Internally cooled airfoil
AssigneePratt & Whitney Canada Corp.
InventorMichael Papple
Life of this patent
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Abstract
An internally cooled airfoil for a gas turbine engine has a hollow airfoil body defining a core cavity. An insert is mounted in the core cavity. A cooling gap is provided between the insert and the hollow airfoil body. A plurality of standoffs project across the cooling gap. Trip-strips projecting laterally between adjacent standoffs. The trip-strips and the standoffs may be integrated into a unitary heat transfer feature.
Claims18
An internally cooled airfoil for a gas turbine engine, comprising a hollow airfoil body including a pressure sidewall and a suction sidewall extending chordwise from a leading edge to a trailing edge, the pressure and suction sidewalls having an internal surface bounding a core cavity, an insert mounted in the core cavity in spaced-apart relationship with said internal surface to define a cooling gap therewith, and a plurality of standoffs projecting from said internal surface of said pressure and suction sidewalls into the cooling gap toward the insert, a plurality of trip-strips projecting from said internal surface of the pressure and suction sidewalls, the trip-strips being intersperse between adjacent standoffs and extending laterally with respect thereto, wherein the plurality of standoffs include standoffs in a mid-chord area of the pressure and suction sidewalls, the trip-strips intersecting the standoffs in the mid-chord area.
An internally cooled turbine vane comprising a hollow airfoil body defining a core cavity, an insert mounted in the core cavity, a cooling gap between the insert and pressure and suction sidewalls of the hollow airfoil body, a plurality of standoffs projecting across the cooling gap, and trip-strips projecting laterally between adjacent standoffs and only partway through the cooling gap between the insert and the pressure and suction sidewalls of the hollow airfoil body, the plurality of standoffs being distributed over an internal surface of the pressure and suction sidewalls, and including standoffs in a mid-chord area of the pressure and the suction sidewalls, the trip-strips intersecting the standoffs in the mid-chord area.
Dependencies are inferred from the claim text.