Internally cooled airfoil
AssigneePratt & Whitney Canada Corp.
InventorMICHAEL PAPPLE
Life of this patent
Estimating the term…
Abstract
An internally cooled airfoil for a gas turbine engine has a hollow airfoil body including pressure and suction sidewalls defining a cooling passage therebetween. A combination of pedestal and trip-strips are used in the cooling passage to enhance heat transfer while minimizing the coolant pressure drop across these features.
Claims20
An internally cooled airfoil for a gas turbine engine, comprising a hollow airfoil body having opposed pressure and suction sidewalls defining therebetween a cooling passage, and a plurality of pedestals extending across said cooling passage from said pressure sidewall to said suction sidewall, wherein at least some of said pedestals have a trip-strip portion projecting laterally therefrom a distance less than the distance between two adjacent pedestals.
An internally cooled airfoil for a gas turbine engine, comprising a hollow airfoil body having opposed pressure and suction sidewalls defining therebetween a cooling passage, a plurality of pedestals staggered in a trailing edge region of the cooling passage and extending from said pressure sidewall to said suction sidewall, and a plurality of trip-strips provided on an inner surface of at least one of said pressure and suctions sidewalls, each of said trip-strips having a proximal end attached to an associated one of said pedestals and a distal end spaced-apart from adjacent pedestals.
A gas turbine engine component comprising a surface to be cooled by a flow of coolant, a plurality of pedestals staggered on said surface, and a plurality of trip-strips provided on said surface, each of said trip-strips having a proximal end attached to an associated one of said pedestals and a distal end spaced-apart from adjacent pedestals.
Dependencies are inferred from the claim text.