Turbine engine with metered cooling system
AssigneeRolls-Royce North American Technologies Inc.
InventorsBrandon R. Snyder, Jonathan S. Sands
Life of this patent
Estimating the term…
Abstract
An assembly adapted for use with a gas turbine engine includes a static component and a metering band. The static component is fixed relative to an axis. The metering band is arranged to extend circumferentially at least partway about the axis and is coupled with the static component. The metering band defines at least a portion of a cooling passageway for air to flow through.
Claims20
An assembly adapted for use with a gas turbine engine, the assembly comprising
- a static component fixed relative to an axis,
- a first metering band arranged to extend circumferentially at least partway about the axis and coupled with the static component at a discrete location, and
- a second metering band located adjacent the first metering band and arranged to extend circumferentially at least partway about the axis and coupled with the static component,
- wherein the first metering band defines at least a portion of a cooling passageway, the second metering band defines another portion of the cooling passageway, and the first metering band is configured to expand and contract relative to the static component in response to temperature changes of the assembly to change a size of the cooling passageway.
An assembly adapted for use with a gas turbine engine, the assembly comprising
- a static component fixed in position relative to an axis, the static component formed to define a channel that extends circumferentially around the axis,
- a first metering band located in the channel and arranged to extend circumferentially at least partway about the axis, and the first metering band coupled to the static component at a first discrete location for movement with the static component,
- a second metering band located in the channel and arranged to extend circumferentially at least partway about the axis, the second metering band located adjacent the first metering band, and the second metering band coupled to the static component at a second discrete location for movement with the static component,
- wherein the first metering band and the second metering band cooperate to define a cooling passageway and the first metering band and the second metering band are configured to expand and contract relative to the static component in response to temperature changes of the assembly to change a size of the cooling passageway.
A method for varying cooling flow in a gas turbine engine, the method comprising the steps of:
- mounting a first metering band to a static component so that a first terminal end of the first metering band is fixed at a discrete location of the static component and a second terminal end of the first metering band is free to move relative to the first terminal end, and an aperture that extends through the first metering band forms a portion of a cooling passageway,
- arranging a first aperture that extends through in the first metering band to form a portion of a cooling passageway to overlap with a second aperture that extends through the static component that forms another portion of the cooling passageway to form a cooling passage area, and
- varying a circumferential length of the first metering band so that the second terminal end extends away from and toward the first terminal end in response to temperature changes of the gas turbine engine so that the first aperture and the second aperture move relative to each other and vary the cooling passage area.
Dependencies are inferred from the claim text.