Turbine rotor blade
AssigneeGeneral Electric Company
InventorsRohit Chouhan, Shashwat Swami Jaiswal
Life of this patent
Estimating the term…
Abstract
A turbine rotor blade includes a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge. Also included is a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall. Further included is at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity. Yet further included is a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.
Claims20
A turbine rotor blade comprising:
- a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge;
- a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall;
- at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity;
- and
- a main body having a suction side wall and a pressure side wall each extending from a root portion of the turbine rotor blade to the tip portion.
A turbine section of a turbine system comprising:
- a plurality of turbine rotor blades forming a plurality of turbine stages, wherein each of the plurality of turbine rotor blades includes a main body having a leading edge, a trailing edge, a suction side wall and a pressure side wall;
- a tip portion of at least one of the plurality of turbine rotor blades having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge;
- a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall;
- and
- at least one hole defined by the suction tip wall, the at least one hole configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity.
A gas turbine engine comprising:
- a compressor section;
- a combustion section;
- and
- a turbine section comprising:
- a tip portion having a pressure tip wall and a suction tip wall, a tip leading edge and a tip trailing edge;
- a squealer cavity at least partially defined by the pressure tip wall and the suction tip wall;
- and
- a plurality of holes defined by the suction tip wall and located proximate the tip leading edge, the plurality of holes configured to bleed a cooling flow out of the squealer cavity into a hot gas path to reduce pressure within the squealer cavity.
Dependencies are inferred from the claim text.