Electronic fuel control for gas turbine engines

Patent metadata

Field	Value
Publication number	US-11053862-B2
Application number	US-201715714597-A
Country	US
Kind code	B2
Filing date	Sep 25, 2017
Priority date	Sep 25, 2017
Publication date	Jul 6, 2021
Grant date	Jul 6, 2021

Abstract

A fuel injector for a gas turbine engine includes a feed arm defining a conduit extending between an inlet end and an outlet end and a plunger. The plunger is disposed within the conduit and is movable between a plunger first position and a plunger second position. A flow area defined between the plunger and the feed arm is smaller in the plunger first position than in the plunger second position to bias fuel flow through the fuel injector. Fuel systems, gas turbine engines, and methods of controlling fuel flow in gas turbine engine fuel systems are also described.

First claim

What is claimed is:

1. A fuel injector for a gas turbine engine, comprising:
a feed arm;
a conduit extending between an inlet end and an outlet end; and
a plunger disposed within the conduit and movable between a plunger first position and a plunger second position,
wherein the plunger and the conduit define between one another a flow area that is smaller in the plunger second position than in the plunger first position, and wherein the plunger has a blunt segment, a tapered segment, and a constant diameter segment coupling the blunt segment to the tapered segment, wherein the tapered segment is tapered from a wider end to a narrower end in a direction away from the blunt segment.

2. The fuel injector as recited in claim 1 , further comprising an electrical actuator operably connected to the plunger and arranged to move the plunger relative to the feed arm.

3. The fuel injector as recited in claim 2 , wherein the electrical actuator is appurtenant to the fuel injector.

4. The fuel injector as recited in claim 2 , wherein the electrical actuator is severable from the fuel injector.

5. The fuel injector as recited in claim 2 , further comprising a rotary drive coupling the electrical actuator to the plunger and arranged to rotate the plunger relative to the feed arm.

6. The fuel injector as recited in claim 2 , wherein the electrical actuator includes a solenoid, a rotary motor, or a stepper motor.

7. The fuel injector as recited in claim 1 , wherein the feed arm has female threads engagable with the plunger.

8. The fuel injector as recited in claim 7 , wherein the plunger has male threads engagable with the female threads of the feed arm.

9. The fuel injector as recited in claim 7 , wherein the conduit extends about the female threads.

10. The fuel injector as recited in claim 1 , wherein the conduit tapers between a large flow area and a small flow area, the small flow area arranged between the large flow area and the outlet end of the feed arm.

11. The fuel injector as recited in claim 1 , further comprising an electrical connector and an inlet port arranged on the inlet end of the feed arm, the inlet port being in fluid communication with the conduit.

12. The fuel injector as recited in claim 11 , further comprising a controller operably connected to plunger by the electrical connector, the controller arranged to rotate the plunger within the conduit relative to the feed arm.

13. The fuel injector as recited in claim 1 , further comprising a threaded annulus fixed within the feed arm and seating the plunger, the conduit extending about the threaded annulus, a plurality of support members spanning the conduit and coupling the threaded annulus to the feed arm.

14. A fuel system for a gas turbine engine, comprising:
the fuel injector as recited in claim 1 , wherein a flow area of the fuel injector is adjustable to allow fuel flow through the fuel injector to bias fuel flow through the fuel injector relative to fuel flow through a second fuel injector.

15. A gas turbine engine having a fuel system as recited in claim 1 , comprising:
a combustion section;
a turbine section in fluid communication with the combustion section, wherein a temperature range within the turbine section is smaller when fuel flow through the fuel injector is biased relative to fuel flow through a second fuel injector than when fuel flow through the fuel injector is matched to fuel flow through the second fuel injector; and
an electrical actuator operably connected to the plunger and arranged to rotate the plunger within the feed arm.

16. The gas turbine engine as recited in claim 15 , wherein neither the fuel injector nor the second fuel injector include an electrical actuator.

Assignees

• Delavan Inc

Inventors

• Ryon Jason A
• Prociw Lev Alexander

Classifications

• F23N1/005 Primary

  using electrical or electromechanical means (F23N1/04 - F23N1/10 take precedence) · CPC title

• F23D11/26

  with provision for varying the rate at which the fuel is sprayed · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R3/38

  comprising rotary fuel injection means · CPC title