Granted Patent B2

US 12,377,954 · App. 17/826,276 · Granted Aug 5, 2025

Inventors: Kishore Ramakrishnan (Rexford, NY); Shourya Otta (Niskayuna, NY); Trevor Wood (Clifton Park, NY)

Assignee: General Electric Company

B64C1/40B64D27/14B64C2220/00B64D27/00B64D27/20

Abstract

Claims (43)

1. An aircraft comprising:

a fuselage defining a longitudinal centerline, an aft end, and a forward end located axially forward of the aft end;

an aircraft body having an outer surface and a pair of wings extending radially outward from the fuselage, with respect to the longitudinal centerline;

at least one aircraft engine system defining an axial centerline and having a nacelle and at least one rotatable propeller configured to rotate about the axial centerline, the at least one rotatable propeller extending between a free end and a base end, with the free end being spaced radially outward from the nacelle with respect to the axial centerline, the at least one aircraft engine system being located axially closer to the pair of the wings, with respect to the longitudinal centerline, than to the aft end and the forward end; and

a feature provided along a portion of the aircraft body and defining a respective portion of the outer surface, the feature being shaped to alter a flow of air between the aircraft body and the at least one rotatable propeller, the feature having a continuous contour when viewed along a vertical plane perpendicular to the longitudinal centerline and intersecting the feature;

wherein the feature forms one of either:

a depression along the aircraft body such that the continuous contour is concave with respect to the aircraft body when viewed along a horizontal plane extending along the longitudinal centerline and intersecting the feature; or

a bump along the aircraft body such that the continuous contour is convex with respect to the aircraft body when viewed along the horizontal plane extending along the longitudinal centerline and intersecting the feature;

wherein the at least one rotatable propeller is axially aligned, with respect to the axial centerline, with a respective portion of the feature.

2. The aircraft of claim 1 , wherein the aircraft body is one of the fuselage, the nacelle or a pylon operably coupled to the at least one aircraft engine system.

3. The aircraft of claim 1 , wherein the feature comprises:

a fore edge; and

an aft edge axially downstream of the fore edge with respect to the longitudinal centerline;

wherein a straight reference line is formed between the fore edge and the aft edge of the feature;

wherein the at least one rotatable propeller is provided a first distance between the fore edge and a propeller plane perpendicular to the axial centerline and intersecting the at least one rotatable propeller, and a second distance between the aft edge and the propeller plane; and

wherein the feature extends a height defined by a line perpendicular to the straight reference line and intersecting the feature, and the feature having a maximum height relative to the straight reference line.

4. The aircraft of claim 3 , wherein the first distance is larger than the second distance.

5. The aircraft of claim 3 , wherein the at least one rotatable propeller is aft of the maximum height with respect to the longitudinal centerline.

6. The aircraft of claim 3 , wherein the maximum height is provided along the first distance.

7. The aircraft of claim 3 , wherein the maximum height is provided along the second distance.

8. The aircraft of claim 3 , wherein the straight reference line is parallel to the longitudinal centerline.

9. The aircraft of claim 3 , wherein the maximum height is axially offset from the vertical plane.

10. The aircraft of claim 1 , wherein at least a portion of the feature is configured to dynamically change during operation of the aircraft.

11. The aircraft of claim 10 , wherein the feature further comprises a first surface and a second surface, wherein the first surface and the second surface each dynamically change during operation of the aircraft during operation the aircraft.

12. The aircraft of claim 1 , wherein the feature is one of either integrally formed with the aircraft body or retrofittable to the aircraft body.

13. The aircraft of claim 1 , wherein an altering of the flow of air results in at least one of a reduction in a local load on the at least one rotatable propeller or a reduction in a local angle of attack of the at least one rotatable propeller relative to the aircraft body not including the feature.

14. The aircraft of claim 13 , wherein reducing the local angle of attack of the at least one rotatable propeller reduces an angle of attack distortion on the at least one rotatable propeller relative to the aircraft body not including the feature.

15. The aircraft of claim 1 , wherein an altering of the flow of air results in a reduction in a noise level associated with an operation of the at least one aircraft engine system relative to the aircraft body not including the feature.

16. An aircraft comprising:

a fuselage defining a longitudinal centerline;

an aircraft body;

at least one aircraft engine system defining an axial centerline and having a nacelle and at least one rotatable propeller configured to rotate about the axial centerline, the at least one rotatable propeller extending between a free end and a base end, with the free end being spaced radially outward from the nacelle with respect to the axial centerline; and

a feature provided along a portion of the aircraft body, the feature having a cross-sectional area when viewed along a horizontal plane extending along the longitudinal centerline and intersecting the feature, the cross-sectional area defining one of either a depression extending radially toward the longitudinal centerline or a bump extending radially away from the longitudinal centerline, the feature having a continuous contour when viewed along a vertical plane perpendicular to the longitudinal centerline and intersecting the feature;

wherein the cross-sectional area of the feature is configured to dynamically change between at least a first shape during a first operation of the aircraft, and a second shape, different from the first shape, during a second operation of the aircraft; and

wherein the rotatable propeller is axially aligned, with respect to the axial centerline, with a respective portion of the feature.

17. The aircraft of claim 16 , wherein the aircraft body is one of the fuselage, the nacelle or a pylon operably coupled to the at least one aircraft engine system.

18. The aircraft of claim 16 , wherein the feature includes a first surface and a second surface, and wherein the first surface and the second surface each dynamically change during operation of the aircraft independently of one another.

19. The aircraft of claim 16 , further comprising a controller is configured to automatically dynamically change the feature during operation of the aircraft.

20. An aircraft comprising:

a fuselage defining a longitudinal centerline;

at least one aircraft engine system defining an axial centerline and having a nacelle and at least one rotatable propeller configured to rotate about the axial centerline, the at least one rotatable propeller extending between a free end and a base end, with the free end being spaced radially outward from the nacelle with respect to the axial centerline; and

a feature provided along a portion of the fuselage and extending radially toward or radially away from the longitudinal centerline and having a continuous contour when viewed along a vertical plane perpendicular to the longitudinal centerline and intersecting the feature;

wherein a shape of the feature is configured to dynamically change during operation of the aircraft.

Assignments (1)

Continuity (2)

References Cited (68)