US 12,215,621 B1
Heat exchanger inlet vane assemblies with improved mixing trailing edge features
Kerry J. Lighty, Plainfield, IN (US); William Williamson, Indianapolis, IN (US); Luke Dillard, Indianapolis, IN (US); and David Templin, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed on Jul. 31, 2023, as Appl. No. 18/228,266.
Int. Cl. F02C 7/141 (2006.01)
CPC F02C 7/141 (2013.01) [F05D 2240/12 (2013.01); F05D 2250/18 (2013.01); F05D 2260/213 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a heat exchanger configured to transfer heat from a cooling fluid passing through the heat exchanger to a flow of air received by the heat exchanger, and
an inlet shroud configured to be coupled with the heat exchanger upstream of the heat exchanger, the inlet shroud including a vane frame and a plurality of inlet turning vanes coupled with the vane frame and configured to direct the flow of air into the heat exchanger, the vane frame having a first side wall and a second side wall spaced apart from and opposite the first side wall, the first side wall and the second side wall are both formed to include a first slot having a first chord length and a second slot neighboring the first slot and having a second chord length different from the first chord length, and the plurality of inlet turning vanes located in the vane frame and configured to adjust a direction of the flow of air before the flow of air enters the heat exchanger,
wherein the plurality of inlet turning vanes includes a first inlet vane and a second inlet vane, the first inlet vane including a first airfoil body having a third chord length, a first tab extending from a first end of the first airfoil body and into the first slot of the first side wall, and a second tab extending from a second end of the first airfoil body and into the first slot of the second side wall, and the second inlet vane including a second airfoil body having the third chord length, a third tab extending from a first end of the second airfoil body and into the second slot of the first side wall, and a fourth tab extending from a second end of the second airfoil body and into the second slot of the second side wall.