Back to results
US 8,801,372 B2Granted
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
Estimating the term…
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.
Claims17
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, wherein a length of at least one of the first set of circumferentially spaced slots is approximately 40% of an axial length of the shroud;
- 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, wherein a length of at least one of the first set of circumferentially spaced slots is approximately 40% of an axial length of the shroud;
- and
- a trailing portion adjacent to the leading portion, the trailing portion having a trailing edge.
Dependencies are inferred from the claim text.