Turbine airfoil with near-wall impingement and vortex cooling
AssigneeFlorida Turbine Technologies, Inc.
InventorGeorge Liang
Life of this patent
Estimating the term…
Abstract
A turbine airfoil includes a plurality of cooling modules formed on the outer surface of the airfoil wall and spaced along the pressure side and the suction side of the airfoil. Each cooling module includes a first diffusion cavity connected to the cooling supply cavity by a first metering hole to provide impingement cooling in the first diffusion cavity. On the sides of the first diffusion cavity are second and third vortex chambers connected to the first diffusion cavity by second and third metering holes. The first diffusion cavity and the two vortex chambers each include film cooling holes to provide film cooling to the airfoil wall. The cooling circuit provides an impingement cooling in series with vortex cooling in order to provide a more efficient cooling of the airfoil wall.
Claims20
A turbine airfoil comprising:
- a turbine wall having an inner surface forming a cooling supply channel and an outer surface forming the airfoil surface;
- a first diffusion cavity formed in the wall;
- a first metering hole connecting the cooling supply channel to the first diffusion cavity;
- a first film cooling hole connected to the first diffusion cavity;
- a first vortex chamber formed in the wall and adjacent to the first diffusion cavity;
- a second metering hole connecting the first diffusion cavity to the first vortex chamber;
- the second metering hole being formed between the inner surface and the outer surface such that convection cooling of the outer surface occurs within the second metering hole;
- the first diffusion cavity and the first vortex chamber being arranged along the airfoil chordwise direction;
- and,
- a second film cooling hole connected to the first vortex chamber.
A turbine airfoil having a leading edge and a trailing edge, and a pressure side and a suction side, the airfoil having a wall with an inner surface forming a cooling supply cavity, the turbine airfoil comprising:
- a plurality of cooling modules spaced along the pressure side and the suction side of the airfoil, each module including:
- a first diffusion cavity with a first metering hole connected to the cooling supply cavity;
- a second and third vortex chambers located on adjacent sides of the first diffusion cavity, the second vortex chamber being connected to the first diffusion cavity by a second metering hole, and the third vortex chamber being connected to the first diffusion cavity by a third metering hole;
- the second and third metering holes being formed between the inner surface and the outer surface such that convection cooling of the outer surface occurs within the second and third metering holes;
- the first diffusion cavity and the two vortex chambers each having at least one film cooling hole to discharge cooling air onto the airfoil surface;
- and,
- the first diffusion cavity and the second and third vortex chambers that form a single module are arranged along the blade chordwise direction with the third vortex chamber located upstream from the first diffusion cavity and the second vortex chamber located downstream from the first diffusion cavity.
Dependencies are inferred from the claim text.