Fuel flexible fuel injector

Patent metadata

Field	Value
Publication number	US-8943833-B2
Application number	US-201213542985-A
Country	US
Kind code	B2
Filing date	Jul 6, 2012
Priority date	Jul 6, 2012
Publication date	Feb 3, 2015
Grant date	Feb 3, 2015

Abstract

A disclosed fuel injector provides mixing of fuel with airflow by surrounding a swirled fuel flow with first and second swirled airflows that ensures mixing prior to or upon entering the combustion chamber. Fuel tubes produce a central fuel flow along with a central airflow through a plurality of openings to generate the high velocity fuel/air mixture along the axis of the fuel injector in addition to the swirled fuel/air mixture.

First claim

The invention claimed is:

1. A combustor system for a gas turbine engine comprising:
a combustor defining a combustor chamber;
a fuel air mixer including a chamber disposed along an axis including a bulkhead at a forward end and an opening at an aft end;
a first annular passage disposed about the chamber, the first annular passage including a first plurality of vanes to generate a swirled first airflow and a first open end at the aft end of the chamber;
a second annular passage disposed about the first annular passage, the second annular passage including a second plurality of vanes to generate a swirled fuel flow and a second open end at the aft end of the chamber;
a third annular passage disposed about the second annular passage, the third annular passage including a third plurality of vanes to generate a swirled second airflow and a third open end at the aft end of the chamber;
a plurality of openings through the bulkhead of the chamber for communicating a central airflow to the chamber, wherein each of the openings are open to the chamber; and
a plurality of fuel tubes disposed about the axis and extending through the bulkhead into the chamber to communicate a second fuel flow to the chamber, wherein the plurality of openings are disposed between the plurality of fuel tubes.

2. The combustor system as recited in claim 1 , wherein the fuel tubes include an open end that is spaced apart from the bulkhead.

3. The combustor system as recited in claim 1 , including a duct extending from the aft end of the chamber to a combustion chamber.

4. The combustor system as recited in claim 1 , wherein an end of each of the plurality of fuel tubes extends into the chamber and is spaced apart from the opening at the aft end of the chamber.

5. A fuel injector for a gas turbine engine comprising:
a chamber disposed along an axis including a bulkhead at a forward end and an opening at an aft end spaced axially apart from the bulkhead;
a first annular passage disposed about the chamber, the first annular passage including a first plurality of vanes to generate a swirled first airflow and a first opening at the aft end of the chamber, wherein the first plurality of vanes are spaced apart from the aft end;
a second annular passage disposed about the first annular passage, the second annular passage including a second plurality of vanes to generate a swirled fuel flow and a second opening at the aft end of the chamber, wherein the second plurality of vanes are spaced apart from the aft end;
a third annular passage disposed about the second annular passage, the third annular passage including a third plurality of vanes to generate a swirled second airflow and a third opening at the aft end of the chamber, wherein the third plurality of vanes are spaced apart from the aft end;
a plurality of openings through the bulkhead of the chamber for communicating a central airflow to the chamber; and
a plurality of fuel tubes disposed about the axis and extending through the bulkhead into the chamber to communicate a second fuel flow to the chamber, wherein each of the plurality of fuel tubes includes an aft end that opens into the chamber and each of the ends are spaced axially away from the aft end of the chamber such that each of the plurality of fuel tubes communicate with the chamber.

6. The fuel injector as recited in claim 5 , wherein the plurality of fuel tubes includes a central tube disposed along the axis and a first plurality of fuel tubes disposed about the central tube, with at least some of the plurality of openings disposed between the central tube and the first plurality of fuel tubes.

7. The fuel injector as recited in claim 6 , including a second plurality of fuel tubes disposed about the first plurality of fuel tubes with at least some of the plurality of openings disposed between the first plurality of fuel tubes and the second plurality of fuel tubes.

8. The fuel injector as recited in claim 5 , including a fuel manifold disposed at a forward end of the plurality of fuel tubes for supplying fuel.

9. The fuel injector as recited in claim 8 , including an annular fuel chamber disposed forward of the second annular passage, the annular fuel chamber including a plurality of fuel inlets for receiving a fuel flow.

10. The fuel injector as recited in claim 5 , including a duct extending from the aft end of the chamber to a combustion chamber.

11. The fuel injector as recited in claim 5 , wherein the second annular passage is disposed between the first annular passage and the third annular passage.

12. The fuel injector as recited in claim 5 , wherein the aft end of each of the plurality of fuel tubes extends into the chamber and is spaced apart from the opening at the aft end of the chamber.

13. The fuel injector as recited in claim 5 , wherein at least one of the first plurality of vanes, the second plurality of vanes and the third plurality of vanes are disposed axially between the bulkhead and the aft end of the chamber.

Assignees

• Tuthill Richard S
• Davis Dustin W
• Dai Zhongtao
• United Technologies Corp

Inventors

• Tuthill Richard S
• Davis Dustin W
• Dai Zhongtao

Classifications

• F23R3/286

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

• F23R3/14 Primary

  by using swirl vanes · CPC title