Granted Patent B2

US 12,326,257 · App. 18/652,159 · Granted Jun 10, 2025

Inventors: Karpaga Vipran Kannan (Derby, GB); Joseph R Hardy (Derby, GB); Ryan L Rogers (Derby, GB); Andrés E Leiva Gonzalez (Loughborough, GB); Shahrokh Shahpar (Derby, GB)

Assignee: ROLLS-ROYCE plc

F23R3/14F23R3/283F23R3/346F23R3/286

Abstract

Claims (49)

1. A fuel swirl nozzle for a gas turbine engine, the gas turbine engine having a longitudinal axis, the fuel swirl nozzle comprising, in axial fuel flow sequence, a fuel inlet portion, a fuel stem portion, and a fuel/air swirler portion, an inlet to the fuel stem portion being fluidly sealed against the fuel inlet portion, and an outlet from the fuel stem portion being fluidly sealed against the fuel/air swirler portion; and

wherein the fuel/air swirler portion has a cross-sectional profile being generally dolioform shaped along an axis parallel to the engine longitudinal axis, and having a first end and a second end, the first end being an air inlet face to the fuel/air swirler portion, and the second end being a fuel/air mixture outlet face from the fuel/air swirler portion, the first end comprising a rim portion enclosing the air inlet face where the rim portion has a rim portion radius (Trim) normal to an outer circumference of the inlet face, and

wherein the air inlet face has a radius R in a plane normal to the engine longitudinal axis, and the rim portion radius frim is in a range of:

(

0.4

*

R

)

<

r

r

⁢

i

⁢

m

<

(

1.2

*

R

)

where: r rim is the rim portion radius, and

R is a radius of the air inlet face.

2. The fuel swirl nozzle as claimed in claim 1 , wherein the fuel/air swirler portion comprises two or more swirler portions, wherein at least one of the swirler portions is formed by an additive layer manufacturing process.

3. The fuel swirl nozzle as claimed in claim 1 , wherein the fuel stem portion is an elongate cylinder having an outer diameter D, the fuel stem portion having a first connection to the fuel inlet portion, and a second connection to the fuel/air swirler portion, and at least one of the first connection and the second connection comprises a blended joint having a joint blend radius, l′blend.

4. The fuel swirl nozzle as claimed in claim 3 , wherein the joint blend radius r blend is in a range of:

(

0.5

*

D

)

<

r

blend

<

(

1.

*

D

)

where: r blend is the joint blend radius, and

D is the diameter of the fuel stem portion.

5. The fuel swirl nozzle as claimed in claim 1 , further comprising a fuel stem shroud, the fuel stem shroud enclosing an axial length of the fuel stem portion, the fuel stem portion having a first cross-sectional profile with a corresponding first drag coefficient, wherein the fuel stem shroud has a second cross-sectional profile with a corresponding second drag coefficient, in which the second drag coefficient is less than the first drag coefficient.

6. The fuel swirl nozzle as claimed in claim 5 , wherein the second cross-sectional profile is generally lachrymiform shaped along an axis parallel to the engine longitudinal axis.

7. The fuel swirl nozzle as claimed in claim 1 , wherein the fuel inlet portion comprises a fluid restrictor, the fluid restrictor being configured to limit the flow of fuel through the fuel inlet portion.

8. The fuel swirl nozzle as claimed in claim 1 , wherein the gas turbine engine comprises, in axial flow sequence, a fan assembly, a compressor assembly, a combustor assembly, a turbine assembly, and an exhaust assembly, wherein the combustor assembly comprises a plurality of fuel swirl nozzles.

9. The fuel swirl nozzle as claimed in claim 8 , wherein the fan assembly comprises a plurality of fan blades extending radially from a hub, the plurality of fan blades defining a fan diameter (D FAN ), and wherein the fan diameter D FAN is within the range of 0.3 m to 2.0 m, preferably within the range 0.4 m to 1.5 m, and more preferably in the range of 0.7 m to 1.0 m.

10. The fuel swirl nozzle as claimed in claim 9 , wherein the fan assembly has two or more fan stages, at least one of the fan stages comprising a plurality of fan blades defining the fan diameter D FAN .

11. The fuel swirl nozzle as claimed in claim 8 , wherein the turbofan gas turbine engine further comprises an outer casing, the outer casing enclosing the sequential arrangement of fan assembly, compressor module, and turbine module, an annular bypass duct being defined between the outer casing and the sequential arrangement of compressor module, and turbine module, a bypass ratio being defined as a ratio of a mass air flow rate through the bypass duct to a mass air flow rate through the sequential arrangement of modules, and wherein the bypass ratio is less than 4.0.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (99)