US 9,810,071 B2
Internally cooled airfoil
Michael Papple, Verdun (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Sep. 27, 2013, as Appl. No. 14/39,181.
Prior Publication US 2015/0093252 A1, Apr. 2, 2015
Int. Cl. F01D 5/18 (2006.01); F01D 9/06 (2006.01)
CPC F01D 5/18 (2013.01) [F01D 9/065 (2013.01); F01D 5/189 (2013.01); F05D 2250/241 (2013.01); F05D 2260/2212 (2013.01); F05D 2260/22141 (2013.01)] 18 Claims
OG exemplary drawing
 
1. 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.