Airblast fuel injector

Patent metadata

Field	Value
Publication number	US-9562691-B2
Application number	US-201414490789-A
Country	US
Kind code	B2
Filing date	Sep 19, 2014
Priority date	Sep 30, 2013
Publication date	Feb 7, 2017
Grant date	Feb 7, 2017

Abstract

An airblast fuel injector is provided for a fuel spray nozzle of a gas turbine engine. The injector has an annular air passage for the passage of a swirling air flow therethrough. The swirling air flow is used by the injector to produce an atomized fuel spray. The air passage contains a swirler for producing the swirling air flow, the swirler comprising a circumferential row of vanes which span inner and outer side walls of the air passage. Viewed on a longitudinal section through the injector, the air passage has a bend downstream of the swirler, the bend changing the direction of the air passage. The vanes are configured to introduce a radial component to the air flow exiting the swirler, the radial component guiding the air flow around the bend.

First claim

The invention claimed is:

1. An airblast fuel injector for a fuel spray nozzle of a gas turbine engine, the fuel injector having an annular air passage for the passage of a swirling air flow therethrough, the swirling air flow being used by the fuel injector to produce an atomised fuel spray, wherein:
the air annular passage contains a swirler for producing the swirling air flow, the swirler comprising a circumferential row of vanes which span inner and outer side walls of the annular air passage;
viewed on a longitudinal section through the fuel injector, the annular air passage has a bend downstream of the swirler, the bend changing the direction of the annular air passage; and
the vanes are configured to introduce a radial outward component to the air flow exiting the swirler, the radial outward component guiding the air flow around the bend,
wherein the vanes are leant to introduce the radial component to the air flow exiting the swirler such that, across each inter-vane passage formed by a suction surface of one vane and a facing pressure surface of a neighbouring vane, with increasing radial distance the lean inclines the suction surface towards the pressure surface.

2. The airblast fuel injector of claim 1 , wherein the bend changes the direction of the annular air passage such that the annular air passage turns radially outwards downstream of the bend, the vanes being configured to introduce a radial outward component to the air flow exiting the swirler.

3. The airblast fuel injector of claim 1 , which further has an annular fuel passage coaxial with the annular air passage, the annular fuel passage feeding fuel into the annular air passage through a port located downstream of the bend at the radially outer side wall of the annular air passage.

4. The airblast fuel injector of claim 3 , wherein the bend is formed by smoothly curved portions of the side walls of the annular air passage.

5. The airblast fuel injector of claim 4 , wherein the smoothly curved portions of the side walls begin at the swirler.

6. The airblast fuel injector of claim 1 , wherein the leading and/or trailing edges of the vanes are forward swept to introduce the radial outward component to the air flow exiting the swirler.

7. A fuel spray nozzle of a gas turbine engine having the airblast fuel injector of claim 1 .

8. A fuel spray nozzle according to claim 1 , wherein the airblast fuel injector is a mains fuel injector, the nozzle further having a pilot fuel injector radially inwardly of the mains fuel injector.

9. A combustor of a gas turbine engine having a plurality of fuel spray nozzles according to claim 7 .

10. A gas turbine engine having the combustor of claim 9 .

11. An airblast fuel injector for a fuel spray nozzle of a gas turbine engine, the fuel injector having an annular air passage for the passage of a swirling air flow therethrough, the swirling air flow being used by the fuel injector to produce an atomised fuel spray,
wherein the annular air passage contains a swirler for producing the swirling air flow, the swirler comprising a circumferential row of vanes which span inner and outer side walls of the annular air passage, viewed on a longitudinal section through the fuel injector, the annular air passage has a bend downstream of the swirler, the bend changing the direction of the annular air passage such that the annular air passage turns radially outwards downstream of the bend, each vane comprises a suction surface and a pressure surface, the vanes are configured to introduce a radial outward component to the air flow exiting the swirler, the radial outward component guiding the air flow around the bend, the vanes are leant to introduce the radial outward component to the air flow exiting the swirler such that, across each inter-vane passage formed by a suction surface of one vane and a facing pressure surface of a neighbouring vane, with increasing radial distance the lean inclines the suction surface towards the pressure surface, and an annular fuel passage coaxial with the annular air passage, the annular fuel passage feeding fuel into the annular air passage through a port located downstream of the bend at the radially outer side wall of the annular air passage.

12. An airblast fuel injector for a fuel spray nozzle of a gas turbine engine, the fuel injector having an annular air passage for the passage of a swirling air flow therethrough, the swirling air flow being used by the fuel injector to produce an atomised fuel spray,
wherein the annular air passage contains a swirler for producing the swirling air flow, the swirler comprising a circumferential row of vanes which span inner and outer side walls of the annular air passage, viewed on a longitudinal section through the fuel injector, the annular air passage has a bend downstream of the swirler, the bend changing the direction of the annular air passage such that the annular air passage turns radially outwards downstream of the bend, each vane comprises a suction surface and a pressure surface, the vanes are configured to introduce a radial outward component to the air flow exiting the swirler, the radial outward component guiding the air flow around the bend, the each vane comprises a leading edge and a trailing edge, the leading and/or trailing edges of the vanes are forward swept to introduce the radial outward component to the air flow exiting the swirler, and an annular fuel passage coaxial with the annular air passage, the annular fuel passage feeding fuel into the annular air passage through a port located downstream of the bend at the radially outer side wall of the annular air passage,
wherein the bend is formed by smoothly curved portions of the inner and outer side walls of the annular air passage.

Assignees

• Rolls Royce Plc

Inventors

• Ford Christopher
• Barker Ashley Gavin
• Walker Alastair Duncan
• Carrotte Jonathan

Classifications

• F23R3/30 Primary

  comprising fuel prevapourising devices · CPC title

• F23R3/14 Primary

  by using swirl vanes · CPC title