US 11,725,530 B1
Offtake scoops for bleed pressure recovery in gas turbine engines
Sesha Subramanian, Bengaluru (IN); Scott Alan Schimmels, Evendale, OH (US); Jeffrey D. Carnes, Lynn, MA (US); and Vishnu Das K, Bengaluru (IN)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on May 20, 2022, as Appl. No. 17/749,929.
Int. Cl. F01D 9/06 (2006.01); F01D 9/04 (2006.01); F01D 5/14 (2006.01); F01D 25/24 (2006.01)
CPC F01D 9/065 (2013.01) [F01D 5/145 (2013.01); F01D 9/041 (2013.01); F01D 25/24 (2013.01); F05D 2240/126 (2013.01); F05D 2240/60 (2013.01); F05D 2260/606 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor including a casing defining a passageway;
a shaft extending through the passageway, the shaft drivingly coupling the compressor and a turbine of the gas turbine engine, the shaft having an opening to receive airflow from the passageway;
an inner shroud;
stator vanes coupled to and extending radially between the casing and the inner shroud; and
an offtake scoop disposed on a downstream side of the inner shroud, the offtake scoop having a channel to direct the airflow radially inward toward the opening in the shaft, the offtake scoop including an upstream wall, a downstream wall spaced apart from the upstream wall, and a rib extending between the upstream wall and the downstream wall, the channel defined between the upstream and downstream walls, the rib cantilevered from the upstream wall, the downstream wall cantilevered from an aft end of the rib such that the rib supports the downstream wall axially downstream of the upstream wall.