Back to results
US 9,957,817 B2Granted
Tip leakage flow directionality control
AssigneeUnited Technologies Corporation
InventorsMark F. Zelesky, Andrew S. Aggarwala
Life of this patent
Estimating the term…
Abstract
A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall, a tip leakage control channel recessed into an outer surface of the tip wall, a tip leakage control vane integrally formed on the tip wall adjacent to the tip leakage control channel and an air seal radially outward of the tip wall and positioned to minimize leakage at the tip wall.
Claims18
A gas turbine engine, comprising:
- an airfoil having a tip wall that joins outer spanwise ends of a suction sidewall and a pressure sidewall and including a tip rib extending chordwise along a pressure side of said tip wall, wherein said tip wall includes a tip shelf disposed at a junction between said pressure sidewall and said tip rib;
- a plurality curved tip leakage control channels recessed into an outer surface of said tip wall, wherein each of said plurality of curved tip leakage control channels is adjacent to
- one of a plurality of curved tip leakage control vanes integrally formed on said tip wall contiguous with a suction side surface of said tip rib, said plurality of curved tip leakage channels extending toward said trailing edge while extending toward said suction sidewall;
- a first cooling aperture that feeds airflow to said tip leakage control channel;
- a second cooling aperture that feeds airflow to said tip shelf;
- and
- an air seal radially outward of said tip wall and positioned to minimize leakage at said tip wall.
4 more elements
A gas turbine engine, comprising:
- an airfoil having a tip wall including a plurality of curved tip leakage control channels recessed into an outer surface of said tip wall, said plurality of curved tip leakage control channels extending toward a trailing edge of said airfoil while extending toward a suction sidewall of said airfoil a tip leakage control vane formed with the outer surface of said tip wall and adjacent the plurality of curved tip leakage control channels;
- a winglet formed at a junction between said suction sidewall and said tip leakage control vane and localized at said tip leakage control vane;
- and
- a grooved blade outer air seal (BOAS) positioned radially outward of said tip wall and configured to minimize clearances at said tip wall, wherein said grooved BOAS includes a plurality of projections that protrude from a radially inner surface of said grooved BOAS and extend away from said radially inner surface in a direction toward said tip wall.
1 more element
Dependencies are inferred from the claim text.