Continuous flow fuel system

Patent metadata

Field	Value
Publication number	US-12460819-B2
Application number	US-202418598529-A
Country	US
Kind code	B2
Filing date	Mar 7, 2024
Priority date	Mar 7, 2024
Publication date	Nov 4, 2025
Grant date	Nov 4, 2025

Abstract

A fuel system for a gas turbine engine includes a manifold assembly with an assembly inlet, an assembly outlet, and a plurality of fuel injectors. The manifold assembly also includes at least one fuel manifold fluidically connecting each fuel injector of the plurality of fuel injectors to the assembly inlet and to the assembly outlet. A fuel return line is fluidically connected to the assembly outlet. A fuel circulator pump includes a pump outlet fluidically connected to the assembly inlet.

First claim

The invention claimed is:

1 . A fuel system for a gas turbine engine comprises:
a manifold assembly comprising: an assembly inlet; an assembly outlet; a plurality of fuel injectors, each of the plurality of fuel injectors further comprising:
a strut extending radially inward from an outer end toward a center axis of the gas turbine engine;
a nozzle head connected to the strut opposite the outer end of the strut;
a first valve seat in the strut and closer to the nozzle head than to the outer end of the strut, or the first valve seat is in the nozzle head;
a second valve seat in the strut and closer to the nozzle head than to the outer end of the strut, or the second valve seat is in the nozzle head;
a return passage extending from the outer end of the strut to the first valve seat;
a supply passage extending from the outer end of the strut to the second valve seat;
a nozzle exit formed on the nozzle head and fluidically connected to the second valve seat; and
a valve head between the first valve seat and the second valve seat,
wherein in a first position the valve head is against the first valve seat and fluidically opens the nozzle exit to the supply passage and fluidically closing the return passage to both the nozzle exit and the supply passage when the gas turbine engine is on, and
wherein in a second position the valve head is against the second valve seat and fluidically closes the nozzle exit to both the supply passage and the return passage and fluidically opens the return passage to the supply passage when the gas turbine engine is off; and
at least one fuel manifold fluidically connecting each fuel injector of the plurality of fuel injectors to the assembly inlet and to the assembly outlet; a fuel return line fluidically connected to the assembly outlet; and a fuel circulator pump comprising:
a pump outlet fluidically connected to the assembly inlet.

2 . The fuel system of claim 1 , wherein the fuel circulator pump further comprises:
a pump inlet, wherein the pump inlet is fluidically connected to the fuel return line.

3 . The fuel system of claim 2 , further comprising:
a fuel tank; a main fuel pump comprising:
a main pump inlet fluidically connected to the fuel tank; and
a main pump outlet fluidically connected to the assembly inlet; and
a check valve fluidically connecting the main pump outlet to the assembly inlet.

4 . The fuel system of claim 3 , wherein the fuel circulator pump comprises:
a shut off valve configured to open and close the pump inlet and/or the pump outlet of the fuel circulator pump.

5 . The fuel system of claim 1 , further comprising:
an electrical actuator; and a drive shaft extending through the strut to connect the valve head to the electrical actuator.

6 . The fuel system of claim 1 , wherein the fuel circulator pump is mechanically coupled to a core turning motor of a gas turbine engine.

7 . The fuel system of claim 1 , wherein the fuel circulator pump is an electrically powered fuel pump.

8 . The fuel system of claim 1 , further comprising:
a fuel tank; a main fuel pump comprising:
a main pump inlet fluidically connected to the fuel tank; and
a main pump outlet fluidically connected to the assembly inlet; and
a check valve fluidically connecting the main pump outlet to the assembly inlet, and wherein the fuel return line is connected to the fuel tank.

9 . The fuel system of claim 8 , wherein the fuel circulator pump further comprises:
a pump inlet, wherein the pump inlet is fluidically connected to the fuel tank.

10 . A fuel system for a gas turbine engine comprises:
a fuel tank; a first manifold assembly further comprising:
a first assembly inlet;
a first assembly outlet;
a plurality of fuel injectors; and
a first fuel manifold fluidically connecting each fuel injector of the plurality of fuel injectors to the first assembly inlet and to the first assembly outlet;
a fuel return line fluidically connected to the first assembly outlet; a fuel circulator pump comprising:
a circulator pump inlet;
a circulator pump outlet fluidically connected to the first assembly inlet;
a second manifold assembly comprising:
a second assembly inlet;
the plurality of fuel injectors; and
a-second manifold fluidically connecting each fuel injector of the plurality of fuel injectors to the second assembly inlet; and
a main fuel pump comprising:
a main pump inlet fluidically connected to the fuel tank; and
a main pump outlet fluidically connected to the second assembly inlet.

11 . The fuel system of claim 10 , wherein each fuel injector of the plurality of fuel injectors comprises:
a strut; a nozzle head; a first passage in the strut that is fluidically connected to the first fuel manifold and fluidically isolated from an exit of the nozzle head; and a second passage in the strut fluidically connecting the second manifold to the exit of the nozzle head.

12 . A gas turbine engine, the gas turbine engine comprising:
a low-speed spool; a high-speed spool; a manifold assembly comprising:
an assembly inlet;
an assembly outlet;
a plurality of fuel injectors;
at least one fuel manifold fluidically connecting each fuel injector of the plurality of fuel injectors to the assembly inlet and to the assembly outlet;
a main fuel pump fluidically connected to the assembly inlet; a fuel circulator pump comprising:
a pump outlet fluidically connected to the assembly inlet;
a pump inlet fluidically connected to the assembly outlet;
a core turning motor mechanically coupled to the fuel circulator pump; and a coupling, wherein the coupling mechanically connects the core turning motor to the low-speed spool.

13 . The fuel system of claim 12 , wherein the coupling mechanically disconnects the core turning motor to the low-speed spool and the coupling mechanically connects the core turning motor to the high-speed spool.

Assignees

• Rtx Corp

Inventors

• Breault Andrew E
• Sobanski Jon Erik
• Morton Jeffrey T

Classifications

• F02C7/22

  Fuel supply systems · CPC title

• F02C7/16 Primary

  characterised by cooling medium · CPC title

• F02C7/12

  Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) · CPC title

• F05D2260/232

  characterized by the cooling medium · CPC title

• F05D2260/205

  Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes · CPC title