US 11,988,140 B2
Gas turbine engine inlet wall design
Dmytro Mykolayovych Voytovych, Rocky Hill, CT (US); and Om P. Sharma, South Windsor, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jan. 12, 2021, as Appl. No. 17/147,129.
Application 17/147,129 is a division of application No. 14/665,081, filed on Mar. 23, 2015, granted, now 10,907,544.
Claims priority of provisional application 61/971,037, filed on Mar. 27, 2014.
Prior Publication US 2021/0388761 A1, Dec. 16, 2021
Int. Cl. F02C 7/04 (2006.01); B64C 39/10 (2006.01); B64D 27/00 (2006.01); B64D 27/14 (2006.01); B64D 33/02 (2006.01); F01D 5/02 (2006.01)
CPC F02C 7/04 (2013.01) [B64D 27/00 (2013.01); B64D 27/14 (2013.01); B64D 33/02 (2013.01); F01D 5/02 (2013.01); B64C 2039/105 (2013.01); B64D 2033/0253 (2013.01); F05D 2250/14 (2013.01); F05D 2250/312 (2013.01); Y02T 50/10 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A blended wing aircraft comprising:
a blended wing fuselage and at least one embedded gas turbine engine in the fuselage; and
the gas turbine engine including an inlet duct formed with a generally elliptical shape includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct, wherein the inlet duct includes a vertical centerline and the first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections and the area of the second set of ellipse sections increases toward a downstream end of the inlet duct and a fan section having an axis of rotation, wherein the axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice and the inlet duct is upstream of the fan section.