Staged blade injector

Patent metadata

Field	Value
Publication number	US-2025027649-A1
Application number	US-202418774437-A
Country	US
Kind code	A1
Filing date	Jul 16, 2024
Priority date	Jul 21, 2023
Publication date	Jan 23, 2025
Grant date	—

Abstract

A blade fuel injector for a gas turbine engine, including: a mixer, the mixer having a first set of openings located on opposite sides of the mixer and a second set of openings located below the first set of openings; and a blade injector, the blade injector having a plurality of atomizers, wherein some of the first set of openings align with the plurality of atomizers.

First claim

What is claimed is:

1 . A blade fuel injector for a gas turbine engine, comprising:
a mixer, the mixer having a first set of openings located on opposite sides of the mixer and a second set of openings located below the first set of openings; and a blade injector, the blade injector having a plurality of atomizers, wherein some of the first set of openings align with the plurality of atomizers.

2 . The blade fuel injector as in claim 1 , wherein the first set of openings is a pair of opposing elongated openings.

3 . The blade fuel injector as in claim 1 , wherein the blade injector is removably installed into the mixer.

4 . The blade fuel injector as in claim 1 , wherein the blade injector and mixer are formed as a single unitary unit wherein the blade injector is not removable from the mixer.

5 . The blade fuel injector as in claim 1 , wherein the second set of openings are located on opposite sides of the mixer.

6 . The blade fuel injector as in claim 5 , wherein the second set of openings are of varying sizes.

7 . The blade fuel injector as in claim 6 , wherein some of the second set of openings are elliptical in shape.

8 . The blade fuel injector as in claim 7 , wherein the first set of openings is a pair of opposing elongated openings.

9 . The blade fuel injector as in claim 5 , wherein the second set of openings are of varying sizes and are teardrop in shape or elliptical in shape.

10 . The blade fuel injector as in claim 9 , wherein the second set of openings that are teardrop in shape are located in an alternating pattern with respect to the second set of openings that are elliptical in shape.

11 . A combustor for a gas turbine engine, comprising:
a plurality of pilot fuel injectors; a plurality of blade fuel injectors, each blade fuel injector comprising:
a mixer, the mixer having a first set of openings located on opposite sides of the mixer and a second set of openings located below the first set of openings; and
a blade injector, the blade injector having a plurality of atomizers, wherein some of the first set of openings align with the plurality of atomizers.

12 . The combustor as in claim 11 , wherein the plurality of pilot fuel injectors inject fuel in a combustion chamber of the combustor in a first direction and the plurality of blade fuel injectors inject fuel into the combustion chamber is a second direction which is different from the first direction.

13 . The combustor as in claim 12 , wherein the wherein the first direction is generally or substantially aligned with an axis of the gas turbine engine and the second direction is substantially orthogonal or perpendicular to the first direction.

14 . The combustor as in claim 11 , wherein the combustor is an annular combustor.

15 . The combustor as in claim 11 , wherein the plurality of blade fuel injectors are located at a 45 degree angle with respect to a forward end of the combustor.

16 . The combustor as in claim 12 , wherein the mixer is located in an annular outer plenum and extends from an outer case to an outer wall of the combustion chamber and the mixer provides a path for air and fuel to the combustion chamber and the mixer provides a path from the annular outer plenum to the combustion chamber.

17 . The combustor as in claim 11 , wherein the first set of openings is a pair of opposing elongated openings.

18 . The combustor as in claim 11 , wherein the blade injector is removably installed into the mixer.

19 . The combustor as in claim 11 , wherein the blade injector and mixer are formed as a single unitary unit wherein the blade injector is not removable from the mixer.

20 . The combustor as in claim 11 , wherein the second set of openings are located on opposite sides of the mixer.

Assignees

• Rtx Corp

Inventors

• Boardman Gregory

Classifications

• F23R3/343

  Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion (ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00) · CPC title

• F23R3/346

  for staged combustion · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title