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US 11,454,125 B1Granted
Airfoil with directional diffusion region
AssigneeDoosan Heavy Industries Construction Co., Ltd
InventorsGene Chong, Andres Jaramillo, Kibaek Kim
Life of this patent
Estimating the term…
Abstract
A turbine blade for a gas turbine engine. The turbine blade includes a cooling path for a coolant, routing the coolant through an internal cooling cavity and out through a plurality of cooling holes formed proximate a trailing edge of the turbine blade. Each of the cooling holes including a diffusing region designed so that a coolant does not separate from a radially inward sidewall of the diffusing region.
Claims19
An airfoil comprising:
- a suction sidewall extending from a leading edge to a trailing edge;
- a pressure sidewall extending from the leading edge to the trailing edge and joined to the suction sidewall at the leading edge and the trailing edge, the suction sidewall and the pressure sidewall defining a cooling cavity therebetween;
- a first flow divider positioned proximate the trailing edge and within the cooling cavity, the first flow divider extending from the suction sidewall to the pressure sidewall;
- the first flow divider comprising a leading wall, a first wall extending from the leading wall to the trailing edge, and a second wall extending from the leading wall to the trailing edge opposite the first wall;
- the first wall having a parallel portion and a converging portion, the parallel portion of the first wall being parallel with the second wall, the converging portion of the first wall converging towards the second wall, the converging portion positioned between the parallel portion and the trailing edge;
- a second flow divider positioned proximate the trailing edge and within the cooling cavity, the second flow divider extending from the suction sidewall to the pressure sidewall;
- the second flow divider comprising a second leading wall, a third wall extending from the second leading wall to the trailing edge, and a fourth wall extending from the second leading wall to the trailing edge opposite the third wall;
- and
- the third wall having a parallel portion and a converging portion, the parallel portion of the third wall being parallel with the fourth wall, the converging portion of the third wall converging towards the fourth wall, the converging portion positioned between the parallel portion and the trailing edge,
- wherein the first wall faces the fourth wall to define a passageway for communicating coolant from within the cooling cavity out of the airfoil.
7 more elements
The airfoil of 5 further comprising a plurality of additional flow dividers defining a plurality of additional passageways in communication with a plurality of additional cooling holes.
A turbine blade comprising:
- a suction sidewall extending from a leading edge to a trailing edge;
- a pressure sidewall extending from the leading edge to the trailing edge and joined to the suction sidewall at the leading edge and the trailing edge, the suction sidewall and the pressure sidewall defining a cooling cavity therebetween;
- a first flow divider positioned proximate the trailing edge and within the cooling cavity, the first flow divider extending from the suction sidewall to the pressure sidewall, the first flow divider having a first leading wall positioned opposite the trailing edge, the first flow divider having a first parallel wall extending from the first leading wall to the trailing edge in a first direction;
- and
- a second flow divider positioned proximate the trailing edge and within the cooling cavity, the second flow divider extending from the suction sidewall to the pressure sidewall, the second flow divider having a second leading wall positioned opposite the trailing edge, the second flow divider having a second parallel wall extending from the second leading wall to a diverging wall in the first direction and in parallel with the first parallel wall, the diverging wall extending from the second parallel wall to the trailing edge in a second direction away from the first parallel wall.
2 more elements
A method of manufacturing a turbine blade having directional diffusing cooling holes, the method comprising:
- forming an airfoil portion of the turbine blade, wherein the airfoil portion comprises:
- a suction sidewall extending from a leading edge to a trailing edge;
- a pressure sidewall extending from the leading edge to the trailing edge and joined to the suction sidewall at the leading edge and the trailing edge, the suction sidewall and the pressure sidewall defining a cooling cavity therebetween;
- a plurality of cooling holes formed in the pressure sidewall, the plurality of cooling holes being radially aligned proximate the trailing edge;
- a plurality of flow dividers extending from the pressure sidewall to the suction sidewall, the plurality of flow dividers being radially aligned proximate the trailing edge in alternating arrangement with the plurality of cooling holes such that each cooling hole opens to a passageway defined between adjacent flow dividers;
- each passageway defined by a first boundary wall associated with a first flow divider and a second boundary wall associated with a second flow divider, the first boundary wall extends in parallel to the trailing edge in a first direction, the second boundary wall has a parallel portion that extends in the first direction and parallel with the first boundary wall and a diverging portion that extends from the parallel portion to the trailing edge and away from the first boundary wall;
- and
- removing a portion of the pressure sidewall adjacent at which the plurality of cooling holes are formed.
5 more elements
Dependencies are inferred from the claim text.