US 9,810,147 B2
Angled inlet system for a precooler
Paul R. Tretow, Mukilteo, WA (US); Robert Henry Willie, Bothell, WA (US); and Donald Edwin Robinson, Mercer Island, WA (US)
Assigned to THE BOEING COMPANY, Chicago, IL (US)
Filed by The Boeing Company, Chicago, IL (US)
Filed on Oct. 31, 2013, as Appl. No. 14/68,403.
Prior Publication US 2015/0113999 A1, Apr. 30, 2015
Int. Cl. F02C 7/04 (2006.01); F02C 6/08 (2006.01); B64D 13/06 (2006.01); F02C 6/04 (2006.01); F02C 7/18 (2006.01); B64D 13/02 (2006.01)
CPC F02C 7/04 (2013.01) [B64D 13/06 (2013.01); F02C 6/04 (2013.01); F02C 6/08 (2013.01); F02C 7/18 (2013.01); B64D 13/02 (2013.01); B64D 2241/00 (2013.01); F05D 2250/51 (2013.01); F05D 2260/213 (2013.01); Y02T 50/676 (2013.01); Y10T 137/0536 (2015.04)] 18 Claims
OG exemplary drawing
 
16. A method for improving performance of an engine system, the method comprising:
creating an air flow through a fan duct in the engine system; and
positioning a leading edge of an inlet in a bifurcation surface downstream of a leading edge of a bifurcation of the fan duct such that the leading edge is swept at a first angle relative to a first normal axis of the engine system such that an upper portion at an upper end of the leading edge is downstream relative to a lower portion at a lower end of the leading edge relative to a flow direction of the air flow, and such that the leading edge is swept at a second angle relative to a second normal axis that is substantially normal to the first normal axis and is substantially normal to the flow direction of the air flow such that the upper portion at the upper end is offset along the second normal axis relative to the lower portion at the lower end, wherein the first normal axis extends radially outward from a center axis of the engine system and is substantially normal to the flow direction of the air flow through the engine system, and wherein the leading edge extends linearly from the upper end to the lower end along a length of the leading edge.