Staged radial air swirler with radial liquid fuel distributor

Patent metadata

Field	Value
Publication number	US-10527286-B2
Application number	US-201615381609-A
Country	US
Kind code	B2
Filing date	Dec 16, 2016
Priority date	Dec 16, 2016
Publication date	Jan 7, 2020
Grant date	Jan 7, 2020

Abstract

A nozzle includes a nozzle body with an inner air passage fed by a first radial swirler and a second radial swirler axially downstream of the first radial swirler. A first fuel circuit is axially between the first and second radial swirlers. A second fuel circuit is axially downstream of the second radial swirler, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet. An outer air passage is defined between a fuel circuit outer wall of the second fuel circuit and an outer air passage wall, wherein the outer air passage is a converging non-swirling air passage. An intermediate air passage can be defined between an intermediate wall and the second radial swirler, wherein the intermediate air passage is a converging non-swirling air passage.

First claim

What is claimed is:

1. A nozzle comprising:
a nozzle body defining a longitudinal axis and including:
an inner air passage fed by a first radial swirler and a second radial swirler axially downstream of the first radial swirler;
a first fuel circuit axially between the first and second radial swirlers with respect to the longitudinal axis;
a second fuel circuit axially downstream of the second radial swirler with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet; and
an outer air passage defined between a fuel circuit outer wall of the second fuel circuit and an outer air passage wall, wherein the outer air passage is a converging non-swirling air passage, wherein the fuel circuit inlet of the first fuel circuit includes a plurality of circumferentially spaced apart openings for fluid communication with a fuel manifold, and wherein the fuel circuit inlet of the second fuel circuit includes a plurality of circumferentially spaced apart openings for fluid communication with the fuel manifold, wherein the first radial swirler includes radial swirl vanes circumferentially spaced apart from one another about an annular inner air inlet, wherein the nozzle body includes a plurality of tubes, wherein the plurality of tubes comprise a first set of tubes and a second set of tubes, each tube of the first set of tubes connecting a respective circumferentially spaced apart opening of the first fuel circuit to the fuel manifold and each tube of the second set of tubes connecting a respective circumferentially spaced apart opening of the second fuel circuit to the fuel manifold, wherein the plurality of tubes pass axially through the radial swirl vanes of the first radial swirler.

2. The nozzle as recited in claim 1 , wherein the inner air passage, outer air passage, first fuel circuit, and second fuel circuit are configured for diffusion flame injection without pre-mixing within the nozzle body.

3. The nozzle as recited in claim 1 , wherein the inner air passage is free from obstructions along the longitudinal axis downstream of the first radial swirler.

4. The nozzle as recited in claim 1 , wherein each of the first and second fuel circuits is configured for injection of liquid fuel.

5. The nozzle as recited in claim 1 , wherein the first and second fuel circuits are configured for staged operation.

6. The nozzle as recited in claim 1 , wherein an ignitor is located in an upstream wall of the nozzle body, oriented concentrically on the longitudinal axis.

7. The nozzle as recited in claim 1 , wherein at least one of the first and second fuel circuits includes a plurality of helical passages, wherein each helical passage opens tangentially with respect to the respective fuel circuit outlet.

8. The nozzle as recited in claim 7 , wherein the helical passages define a flow exit angle relative to the longitudinal axis of at least 85°.

9. The nozzle as recited in claim 1 , wherein the second fuel circuit is defined between the fuel circuit outer wall of the second fuel circuit and a fuel circuit inner wall of the second fuel circuit, and wherein the first fuel circuit is defined between a fuel circuit inner wall of the first fuel circuit and a fuel circuit outer wall of the first fuel circuit.

10. The nozzle as recited in claim 9 , wherein an intermediate wall is between the first and second fuel circuits, wherein an intermediate air passage is defined between the intermediate wall and the first fuel circuit, wherein the intermediate air passage is a converging non-swirling air passage.

11. The nozzle as recited in claim 9 , wherein at least a portion of the fuel circuit inner wall of the first fuel circuit, a portion of the fuel circuit outer wall of the first fuel circuit, a portion of the fuel circuit inner wall of the second fuel circuit and a portion of the fuel circuit outer wall of the second fuel circuit each have a conical shape that converges toward the longitudinal axis.

12. A nozzle comprising:
a nozzle body defining a longitudinal axis and including:
an inner air passage fed by a first radial swirler and a second radial swirler axially downstream of the first radial swirler;
a first fuel circuit axially between the first and second radial swirlers with respect to the longitudinal axis;
a second fuel circuit axially downstream of the second radial swirler with respect to the longitudinal axis, wherein each of the first fuel circuit and the second fuel circuit extends from a respective fuel circuit inlet to a respective annular fuel circuit outlet, wherein the second fuel circuit is defined between a fuel circuit outer wall of the second fuel circuit and a fuel circuit inner wall of the second fuel circuit, and wherein the first fuel circuit is defined between a fuel circuit inner wall of the first fuel circuit and a fuel circuit outer wall of the first fuel circuit; and
an outer air passage defined between the fuel circuit outer wall of the second fuel circuit and an outer air passage wall, wherein the outer air passage is a converging non-swirling air passage, wherein the fuel circuit inlet of the first fuel circuit includes a plurality of circumferentially spaced apart openings for fluid communication with a fuel manifold, and wherein the fuel circuit inlet of the second fuel circuit includes a plurality of circumferentially spaced apart openings for fluid communication with the fuel manifold, wherein a first set of tubes connect the circumferentially spaced apart openings of the second fuel circuit and pass axially through the fuel circuit inner wall of the first fuel circuit, the first fuel circuit, and the fuel circuit outer wall of the first fuel circuit.

13. The nozzle as recited in claim 12 , wherein a second set of tubes connect the circumferentially spaced apart openings of the first fuel circuit and pass axially through respective vanes of the first radial swirler.

14. The nozzle as recited in claim 13 , wherein each tube in the first set of tubes passes through vanes in both the first and second radial swirlers.

Assignees

• Delavan Inc

Inventors

• Prociw Lev Alexander
• Ryon Jason A

Classifications

• F23D11/105

  at least one of the fluids being submitted to a swirling motion · CPC title

• F23R3/346

  for staged combustion · CPC title

• F23D14/24

  at least one of the fluids being submitted to a swirling motion · CPC title

• F23R3/54

  Reverse-flow combustion chambers · CPC title

• F02C7/22

  Fuel supply systems · CPC title