuel systems and methods can permit reverse purging of one or more fuel manifolds of a gas turbine engine to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds fluidly connectable to a combustor of the gas turbine engine. A valve is operatively disposed between the second fuel manifold and a fuel supply line for controlling fuel supply to the second fuel manifold. A reservoir includes a movable piston disposed therein and dividing the reservoir into a first chamber and a second chamber. The first chamber is fluidly connectable to the fuel supply line or to a fuel purge line via the valve. The second chamber is in fluid communication with the second fuel manifold to receive residual fuel from the second fuel manifold.

First claim

The invention claimed is:

1. A method of operating a gas turbine engine of an aircraft, the method comprising:
receiving fuel;
supplying a first portion of the fuel to a combustor of the gas turbine engine via a first valve and a first fuel manifold;
supplying a second portion of the fuel to the combustor of the gas turbine engine via a second valve and a second fuel manifold;
supplying a third portion of the fuel to a first reservoir chamber of a reservoir via the second valve, the reservoir including a movable piston dividing the reservoir into the first reservoir chamber and a second reservoir chamber;
stopping fuel supply to the combustor via the second valve and the second fuel manifold, the second fuel manifold containing residual fuel; and
after stopping fuel supply to the combustor via the second fuel manifold:
receiving the residual fuel purged from the second fuel manifold into the second reservoir chamber; and
using the piston to drive the third portion of the fuel out of the first reservoir chamber and toward an outlet via the second valve.

2. The method as defined in claim 1 , comprising driving the piston to move and cause expansion of the second reservoir chamber to drive the residual fuel in the second fuel manifold upstream and purge the second fuel manifold of the residual fuel.

3. The method as defined in claim 1 , wherein receiving the residual fuel from the second fuel manifold into the second reservoir chamber occurs while supplying the first portion of the fuel to the combustor via the first valve and the first fuel manifold.

4. The method as defined in claim 1 , wherein:
the gas turbine engine is a first engine of a multi-engine power plant of the aircraft;
the multi-engine power plant includes a second engine; and
receiving the residual fuel from the second fuel manifold into the second reservoir chamber is performed during flight of the aircraft and when the second engine is operating.

5. The method as defined in claim 1 , wherein the residual fuel in the second fuel manifold is second residual fuel and the method comprises:
stopping fuel supply to the combustor via the first valve and the first fuel manifold, the first fuel manifold containing first residual fuel; and
when fuel supply to the combustor via the first and the second fuel manifolds is stopped, using pressurized gas inside the combustor to drive the first residual fuel in the first fuel manifold upstream and purge the first fuel manifold of the first residual fuel.

6. The method as defined in claim 5 , comprising:
combining the first residual fuel and the third portion of the fuel driven out of the first chamber of the reservoir together; and
driving the first residual fuel and the third portion of the fuel driven out of the first chamber of the reservoir toward the outlet.

7. The method as defined in claim 5 , comprising:
using the third portion of the fuel to drive a Venturi pump; and
using the Venturi pump to drive the first residual fuel in the first fuel manifold upstream and purge the first fuel manifold of the first residual fuel.

8. A method of operating a gas turbine engine of an aircraft, the method comprising:
receiving fuel;
supplying a first portion of the fuel to a combustor of the gas turbine engine via a first fuel manifold;
supplying a second portion of the fuel to the combustor of the gas turbine engine via a second fuel manifold;
supplying a third portion of the fuel to a reservoir;
stopping fuel supply to the combustor via the first and the second fuel manifolds, the first fuel manifold containing first residual fuel and the second fuel manifold containing second residual fuel; and
after stopping fuel supply to the combustor via the first and the second fuel manifolds:
receiving the second residual fuel purged from the second fuel manifold into the reservoir;
driving the third portion of the fuel out of the reservoir and using the third portion of the fuel to drive a Venturi pump; and
using the Venturi pump to drive the first residual fuel in the first fuel manifold upstream and purge the first fuel manifold of the first residual fuel.

9. The method as defined in claim 8 , wherein:
the reservoir includes a movable piston dividing the reservoir into a first reservoir chamber and a second reservoir chamber;
the third portion of the fuel is received into the first reservoir chamber; and
the second residual fuel from the second fuel manifold is received into the second reservoir chamber.

10. The method as defined in claim 9 , comprising causing the piston to move and cause expansion of the first reservoir chamber when the third portion of the fuel is received into the first reservoir chamber.

11. The method as defined in claim 9 , comprising driving the piston to move and cause expansion of the second reservoir chamber to drive the second residual fuel in the second fuel manifold upstream and purge the second fuel manifold of the second residual fuel.

12. The method as defined in claim 11 , comprising driving the piston to move and cause contraction of the first reservoir chamber to drive the third portion of the fuel out of the first reservoir chamber.

13. The method as defined in claim 8 , comprising:
storing the second residual fuel into the reservoir after fuel supply to the combustor via the second fuel manifold is stopped;
resuming fuel supply to the combustor via the second fuel manifold; and
when the fuel supply to the combustor via the second fuel manifold is resumed, driving the second residual fuel out of the reservoir and into the second fuel manifold.

14. The method as defined in claim 8 , comprising using a pressurized gas inside the combustor to drive the second residual fuel in the second fuel manifold upstream and into the reservoir.

15. The method as defined in claim 14 , comprising using the pressurized gas inside the combustor to drive the first residual fuel in the first fuel manifold upstream and purge the first fuel manifold.

Assignees

• Pratt & Whitney Canada

Inventors

• Jarvo James Robert
• Saintignan Cédric
• Mokhtar Hytham

Classifications

• F02C9/42

  specially adapted for the control of two or more plants simultaneously · CPC title

• F05D2260/602

  Drainage · CPC title

• F02C9/38 Primary

  characterised by throttling and returning of fuel to sump · CPC title

• F01D21/00

  Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for · CPC title

• F02C7/222

  Fuel flow conduits, e.g. manifolds · CPC title