US 12,188,408 B1
Inlet turning vanes having trailing edge features for improved flow uniformity
Scott Schwenker, 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. 18/228,268.
Int. Cl. F02C 7/18 (2006.01); F01D 25/12 (2006.01); F02C 7/04 (2006.01); F02C 9/18 (2006.01)
CPC F02C 7/04 (2013.01) [F01D 25/12 (2013.01); F02C 7/18 (2013.01); F02C 9/18 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a bypass duct configured to direct air through a flow path to provide thrust to propel the gas turbine engine, the bypass duct including an outer wall that defines an outer boundary of the flow path and an inner wall that defines an inner boundary of the flow path,
a heat exchanger configured to receive a portion of the air flowing through the flow path of the bypass duct and to transfer heat from a cooling fluid passing through the heat exchanger to the portion of the air, and
an inlet shroud coupled with the heat exchanger and configured to adjust a direction of the portion of the air entering the heat exchanger, the inlet shroud including a vane frame coupled with the heat exchanger and a plurality of inlet turning vanes coupled with the vane frame, each of the plurality of inlet turning vanes having a leading edge, a trailing edge, a pressure side extending between the leading edge and the trailing edge, and a suction side extending between the leading edge and the trailing edge on an opposing side of each of the plurality of inlet turning vanes,
wherein the trailing edge of each of the plurality of inlet turning vanes is formed to include notches that extend into the trailing edge toward the leading edge so that a first part of the air flowing on the pressure side of each of the plurality of inlet turning vanes flows through the notches and mixes with a second part of the air flowing on the suction side of each of the plurality of inlet turning vanes to increase uniformity of a velocity profile of the portion of the air exiting the inlet shroud and entering the heat exchanger,
wherein the plurality of inlet turning vanes includes a first inlet vane and a second inlet vane located adjacent the first inlet vane, and the notches formed in the trailing edge of the first inlet vane are offset in a spanwise direction relative to the notches formed in the trailing edge of the second inlet vane.