US 12,442,315 B2
Gas turbine engine
William Joseph Bowden, Cleves, OH (US); and Keith Edward James Blodgett, Milford, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Aug. 17, 2022, as Appl. No. 17/889,927.
Prior Publication US 2024/0060430 A1, Feb. 22, 2024
Int. Cl. F01D 25/24 (2006.01); F01D 25/28 (2006.01)
CPC F01D 25/24 (2013.01) [F01D 25/28 (2013.01); F05D 2220/323 (2013.01); F05D 2240/14 (2013.01); F05D 2250/38 (2013.01); F05D 2250/72 (2013.01); F05D 2260/30 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis, the gas turbine engine attachable to a wing via a pylon fairing and a gully distance defined between the wing and the gas turbine engine, the gas turbine engine comprising:
a fan rotatable about the longitudinal axis, wherein the fan is an unducted fan having fan blades rotatable about the longitudinal axis and fan guide vanes not rotatable about the longitudinal axis;
a turbomachine; and
a housing surrounding the turbomachine and comprising an upper outer surface portion and a lower outer surface portion,
at a corresponding axial position of the gully distance, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion,
at the corresponding axial position of the gully distance, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and
the second distance is greater than the first distance,
wherein the gas turbine engine includes a fan exhaust nozzle that has a first width along the first distance and a second width along the second distance, wherein the second width is greater than the first width; wherein the first point, the second point, and the gully distance are collinear with an exit plane of the fan exhaust nozzle; and wherein the gully distance is defined between a wing surface below a leading edge of the wing and the gas turbine engine.
 
10. An aircraft engine assembly comprising:
a wing;
a pylon fairing; and
a gas turbine engine attached to the wing via the pylon fairing and a gully distance defined between the wing and the gas turbine engine, wherein the wing, the gas turbine engine, and the pylon fairing together defining in part a gully area, the gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis, the gas turbine engine comprising:
a fan rotatable about the longitudinal axis, wherein the fan is an unducted fan having fan blades rotatable about the longitudinal axis and fan guide vanes not rotatable about the longitudinal axis;
a turbomachine; and
a housing surrounding the turbomachine and comprising an outer surface,
at a corresponding axial position of the gully distance, the housing defining a first distance between the longitudinal axis and a first point on the outer surface of the housing,
at the corresponding axial position of the gully distance, the housing further defining a second distance between the longitudinal axis and a second point on the outer surface of the housing, the first point closer to the gully area than the second point, the first distance and the second distance defined in a reference plane extending perpendicular to the longitudinal axis, and the second distance being greater than the first distance,
wherein the gas turbine engine includes a fan exhaust nozzle that has a first width along the first distance and a second width along the second distance, wherein the second width is greater than the first width; wherein the first point, the second point, and the gully distance are collinear with an exit plane of the fan exhaust nozzle; and wherein the gully distance is defined between a wing surface below a leading edge of the wing and the gas turbine engine.