System and method for purging a fuel manifold of a gas turbine engine through a flow divider valve

Patent metadata

Field	Value
Publication number	US-11732653-B2
Application number	US-202217989247-A
Country	US
Kind code	B2
Filing date	Nov 17, 2022
Priority date	May 15, 2019
Publication date	Aug 22, 2023
Grant date	Aug 22, 2023

Abstract

Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.

First claim

What is claimed is:

1. A fuel system of a gas turbine engine, the fuel system comprising:
a pressurized gas source;
a first fuel manifold fluidly connectable to a combustor of the gas turbine engine;
a second fuel manifold fluidly connectable to the combustor; and
a flow divider valve actuatable between a first configuration and a second configuration, wherein:
in the first configuration, the flow divider valve is configured to supply fuel to the first and second fuel manifolds; and
in the second configuration, the flow divider valve is configured to:
supply fuel to the first fuel manifold,
stop supplying fuel to the second fuel manifold, and
permit pressurized gas to be supplied from the pressurized gas source to the second fuel manifold to flush fuel in the second fuel manifold into the combustor.

2. The fuel system of claim 1 , comprising a reservoir for storing the pressurized gas.

3. The fuel system of claim 2 , wherein the pressurized gas source is a compressor of the gas turbine engine and the reservoir is in fluid communication with the compressor of the gas turbine engine to receive pressurized air from the compressor.

4. The fuel system of claim 1 , comprising a regulator for regulating the pressurized gas supplied to the second fuel manifold.

5. The fuel system of claim 1 , wherein the flow divider valve is a spool valve.

6. The fuel system of claim 1 , wherein the flow divider valve includes:
a fuel inlet;
a first fuel outlet;
a second fuel outlet;
a first valve member operatively disposed between the fuel inlet and the first fuel outlet to establish fluid communication between the fuel inlet and the first fuel outlet; and
a second valve member operatively disposed between the fuel inlet and the second fuel outlet to establish fluid communication between the fuel inlet and the second fuel outlet.

7. The fuel system of claim 6 , wherein the flow divider valve includes a gas inlet and a third valve member operatively disposed between the gas inlet and the second fuel outlet to establish fluid communication between the gas inlet and the second fuel outlet.

8. The fuel system of claim 7 , wherein the flow divider valve includes a fourth valve member operatively disposed between the gas inlet and the first fuel outlet to establish fluid communication between the gas inlet and the first fuel outlet.

Assignees

• Pratt & Whitney Canada

Inventors

• Jarvo James Robert
• Saintignan Cédric
• Cirtwill Joseph Daniel Maxim
• Mccaldon Kian
• Tremblay Marc-Andre
• Waddleton David

Classifications

• F02C7/30 Primary

  Preventing corrosion {or unwanted deposits} in gas-swept spaces · CPC title

• F02C6/00

  Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use · CPC title

• F02C6/16

  for storing compressed air · CPC title

• F02C7/222

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

• F02C7/228

  Dividing fuel between various burners · CPC title