Coolable air foil for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsMark F. Zelesky, Dominic J. Mongillo, David J. Candelori, Gary D. Steuber
Life of this patent
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Abstract
A coolable airfoil (25) for a gas turbine engine includes a leading edge portion (52) cooled by a combination of radial and impingement flows through internal passages (80) and (90) separated by an internal wall (95) which is imperforate along a radially inner portion (100) thereof and apertured along a radially outer portion (105) thereof
Claims12
A coolable airfoil for a gas turbine engine, said airfoil having a leading edge portion, said airfoil further including an internal wall defining, with an inner surface of said leading edge portion, a first cooling gas passage, said internal wall further defining in part, a second cooling gas passage generally parallel and adjacent to said first cooling gas passage, said airfoil being characterized by:
- said first and second cooling gas passages being supplied with cooling gas from radially inner ends thereof;
- said internal wall being perforated along a first portion thereof to accommodate cooling gas flow from said second passage through said perforations, to said first passage for impingement cooling of said inner surface of said leading edge portion;
- and
- said internal wall being imperforate along a second portion thereof, whereby a corresponding portion of said leading edge inner surface is cooled by radial flow of cooling gas through said first passage.
A coolable airfoil for a gas turbine engine, said airfoil having a leading edge portion, said airfoil further including an internal wall defining, with an inner surface of said leading edge portion, a first cooling gas passage, said internal wall further defining in part, a second cooling gas passage generally parallel and adjacent to said first cooling gas passage, said airfoil being characterized by:
- said first and second cooling gas passages being supplied with cooling gas from radially inner ends thereof;
- said internal wall being imperforate along a radially inner portion thereof, whereby a radially inner portion of said leading edge portion is cooled only by radial outer flow through said first passage;
- said internal wall being perforated along a radially outer portion thereof, whereby a radially medial portion of said leading edge is cooled by a combination of radial flow through said first passage, and impingement flow of cooling gas against an inner surface of said leading edge portion from said second passage, through said perforations in said internal wall and;
- a flow resistance disposed in at least a radially outer portion of said first passage to stagnate radial coolant gas flow therein, whereby a radially outer portion of said leading edge is cooled only by impingement flow of cooling gas against an inner surface of said leading edge from said second passage, through said perforations in said internal wall.
Dependencies are inferred from the claim text.