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US 2023/0399114 A1Published application
Aircraft with a fuselage accommodating an unducted turbine engine
AssigneeGeneral Electric Company
InventorsKeith Edward James Blodgett, William J. Bowden, Egbert Geertsema
Life of this patent
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Abstract
An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h/L.
Claims20
An aircraft comprising:
- a fuselage defining a fuselage centerline, the fuselage comprising:
- a divot having an upstream edge and a downstream edge axially aft of the upstream edge with respect to the fuselage centerline;
- wherein the divot is defined by a straight reference line connecting the upstream edge and the downstream edge, with the straight reference line extending a length (L), and the divot having a maximum depth (h) relative to the straight reference line;
- and
- an unducted turbine engine operably coupled to the fuselage, the unducted turbine engine comprising:
- an engine core defining an engine centerline;
- a nacelle circumscribing at least a portion of the engine core;
- and
- a set of blades operably coupled to at least a portion of the engine core, the set of blades having an axially forwardmost point and wherein the set of blades defining a swept area defining a circle having a diameter (D);
- wherein a first flow ratio (FR1) of the aircraft is equal to:h/L, and
- wherein the first flow ratio (FR1) is greater than or equal to 0.01 and less than or equal to 0.15 (0.01≤FR1≤0.15).
8 more elements
An aircraft comprising:
- a fuselage defining a fuselage centerline;
- a tail wing coupled to the fuselage and having a leading edge, with an axially forwardmost point relative to the fuselage centerline;
- an unducted turbine engine operably coupled to the fuselage, the unducted turbine engine comprising:
- an engine core defining an engine centerline;
- a nacelle circumscribing at least a portion of the engine core;
- and
- a set of blades operably coupled to at least a portion of the engine core, the set of blades having an axially forwardmost point;
- wherein the set of blades define a swept area defining a circle having a diameter (D);
- wherein a second distance (x2) is a distance along a line parallel to the fuselage centerline between the axially forwardmost point of the leading edge of the tail wing and the axially forwardmost point of the set of blades;
- wherein a flow ratio (FR4) is equal to:
- x
-
- 2
- D
- ;
- and
- wherein the flow ratio (FR4) is greater than or equal to 0.5 and less than or equal to 2 (0.5≤FR4≤2).
14 more elements
Dependencies are inferred from the claim text.