Swirler for combustor of gas turbine engine
AssigneeUnited Technologies Corporation
InventorsSteven D. Porter, Cara M. Redding
Life of this patent
Estimating the term…
Abstract
A combustor for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber, and a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion. The fuel injector includes a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis. A swirler for a gas turbine engine includes a swirler entrance and a swirler exit. The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.
Claims15
A combustor for a gas turbine engine, comprising:
- an annular combustor shell, the annular combustor shell defining a combustion chamber;
- and
- a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion, the fuel injector including a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis, the swirler exit including:
- an inboard exit portion formed with an inboard radius;
- an outboard exit portion formed with an outboard radius;
- and
- a circumferential end portion connecting the inboard exit portion and the outboard exit portion, the circumferential end portion continuously curvilinear from the inboard exit portion to the outboard exit portion;
- wherein one or more of the inboard radius and the outboard radius are coaxial with the annular combustor shell.
A gas turbine engine comprising:
- a turbine section;
- and
- a combustor section to provide combustion gases to the turbine section to drive the turbine section, the combustion section including:
- an annular combustor shell, the annular combustor shell defining a combustion chamber;
- and
- a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion, the fuel injector including a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis, the swirler exit including:
- an inboard exit portion formed with an inboard radius;
- an outboard exit portion formed with an outboard radius;
- and
- a circumferential end portion connecting the inboard exit portion and the outboard exit portion, the circumferential end portion continuously curvilinear from the inboard exit portion to the outboard exit portion;
- wherein one or more of the inboard radius and the outboard radius are coaxial with the annular combustor shell.
A swirler for a gas turbine engine, comprising:
- a swirler entrance;
- and
- a swirler exit, the swirler exit having a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis, the swirler exit including:
- an inboard exit portion formed with an inboard radius;
- an outboard exit portion formed with an outboard radius;
- and
- a circumferential end portion connecting the inboard exit portion and the outboard exit portion, the circumferential end portion continuously curvilinear from the inboard exit portion to the outboard exit portion;
- wherein one or more of the inboard radius and the outboard radius are coaxial with the curvilinear circumferential axis.
Dependencies are inferred from the claim text.