IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0768585
(2010-04-27)
|
등록번호 |
US-8720815
(2014-05-13)
|
발명자
/ 주소 |
- Vetters, Daniel Kent
- Cedoz, Robert Wayne
- Eames, David
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
18 |
초록
▼
An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core en
An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core engine. The aircraft propulsion system also includes at least one free power turbine driven to rotate by exhaust gases exiting the turbine section. The aircraft propulsion system also includes at least one rotor module driven to rotate by at least one free power turbine. The aircraft propulsion system also includes first and second pylons extending away from the nacelle and operable to mount the core engine to an aircraft. The first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane.
대표청구항
▼
1. An aircraft propulsion system comprising: a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis;a nacelle surrounding said core engine;at least one free power turbine driven to rotate by exhaust gases exiting said turbine
1. An aircraft propulsion system comprising: a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis;a nacelle surrounding said core engine;at least one free power turbine driven to rotate by exhaust gases exiting said turbine section;at least one rotor module driven to rotate by said at least one free power turbine; andfirst and second pylons extending away from said nacelle and operable to mount said core engine to an aircraft, wherein said first and second pylons are spaced from one another on opposite sides of at least one plane containing said centerline axis and mirror one another across said at least one plane. 2. The aircraft propulsion system of claim 1 wherein said first and second pylons are substantially centered and extend in respective first and second longitudinal pylon planes and wherein said first and second longitudinal pylon planes intersect one another. 3. The aircraft propulsion system of claim 2 wherein said first and second longitudinal pylon planes intersect along an intersection line extending parallel to said centerline axis. 4. The aircraft propulsion system of claim 1 wherein each of said first and second pylons further comprise: a first beam having first and second ends wherein said first end of said first beam is mounted to said core engine at a first position along said centerline axis proximate to a composite center of gravity of said core engine, said nacelle, said at least one free power turbine, and said at least one rotor module. 5. The aircraft propulsion system of claim 4 wherein each of said first and second pylons further comprise: a second beam having first and second ends wherein said first end of said second beam is mounted to said core engine at said first position, wherein said respective second ends of said first beam and said second beam are spaced from one another along said centerline axis. 6. The aircraft propulsion system of claim 4 wherein each of said first and second pylons have a variable cross-sectional area, wherein each cross-sectional area is defined in a transverse pylon plane being normal to said respective longitudinal pylon plane. 7. The aircraft propulsion system of claim 6 wherein each of said first and second pylons have a smallest cross-sectional area proximate to said first end of said first beam. 8. The aircraft propulsion system of claim 4 wherein each of said first and second pylons further comprise: a second beam having first and second ends wherein said first end of said second beam is mounted to said core engine at a second position along said centerline axis spaced closer to said intake than said first position; anda third beam having first and second ends wherein said first end of said third beam is mounted to said core engine at said first position, wherein said respective first ends of said first beam and said third beam are proximate to one another and said respective second ends of said second beam and said third beam are proximate to one another. 9. An aircraft propulsion system comprising: a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis;a nacelle surrounding said core engine;at least one free power turbine driven to rotate by exhaust gases exiting said turbine section;at least one rotor module driven to rotate by said at least one free power turbine; andfirst and second pylons extending away from said nacelle and operable to mount said core engine to an aircraft, wherein said first and second pylons are spaced from one another on opposite sides of at least one plane containing said centerline axis and mirror one another across said at least one plane; anda third pylon disposed between said first and second pylons relative to a circumferential perimeter of said nacelle, wherein said first and second pylons are mounted to said core engine at a first position along said centerline axis and said third pylon is mounted to said core engine at a second position along said centerline axis spaced from the first position. 10. The aircraft propulsion system of claim 9 wherein a central axis of said third pylon is coplanar with said centerline axis and not coplanar with respective central axes of both of said first and second pylons. 11. The aircraft propulsion system of claim 9 wherein said third pylon extends between first and second ends wherein said first end is mounted to said core engine at said second position along said centerline axis and wherein said second end is moveable to change an orientation of said centerline axis relative to said first and second pylons. 12. The aircraft propulsion system of claim 1 wherein said rotor module is disposed in one of a pusher and tractor configuration relative said core engine. 13. The aircraft propulsion system of claim 1 wherein said rotor module further comprises a pair of counter-rotating rotors. 14. A method comprising the steps of: arranging an intake, a compressor section, a combustor section, and a turbine section of a core engine along a centerline axis;surrounding the core engine with a nacelle;positioning at least one free power turbine to be driven to rotate by exhaust gases exiting the turbine section;driving at least one rotor module to rotate with the at least one free power turbine; andextending first and second pylons away from the nacelle each being operable to mount the core engine to an aircraft, wherein the first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane. 15. A method comprising the steps of: arranging an intake, a compressor section, a combustor section, and a turbine section of a core engine along a centerline axis;surrounding the core engine with a nacelle;positioning at least one free power turbine to be driven to rotate by exhaust gases exiting the turbine section;driving at least one rotor module to rotate with the at least one free power turbine;extending first and second pylons away from the nacelle each being operable to mount the core engine to an aircraft, wherein the first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane; andpivotally mounting the core engine to the first and second pylons. 16. The method of claim 15 further comprising the step of: pivotally mounting the core engine to a third pylon disposed between the first and second pylons relative to a circumferential perimeter of the nacelle, wherein the first and second pylons are mounted to the core engine at a first position along the centerline axis and the third pylon is mounted to the core engine at a second position along the centerline axis spaced from the first position. 17. The method of claim 16 further comprising the step of: moving an end of the third pylon spaced from the core engine to shift the position of the rotor module. 18. An aircraft propulsion system comprising: a plurality of core engines, each core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a respective centerline axis;a plurality of nacelles, each nacelle surrounding one of said plurality of core engines;a plurality of free power turbines, each free power turbine driven to rotate by exhaust gases exiting said turbine section;a plurality of rotor modules, each rotor module driven to rotate by one of said plurality of free power turbines;first and second pylons extending away from at least one of said plurality of nacelles and operable to mount said respective core engine to an aircraft, wherein said first and second pylons are spaced from one another on opposite sides of at least one plane containing said respective centerline axis of said respective core engine and mirror one another across said at least one plane; anda cross-member extending between a first of said nacelles and a second of said nacelles. 19. An aircraft propulsion system comprising: a plurality of core engines, each core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a respective centerline axis;a plurality of nacelles, each nacelle surrounding one of said plurality of core engines;a plurality of free power turbines, each free power turbine driven to rotate by exhaust gases exiting said turbine section;a plurality of rotor modules, each rotor module driven to rotate by one of said plurality of free power turbines; andfirst and second pylons extending away from at least one of said plurality of nacelles and operable to mount said respective core engine to an aircraft, wherein said first and second pylons are spaced from one another on opposite sides of at least one plane containing said respective centerline axis of said respective core engine and mirror one another across said at least one plane, wherein said first and second pylons extend away from a first nacelle of said plurality of nacelles and wherein a third pylon alone extends from a second nacelle of said plurality of nacelles, said first and second nacelles adjacent to one another. 20. The aircraft propulsion system of claim 19 further comprising: a cross-member extending between said first and second nacelles. 21. The aircraft propulsion system of claim 1 wherein said at least one rotor module comprises an open rotor including a hub portion and a plurality of propeller blades extending radially from said hub portion and outwardly beyond said nacelle to thereby define an open rotor propulsion system. 22. The aircraft propulsion system of claim 1 wherein said first and second pylons extend from said nacelle to an outer surface of said aircraft; and wherein said rotor module includes a plurality of blades extending radially outward beyond said nacelle and having blade tips that are spaced radially from said outer surface. 23. The method of claim 14 further comprising providing an open rotor propulsion system wherein the at least one rotor module comprises an open rotor including a hub portion and a plurality of propeller blades extending radially from the hub portion and outwardly beyond the nacelle. 24. The method of claim 14 wherein the first and second pylons extend from said nacelle to an outer surface of the aircraft; and wherein the rotor module includes a plurality of blades extending radially outward beyond the nacelle and having blade tips that are spaced radially from the outer surface. 25. The aircraft propulsion system of claim 1 wherein said first and second pylons are pivotally mounted to said core engine. 26. The aircraft propulsion system of claim 1 wherein each of said first and second pylons include opposite engine mount ends spaced from one another along said centerline axis, said first engine mount end mounted to said core engine at a first position along said centerline axis proximate to a composite center of gravity of said core engine, said nacelle, said at least one free power turbine, and said at least one rotor module. 27. The method of claim 14 wherein each of said first and second pylons include opposite engine mount ends spaced from one another along the centerline axis; and mounting the first engine mount end of the first and second pylons to the core engine at a first position along the centerline axis proximate to a composite center of gravity of the core engine, the nacelle, the at least one free power turbine, and the at least one rotor module. 28. The aircraft propulsion system of claim 18 wherein said cross-member extends from a first of said core engines surrounded by said first nacelle to a second of said core engines surrounded by said second nacelle.
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