Shear jet cooling passages for internally cooled machine elements
AssigneeGeneral Electric Company
InventorChing-Pang Lee
Life of this patent
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Abstract
A cooling passageway construction particularly adapted for cooling the interior of a heated turbine engine assembly and/or airfoil blade includes an undulating partition which subdivides the passageway into first and second subpassages. The partition defines localized minimum throat areas within each subpassage to produce localized shear jet flow between the partition and the walls of the passageway. Bleed holes may be formed through the partition to generate additional turbulence within the coolant flow and further enhance heat transfer.
Claims20
A cooling passageway construction for cooling the interior of a heated machine element or machine assembly, said passageway comprising a partition subdividing said passageway into a first subpassage and a second subpassage, said partition having a wavy configuration defining a series of spaced apart minimum throat areas along said first and second subpassages such that said minimum throat areas defined along said first subpassage are staggered between said minimum throat areas defined along said second subpassage.
A gas turbine engine apparatus constructed with an internal cooling passageway defining a first wall and a second wall, said passageway having a partition extending therethrough so as to divide said passageway into a first subpassage and a second subpassage, said first subpassage having a flowpath cross section extending between said partition and said first wall and said second subpassage having a flowpath cross section extending between said partition and said second wall, said first and second subpassages respectively defining along with said partition, spaced apart minimum flowpath throat areas located between said partition and said first and second walls for producing high velocity flow along said first and second walls and further defining spaced apart low velocity flow sections located between said minimum throat areas and wherein said low velocity flow sections define a larger flowpath section that defined at said minimum throat areas.
An airfoil blade comprising:
- an airfoil body having a root portion, a tip portion, a leading edge, a trailing edge and an internal coolant passageway having opposed walls located within said blade, and
- shear jet flow means provided in said coolant passageway for directing coolant flow through said coolant passageway along said walls in a series of spaced apart, localized high velocity flow jets.
Dependencies are inferred from the claim text.