US 11,788,419 B1
Airfoil leading edge venturi cooling passage
Jonas Banhos, West Hartford, CT (US); Ravon Venters, Farmington, CT (US); Russell Kim, Temecula, CA (US); Raymond Surace, Newington, CT (US); and James T. Roach, Vernon, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Aug. 15, 2022, as Appl. No. 17/887,870.
Int. Cl. F01D 5/18 (2006.01); F01D 5/28 (2006.01)
CPC F01D 5/187 (2013.01) [F01D 5/282 (2013.01); F01D 5/284 (2013.01); F05D 2240/121 (2013.01); F05D 2240/303 (2013.01); F05D 2300/6033 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A ceramic matrix composite airfoil comprising:
a high-pressure surface and a low-pressure surface connected at a leading edge and a trailing edge, wherein the high-pressure surface and the low-pressure surface extend from a first end to a second end; and
a leading edge cooling passage defined between a forward wall that defines the leading edge and a forward rib, the leading edge cooling passage including an inlet portion, a midspan portion and an outlet portion wherein a cross-sectional flow area of the midspan portion is less than a cross-sectional flow area of either the inlet portion or the outlet portion, wherein the forward rib includes end wall portions disposed on either end of a middle wall portion that are angled away from the middle wall portion toward the trailing edge at each of the inlet portion and the outlet portion of the leading edge cooling passage.