Fuel nozzles

Patent metadata

Field	Value
Publication number	US-9897321-B2
Application number	US-201514674580-A
Country	US
Kind code	B2
Filing date	Mar 31, 2015
Priority date	Mar 31, 2015
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

A nozzle includes a nozzle body defining a longitudinal axis. The nozzle body includes an air passage having a radial swirler and a converging conical cross-section. A fuel circuit is radially outboard from the air passage with respect to the longitudinal axis. The fuel circuit extends from a fuel circuit inlet to a fuel circuit annular outlet. The fuel circuit includes a plurality of helical passages to mitigate gravitational effects at low fuel flow rates. Each helical passage of the fuel circuit opens tangentially with respect to the fuel circuit annular outlet into an outlet of the air passage.

First claim

What is claimed is:

1. A nozzle, comprising:
a nozzle body defining a longitudinal axis including:
an air passage having a radial swirler and a converging conical cross-section;
an annular fuel manifold upstream of the radial swirler and surrounding the air passage; and
a fuel circuit radially outboard from the air passage with respect to the longitudinal axis, the fuel circuit extending from a fuel circuit inlet to a fuel circuit annular outlet, wherein the fuel circuit includes a plurality of helical passages to mitigate gravitational effects at low fuel flow rates, wherein the plurality of helical passages are located downstream of the radial swirler and are in fluid communication with the annular fuel manifold, and each of the plurality of helical passages of the fuel circuit opens tangentially with respect to the fuel circuit annular outlet into an outlet of the air passage.

2. The nozzle as recited in claim 1 , wherein each of the plurality of helical passages intersects a single cross-sectional plane taken along the longitudinal axis.

3. The nozzle as recited in claim 1 , wherein more than one of the plurality of helical passages intersect each cross-sectional plane taken along the longitudinal axis.

4. The nozzle as recited in claim 1 , wherein each of the plurality of helical passages completes at least one 360 degree pass through the fuel circuit.

5. The nozzle as recited in claim 1 , wherein the plurality of helical passages are defined by helical threads in at least one of a fuel circuit inner wall or a fuel circuit outer wall.

6. The nozzle as recited in claim 1 , wherein the fuel circuit annular outlet is proximate to the outlet of the air passage.

7. The nozzle as recited in claim 1 , wherein the fuel circuit is defined between a fuel circuit inner wall and a fuel circuit outer wall, wherein at least a portion of the fuel circuit outer wall is radially outboard from the fuel circuit inner wall with respect to the longitudinal axis, and wherein at least a portion of both the fuel circuit inner wall and outer wall are conical shapes that converge toward the longitudinal axis.

8. The nozzle as recited in claim 1 , wherein the fuel circuit inlet includes a plurality of circumferentially spaced apart openings in fluid communication with the annular fuel manifold.

9. The nozzle as recited in claim 8 , wherein the nozzle body includes a plurality of tubes defined through the air passage, each tube of the plurality of tubes connecting a respective one of the plurality of circumferentially spaced apart openings to the annular fuel manifold.

10. The nozzle as recited in claim 9 , wherein the air passage includes an annular inlet, and wherein the radial swirler includes radial swirl vanes circumferentially spaced apart from one another about the annular inlet, wherein the plurality of tubes are defined within the radial swirl vanes.

11. The nozzle as recited in claim 1 , wherein the air passage is defined between a backing plate and a fuel circuit inner wall downstream from the backing plate, wherein at least a portion of the fuel circuit inner wall is a conical shape that converges toward the longitudinal axis.

12. The nozzle as recited in claim 1 , wherein the air passage includes an annular inlet, and wherein the radial swirler includes radial swirl vanes circumferentially spaced apart from one another about the annular inlet to induce swirl into air entering the annular inlet.

13. The nozzle as recited in claim 1 , wherein the nozzle body includes an insulation jacket between the air passage and the fuel circuit.

14. The nozzle as recited in claim 1 , wherein the nozzle body includes an outer air passage defined radially outboard of the fuel circuit with respect to the longitudinal axis.

15. The nozzle as recited in claim 14 , wherein the outer air passage is defined between a fuel circuit outer wall and an outer air passage wall, and wherein the outer air passage is a converging non-swirling outer air passage.

Assignees

• Delavan Inc
• Delavan Inc

Inventors

• Prociw Lev Alexander

Classifications

• F23C7/004

  using vanes · CPC title

• F23D11/383

  with swirl means · CPC title

• F23R3/346

  for staged combustion · CPC title

• F23D11/107

  at least one of both being subjected to a swirling motion · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title