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US 6,142,734 AGranted
Internally grooved turbine wall
AssigneeGeneral Electric Company
InventorChing-Pang Lee
Life of this patent
Estimating the term…
Abstract
A turbine wall includes an outer surface for facing combustion gases, and an opposite inner surface for being impingement air cooled. A plurality of adjoining ridges and grooves are disposed in the inner surface for enhancing heat transfer by the impingement cooling air.
Claims43
A turbine wall comprising an outer surface for facing combustion gases;
- an opposite inner surface for being air cooled;
- and a plurality of adjoining parallel and elongate ridges and grooves in said inner surface being generally equal in width;
- and being sized in height to exceed a boundary layer thickness of said cooling air for increasing heat transfer.
A turbine wall comprising an outer surface for facing combustion gases;
- an opposite inner surface for being air cooled;
- and a plurality of adjoining parallel ridges and grooves in said inner surface, and wherein said grooves are concave, and said ridges are convex.
A turbine wall comprising an outer surface for facing combustion gases;
- an opposite inner surface for being air cooled;
- and a plurality of adjoining parallel ridges and grooves in said inner surface, and wherein said grooves are concave, and said ridges are flat between adjacent grooves.
An airfoil comprising:
- an outer surface defining pressure and suction sides extending longitudinally along a span axis and laterally along a chord axis for facing combustion gases;
- an opposite inner surface defining an inner cavity of said airfoil extending along said span axis for being air cooled;
- a plurality of adjoining parallel ridges and grooves in said inner surface, and wherein said ridges are inclined between said span and chord axes.
A turbine rotor blade comprising:
- an outer surface defining pressure and suction sides of an airfoil extending longitudinally along a span axis and laterally along a chord axis for facing combustion gases;
- an opposite inner surface defining an inner cavity of said airfoil extending along said span axis for being air cooled;
- a plurality of adjoining parallel ridges and grooves in said inner surface, wherein said ridges extend along said chord axis;
- and
- an impingement baffle forming a bridge extending integrally between said pressure and suction sides at a leading edge of said airfoil along said inner cavity, and spaced from said ridges for impinging said cooling air thereagainst.
2 more elements
A turbine nozzle vane comprising:
- an outer surface defining pressure and suction sides extending longitudinally along a span axis and laterally along a chord axis;
- an inner surface defining an inner cavity extending along said span axis for channeling cooling air;
- and
- a plurality of adjoining parallel and elongate ridges and grooves in said inner surface being generally equal in width, and being sized in height to exceed a boundary layer thickness of said cooling air for increasing heat transfer.
1 more element
A turbine nozzle vane comprising:
- an outer surface defining pressure and suction sides extending longitudinally along a span axis and laterally along a chord axis;
- an inner surface defining an inner cavity extending along said span axis for channeling cooling air;
- a plurality of adjoining ridges and grooves in said inner surface for being cooled by said air;
- and
- an impingement baffle disposed inside said cavity and spaced from said ridges and grooves for impinging said cooling air thereagainst;
- and
- wherein said ridges are sized in height to exceed a boundary layer thickness of said cooling air for increasing heat transfer.
4 more elements
A turbine rotor blade comprising:
- an outer surface defining pressure and suction sides extending longitudinally along a span axis and laterally along a chord axis;
- an inner surface defining an inner cavity extending along said span axis for channeling cooling air;
- and
- a plurality of adjoining parallel and elongate ridges and grooves in said inner surface being generally equal in width, and being sized in height to exceed a boundary layer thickness of said cooling air for increasing heat transfer.
1 more element
A turbine rotor blade comprising:
- an outer surface defining pressure and suction sides extending longitudinally along a span axis and laterally along a chord axis;
- an inner surface defining an inner cavity extending along said span axis for channeling cooling air;
- a plurality of adjoining ridges and grooves in said inner surface for being cooled by said air;
- an impingement baffle disposed inside said cavity and spaced from said ridges and grooves for impinging said cooling air thereagainst;
- and
- wherein said ridges are sized in height to exceed a boundary layer thickness of said cooling air for increasing heat transfer.
3 more elements
A turbine shroud comprising:
- an outer surface being arcuate to face radially inwardly above a row of turbine blades;
- an opposite inner surface being outwardly exposed for being impingement air cooled;
- and
- a plurality of adjoining parallel and elongate ridges and grooves in said inner surface being generally equal in width, and being sized in height to exceed a boundary layer thickness of said cooling air for increasing heat transfer.
1 more element
A turbine shroud comprising:
- an outer surface being arcuate to face radially inwardly above a row of turbine blades;
- an opposite inner surface being outwardly exposed for being impingement air cooled;
- and
- a plurality of adjoining parallel ridges and grooves in said inner surface for being impingement cooled by said air;
- and wherein said ridges are sized in height to exceed a boundary layer thickness of said cooling air for increasing heat transfer.
2 more elements
A core die for making a core for casting a turbine airfoil having opposite outer and inner surfaces, with a plurality of adjoining ridges and grooves extending along said inner surface, comprising:
- a shell having an inner cavity matching said airfoil inner surface with ridges and grooves therein for forming mirror features around said core;
- and
- wherein said shell has a longitudinal axis and is open at an inlet end, and said ridges are parallel to said longitudinal axis.
Dependencies are inferred from the claim text.