US 12,065,258 B2
Multiple intake distortion adaptive fan for gas turbine engine
Robert W. Heeter, Indianapolis, IN (US); Daniel E. Molnar, Jr., Indianapolis, IN (US); Kathryn A. Sontag, Indianapolis, IN (US); and Michael G. Meyer, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies Inc., Indianapolis, IN (US); and Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on Jan. 25, 2023, as Appl. No. 18/101,567.
Prior Publication US 2024/0246688 A1, Jul. 25, 2024
Int. Cl. B64D 33/02 (2006.01)
CPC B64D 33/02 (2013.01) [B64D 2033/0226 (2013.01); B64D 2033/0286 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft comprising
a duct system configured to receive a flow of air therethrough, the duct system including a main duct, a first inlet duct in fluid communication with the main duct, and a second inlet duct in fluid communication with the main duct, the first inlet duct and the second inlet duct each being arranged fluidly upstream of the main duct so as to conduct the flow of air from the first inlet duct and the second inlet duct into the main duct,
a gas turbine engine in downstream fluid communication with the main duct, the gas turbine engine including a primary fan configured push air to provide thrust for the gas turbine engine, a compressor configured to rotate about an axis of the gas turbine engine to compress at least a portion of the air that flows from the primary fan, a combustor configured to receive the compressed air from the compressor, and a turbine coupled to the compressor and configured to rotate about the axis of the gas turbine engine in response to receiving hot, high-pressure products of the combustor to drive the compressor, and
an inlet distortion mitigation system including a plurality of auxiliary inlet fans having a first electric inlet fan arranged in the first inlet duct, a second electric inlet fan arranged in the second inlet duct, and a control unit configured to vary individually a rotation speed of each of the first electric inlet fan and the second electric inlet fan in response to a pressure differential in the flow path of the gas turbine engine to increase flow distribution uniformity at the primary fan of the gas turbine engine.