Granted Patent B2

US 12,441,475 · App. 17/085,184 · Granted Oct 14, 2025

Inventors: Robert E. Malecki (Storrs, CT); Andrew Hahn (Yorktown, VA); Marc J. Muldoon (Marlborough, CT); Jesse M. Chandler (South Windsor, CT); Joseph B. Staubach (Colchester, CT)

Assignee: RTX Corporation

B64D27/12B64C7/02B64D27/02B64D29/06B64D29/08F02C7/06F02C7/14F02C7/20F02C7/32F05D2220/323F05D2230/72F05D2260/213F05D2260/4031F05D2260/98

Abstract

Claims (23)

1. A gas turbine engine and engine mount structure comprising:

a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing;

a fan, said fan having at least one fan rotor, said compressor section having at least one compressor rotor and said turbine section having at least one turbine rotor, said at least one fan rotor, said at least one compressor rotor and said at least one turbine rotor for rotating about an axis of rotation;

an outer nacelle surrounding said fan, and being spaced from said core engine housing to define a bypass duct, said fan delivering air into said bypass duct and into said core engine housing; and

said outer nacelle being formed with camber, such that a center point of the nacelle is not formed on a straight line parallel relative to the axis of rotation, but so as to be curved, with the curve being in a first plane away from said axis of rotation in a first lateral direction, and an engine mount structure extending from said nacelle at an angle that is non-parallel and non-perpendicular to said first plane, and the angle having a component in a lateral direction that is opposite to said first lateral direction.

2. The gas turbine engine and engine mount structure as set forth in claim 1 , wherein said angle defined away from said first plane, and said angle being between 30 and 50 degrees.

3. The gas turbine engine and engine mount structure as set forth in claim 2 , wherein said first plane will be parallel to a horizontal when the gas turbine engine and engine mount structure is mounted on an aircraft.

4. The gas turbine engine and engine mount structure as set forth in claim 2 , wherein said outer nacelle including D-doors which can be pivoted outwardly away from said core housing to provide access to inside said engine.

5. The gas turbine engine and engine mount structure as set forth in claim 4 , wherein at least one of said D-doors has an attachment that provides a support for maintenance workers when said D-doors are in an open position.

6. The gas turbine engine and engine mount structure as set forth in claim 4 , wherein a second plane is defined perpendicular to said first plane and also extending through said axis of rotation, and said engine mount structure being on one side of said second plane and an auxiliary gearbox driven by said turbine section is positioned on a second side of said second plane.

7. The gas turbine engine and engine mount structure as set forth in claim 6 , wherein an oil tank is also mounted in said opposed side.

8. The gas turbine engine and engine mount structure as set forth in claim 7 , wherein a pre-cooler is provided in a side of said second plane from which engine mount structure extends.

9. The gas turbine engine and engine mount structure as set forth in claim 4 , wherein said outer nacelle is formed to be non-perpendicular to said axis of rotation at a trailing edge plane of said outer nacelle.

10. The gas turbine engine and engine mount structure as set forth in claim 4 , wherein said outer nacelle is formed to be perpendicular to said axis of rotation at a trailing edge plane of said outer nacelle.

11. The gas turbine engine and engine mount structure as set forth in claim 1 , wherein said outer nacelle including D-doors which can be pivoted outwardly away from said core housing to provide access to inside said engine.

12. The gas turbine engine and engine mount structure as set forth in claim 11 , wherein at least one of said D-doors has an attachment that provides a support for maintenance workers when said D-doors are in an open position.

13. The gas turbine engine and engine mount structure as set forth in claim 11 , wherein a second plane is defined perpendicular to said first plane and also extending through said axis of rotation, and said engine mount structure being on one side of said second plane and an auxiliary gearbox driven by said turbine section is positioned on a second side of said second plane.

14. The gas turbine engine and engine mount structure as set forth in claim 13 , wherein an oil tank is also mounted in said opposed side.

15. The gas turbine engine and engine mount structure as set forth in claim 11 , wherein said outer nacelle is formed to be non-perpendicular to said axis of rotation at a trailing edge plane of said outer nacelle.

16. The gas turbine engine and engine mount structure as set forth in claim 1 , wherein a second plane is defined perpendicular to said first plane and also extending through said axis of rotation, and said engine mount structure being on one side of said second plane and an auxiliary gearbox driven by said turbine section is positioned on a second side of said second plane.

17. The gas turbine engine and engine mount structure as set forth in claim 16 , wherein a pre-cooler is provided in a side of said second plane from which engine mount structure extends.

18. The gas turbine engine and engine mount structure as set forth in claim 1 , wherein said outer nacelle is formed to be non-perpendicular to said axis of rotation at a trailing edge plane of said outer nacelle.

19. The gas turbine engine and engine mount structure as set forth in claim 1 , wherein said outer nacelle is formed to be perpendicular to said axis of rotation at a trailing edge plane of said outer nacelle.

Assignments (2)

Continuity (1)

References Cited (29)