Turbine shroud thermal distortion control
AssigneeUnited Technologies Corporation
InventorsJun Shi, Kevin E. Green, Shaoluo L. Butler, Gajawalli V. Srinivasan, Glenn N. Levasseur
Life of this patent
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Abstract
A shroud for a gas turbine engine includes a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that break up the leading portion into circumferentially spaced segments separated by the first set of slots, and a trailing portion adjacent to the leading portion. The trailing portion has a trailing edge.
Claims20
A shroud for a gas turbine engine, the shroud comprising:
- a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that break up the leading portion into circumferentially spaced segments separated by the first set of slots;
- and
- a trailing portion adjacent to the leading portion, the trailing portion having a trailing edge.
A shroud for a gas turbine engine, the shroud comprising:
- a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that interrupt the leading portion in a circumferential direction, each of the first set of slots extends through a full thickness of the leading portion of the shroud and has a closed end within the shroud;
- and
- a trailing portion adjacent to the leading portion, the trailing portion having a trailing edge.
A shroud assembly suitable for use in a gas turbine engine, the shroud assembly comprising:
- a shroud comprising:
- a leading portion;
- a trailing portion adjacent to the leading portion;
- and
- a clamping device exerting a radially inward force on the leading portion for restraining a thermal growth of the leading portion in a radially outward direction while allowing unconstrained thermal growth of the trailing portion to even out thermal growth of the shroud.
Dependencies are inferred from the claim text.