[미국특허]
Balanced turbine rotor fan blade for a tip turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/18
F01D-005/22
출원번호
US-0719952
(2004-12-01)
등록번호
US-8807936
(2014-08-19)
국제출원번호
PCT/US2004/040124
(2004-12-01)
§371/§102 date
20071201
(20071201)
국제공개번호
WO2006/059996
(2006-06-08)
발명자
/ 주소
Nordeen, Craig A.
Suciu, Gabriel L.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
72
초록▼
A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section, a hollow fan blade section and a diffuser section. The hollow fan blade section defines an airflow passage. The core airflow is turned, spread and split toward opposite ends of
A fan-turbine rotor assembly for a tip turbine engine includes a multiple of fan blades, which include an inducer section, a hollow fan blade section and a diffuser section. The hollow fan blade section defines an airflow passage. The core airflow is turned, spread and split toward opposite ends of the diffuser section by a multiple of internal turning vanes. The airflow streams are then further turned by discharge turning vanes before discharge from a diffuser discharge outlet. Along with turning and splitting the core airflow, the fan blade profile balances the mass of the diffuser section such that the center of mass thereof is over the hollow airfoil section structure.
대표청구항▼
1. A fan blade comprising: an airfoil section for rotation about an axis of rotation which defines an airflow passage therethrough, said airflow passage having an inducer section to receive an airflow from a first axial direction and turn said airflow to a radial direction;a diffuser section, within
1. A fan blade comprising: an airfoil section for rotation about an axis of rotation which defines an airflow passage therethrough, said airflow passage having an inducer section to receive an airflow from a first axial direction and turn said airflow to a radial direction;a diffuser section, within which air is diffused in communication with said airflow passage, wherein said diffuser section is radially outboard of said airfoil section, said diffuser section having a diffuser section center of mass positioned directly over said airfoil section, said diffuser section oriented to turn and split said airflow from said radial direction to a second axial direction, said second axial direction being substantially opposite said first axial direction; anda turning vane within said diffuser section, said turning vane within said diffuser section turning said airflow from a radial direction to said second axial direction. 2. The fan blade as recited in claim 1, wherein said diffuser section center of mass does not overhang said airfoil section. 3. The fan blade assembly as recited in claim 1, wherein said turning vane has a relatively flat leading edge and a V-shape trailing edge. 4. The fan blade assembly as recited in claim 3, wherein said turning vane transits said diffuser section along an arcuate path. 5. The fan blade assembly as recited in claim 3, wherein said V-shape trailing edge intersects a diffuser upper surface of said diffuser section. 6. The fan blade assembly as recited in claim 1, wherein said turning vane has a first and second longitudinal side each side of which is progressively folded inward toward a centerline of said turning vane such that a trailing edge of said turning vane forms a V-shape where said trailing edge intersects with an upper surface of said diffuser section. 7. The fan blade as recited in claim 1, wherein said airfoil section and said diffuser section form a whale tail shape. 8. The fan blade as recited in claim 1, further comprising a discharge turning vane within said diffuser section adjacent a diffuser discharge outlet. 9. The fan blade as recited in claim 1, further comprising a rib formed within said airflow passage within said airfoil section wherein said turning vane has a leading edge adjacent said rib wherein said rib segments said airflow in said airfoil section into more than one airflow in said diffuser. 10. The fan blade of claim 1 wherein said diffuser section includes a second turning vane downstream of said turning vane, said second turning vane turning said airflow within said second axial direction. 11. The fan blade as recited in claim 1, wherein the first direction is an axially aft direction, and wherein the second direction is an axially forward direction. 12. A fan-turbine rotor assembly for a tip turbine engine comprising: a multitude of fan blades for rotation about an axis of rotation, each of said multitude of fan blades having an airfoil section, an inducer section, and a diffuser section, said airfoil section defining an airflow passage therethrough;said inducer section in communication with an inlet to said airflow passage to receive an airflow from a first axial direction and turn said airflow to a radial direction;said diffuser section in which air is diffused in communication with an outlet from said airflow passage radially outboard of said airfoil section, said diffuser section having a diffuser section center of mass positioned over said airfoil section, said diffuser section nested into an adjacent diffuser section such that said multitude of fan blades form an annular diffuser, each of said diffuser sections oriented to turn and split said airflow from said radial direction to a second axial direction; anda turning vane within said diffuser section, wherein said turning vane includes a first and second longitudinal side each side of which is progressively folded inward toward a centerline of said turning vane such that a trailing edge of said turning vane forms a V-shape where said trailing edge intersects with an upper surface of said diffuser section. 13. The fan-turbine rotor assembly as recited in claim 12, further comprising a discharge turning vane within said diffuser section adjacent a diffuser discharge outlet. 14. The fan turbine rotor assembly as recited in claim 12, wherein said diffuser section expels said airflow primarily in said second axial direction, wherein said second axial direction is different than said first axial direction. 15. The fan turbine rotor assembly as recited in claim 14, wherein said first axial direction is opposite said second axial direction. 16. A method of communicating an airflow through a fan blade comprising the steps of: (1) communicating said airflow through an airflow passage within an airfoil of said fan blade rotatable about an axis of rotation, said airflow passage having an inducer section to receive said airflow from a first axial direction and turn said airflow to a first radial direction; and(2) turning, within a diffuser section in which air is diffused located radially outboard of an airfoil section, and splitting the airflow from the airflow passage within said airfoil, the diffuser section having a diffuser section center of mass positioned over said airfoil section, said diffuser section oriented to turn and split said airflow from said radial direction to a second axial direction and toward opposite ends of the diffuser section, the second axial airflow direction opposite the first axial direction. 17. A method as recited in claim 16, wherein said step (2) further comprises: equalizing the internal pressure of the airflow through the diffuser section to provide a constant discharge from a diffuser discharge outlet. 18. A method as recited in claim 16, further comprising the step of: generating only tensile stresses in said airfoil section of said fan blade from a centrifugal force exerted upon the diffuser section. 19. A fan blade comprising: a turning vane located within a diffuser of said fan blade with a first and second longitudinal side each side of which is progressively folded inward toward a centerline of said turning vane such that a trailing edge of said turning vane forms a generally V-shape where said trailing edge intersects with an upper surface of a diffuser section. 20. The fan blade as recited in claim 19, wherein a discharge turning vane is disposed within said diffuser section adjacent a diffuser discharge outlet. 21. The fan blade as recited in claim 19, further comprising a rib formed within an airflow passage in communication with said diffuser section and an inducer section, said inducer section to receive an airflow and said diffuser section to expel said airflow. 22. The fan blade as recited in claim 21, wherein said turning vane locates a leading edge adjacent said rib. 23. The fan blade as recited in claim 19, further comprising a multitude of turning vanes sequentially arranged along an airflow passage in communication with said diffuser section. 24. The fan blade as recited in claim 19, further comprising a multitude of discharge turning vanes in communication within said diffuser section adjacent a diffuser discharge outlet. 25. A fan blade comprising: an airfoil section for rotation about an axis of rotation which defines an airflow passage therethrough, said airflow passage having an inducer section to receive an airflow from a first generally axial direction and turn said airflow to a generally radial direction;a diffuser section in communication with said airflow passage, said diffuser section having a diffuser section center of mass positioned directly over said airfoil section, said diffuser section oriented to turn and split said airflow from said generally radial direction to a second generally axial direction: and,a turning vane within said diffuser section wherein said turning vane has a relatively flat leading edge and a generally V-shape trailing edge. 26. A fan blade comprising: an airfoil section for rotation about a first axis, said airfoil section defines an airflow passage therethrough, said airflow passage having an inducer section to receive an airflow from a first axial direction and turn said airflow to a radial direction;a diffuser section receiving airflow from said airflow passage, said diffuser section disposed radially outwardly from said airfoil section and within which said airflow is diffused, said diffuser section enclosed by a shroud extending in a second axial direction from said airfoil section, said second axial direction being substantially opposite said first axial direction, said diffuser section oriented to turn said airflow from said radial direction to said second axial direction; anda first turning vane within said shroud, said turning vane turning said airflow from a radial direction to said second axial direction. 27. The fan blade of claim 26 wherein said diffuser section has a diffuser section center of mass positioned directly over said airfoil section. 28. The fan blade as recited in claim 27, wherein said diffuser section center of mass does not overhang said airfoil section. 29. The fan blade assembly as recited in claim 28, wherein said diffuser section shroud overhangs said airfoil section. 30. The fan blade assembly as recited in claim 26, wherein said first turning vane has a relatively flat leading edge and a V-shape trailing edge. 31. The fan blade assembly as recited in claim 30, wherein said V-shape trailing edge intersects a diffuser upper surface of said diffuser section. 32. The fan blade assembly as recited in claim 30, wherein said first turning vane contacts a top and a bottom of said shroud. 33. The fan blade assembly as recited in claim 30, wherein said first turning vane transits said diffuser section along an arcuate path. 34. The fan blade of claim 26 further comprising a second turning vane within said shroud downstream of said first turning vane, said second turning vane turning said airflow within said second axial direction. 35. The fan blade assembly as recited in claim 34, wherein said second turning vane contacts a top and a bottom of said shroud. 36. The fan blade assembly as recited in claim 26, wherein said diffuser section extends radially and axially above an end of said airfoil section. 37. The fan blade as recited in claim 26, wherein the first direction is an axially aft direction, and wherein the second direction is an axially forward direction.
Gilchrist Alan R. (Fairfield OH) Sullivan Thomas J. (Fairfield OH) Walker Roger C. (Middletown OH), Hybrid spinner nose configuration in a gas turbine engine having a bypass duct.
Rodgers Leonard J.,GB2 ; Newton Arnold C.,GB2 ; Berry James P.,GB2 ; Farrar Peter G. G.,GB2 ; Udall Kenneth F.,GB2, Mounting for coupling a turbofan gas turbine engine to an aircraft structure.
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