Ply architecture for integral platform and damper retaining features in CMC turbine blades
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/28
F01D-005/26
F01D-005/22
F01D-005/14
F01D-011/08
F01D-005/30
F01D-011/00
출원번호
US-0021318
(2014-09-11)
등록번호
US-10202853
(2019-02-12)
국제출원번호
PCT/US2014/055205
(2014-09-11)
국제공개번호
WO2015/080781
(2015-06-04)
발명자
/ 주소
Kleinow, Chad Daniel
출원인 / 주소
General Electric Company
대리인 / 주소
General Electric Company
인용정보
피인용 횟수 :
0인용 특허 :
23
초록
Various embodiments are provided which provide an architecture for CMC plies to improve strength of damper retaining features of a turbine blade assembly. The plies (62) may also be integrated with the platform structure (50) to strength the CMC blade assembly.
대표청구항▼
1. A rotor blade assembly for a gas turbine engine, comprising: a blade portion formed of laid-up ceramic matrix composite (CMC) material having a leading edge and a trailing edge, a pressure side extending between said leading edge and said trailing edge, a suction side opposite said pressure side,
1. A rotor blade assembly for a gas turbine engine, comprising: a blade portion formed of laid-up ceramic matrix composite (CMC) material having a leading edge and a trailing edge, a pressure side extending between said leading edge and said trailing edge, a suction side opposite said pressure side, said suction side extending between said leading edge and said trailing edge; a root formed of said laid-up CMC material having a dovetail at a radially inward end; a shank formed of said laid-up CMC material and integral with said root, said shank extending from said root and a platform extending circumferentially from said shank; a plurality of continuous fiber damper retaining plies of said laid-up CMC material, said plurality of continuous fiber damper retaining plies extending from said dovetail to said platform, said plurality of continuous fiber damper retaining plies being split apart to define an upper at least one ply and a lower at least one ply near the leading edge and the trailing edge; said upper at least one ply extending from said leading edge to said trailing edge and from said dovetail to said platform; said lower at least one ply disposed at said leading edge and said trailing edge opposite said upper at least one ply and extending continuously radially outward from said dovetail, said lower at least one ply forming a damper retaining tab extending from said dovetail and defining a damper pocket near the leading edge and the trailing edge; and, a sheet metal damper disposed in said damper pocket. 2. The rotor blade assembly of claim 1, said lower at least one ply extending continuously from said leading edge to said trailing edge. 3. The rotor blade assembly of claim 1, said lower at least one ply being discontinuous between said leading edge and said trailing edge. 4. The rotor blade assembly of claim 1, wherein said damper pocket receives a machining stock. 5. The rotor blade assembly of claim 4, said machining stock being formed of at least one of resin, matrix, chopped fiber, compound stacks of reinforced fiber plies, and laminate reinforced fiber or fiber stacks. 6. A rotor blade assembly for a gas turbine engine, comprising: a blade portion formed of laid-up ceramic matrix composite (CMC) material having a leading edge and a trailing edge, a pressure side extending between said leading edge and said trailing edge, a suction side opposite said pressure side, said suction side extending between said leading edge and said trailing edge; a root formed of said laid-up CMC material having a dovetail at a radially inward end; a shank formed of said laid-up CMC material and integral with said root, said shank extending from said root and a platform extending circumferentially from said shank; the platform defined by a plurality of continuous fiber CMC flow path plies extending from forward of said leading edge to aft of said trailing edge; a plurality of continuous fiber damper retaining plies of said laid-up CMC material, said plurality of continuous fiber damper retaining plies extending from said dovetail to said platform, said plurality of continuous fiber damper retaining plies being split apart to define an upper at least one ply and a lower at least one ply near the leading edge and the trailing edge; said upper at least one ply extending from said leading edge to said trailing edge and from said dovetail to said platform; said lower at least one ply disposed at said leading edge and said trailing edge opposite said upper at least one ply and extending continuously radially outward from said dovetail, said lower at least one ply forming a damper retaining tab extending from said dovetail and defining a damper pocket near the leading edge and the trailing edge; angel wings formed of continuous fiber CMC angel wing plies, said continuous fiber CMC angel wing plies disposed beneath said plurality of continuous fiber damper retaining plies at the leading edge and the trailing edge, said angel wings extending in a circumferential direction and in an axial direction; and, a sheet metal damper disposed in said damper pocket. 7. The rotor blade assembly of claim 6, said at least one support ply extending at an angle to an engine axis. 8. The rotor blade assembly of claim 6, wherein said at least one support ply further comprises ends which are curvilinear. 9. The rotor blade assembly of claim 6, said at least one support ply disposed between said plurality of continuous fiber CMC flow path plies and said continuous fiber CMC angel wing plies at each of leading edge and said trailing edge. 10. A rotor blade assembly for a gas turbine engine, comprising: a blade portion formed of laid-up ceramic matrix composite (CMC) material having a leading edge and a trailing edge, a pressure side extending between said leading edge and said trailing edge, a suction side opposite said pressure side, said suction side extending between said leading edge and said trailing edge; a root formed of said laid-up ceramic matrix composite (CMC) material having a dovetail at a radially inward end; a shank formed of said laid-up CMC material and integral with said root, said shank extending from said root and a platform extending circumferentially from said shank; a plurality of continuous fiber damper retaining plies of said laid-up CMC material, said plurality of continuous fiber damper retaining plies extending from said dovetail to said platform, said plurality of continuous fiber damper retaining plies extending upwardly from said dovetail and turning outward in a circumferential direction; angel wings formed of laid-up continuous fiber CMC angel wing plies, said laid-up continuous fiber CMC angel wing plies disposed beneath said plurality of continuous fiber damper retaining plies and into said continuous fiber damper retaining plies at the leading edge and the trailing edge, said angel wings extending in the circumferential direction and in an axial direction; retaining tabs formed of a plurality of laid-up CMC retaining tab plies formed near said leading edge and said trailing edge of said pressure side and said suction side, said retaining tabs being positioned between said angel wings along said pressure side and along said suction side, and extending radially outward and having at least one ply extending therebetween; an upper end of said continuous fiber damper retaining plies and said retaining tabs forming a damper pocket near said leading edge and said trailing edge; and, a sheet metal damper disposed in said damper pocket. 11. The rotor blade assembly of claim 10, said retaining tabs further comprising said plurality of laid-up CMC retaining tab plies extending in a direction from said leading edge axially toward said trailing edge, and from said trailing edge axially toward said leading edge from between said laid-up continuous fiber CMC angel wing plies and at least one flow path ply. 12. The rotor blade assembly according to claim 1, wherein said lower at least one ply extends between said leading edge and said trailing edge. 13. A rotor blade assembly, for a gas turbine engine, comprising: a blade portion formed of laid-up ceramic matrix composite (CMC) material having a leading edge and a trailing edge, a pressure side extending between said leading edge and said trailing edge, a suction side opposite said pressure side, said suction side extending between said leading edge and said trailing edge; a root formed of said laid-up CMC material having a dovetail at a radially inward end; a shank formed of said laid-up CMC material and integral with said root, said shank extending from said root and a platform extending circumferentially from said shank; a plurality of continuous fiber damper retaining plies of said laid-up CMC material, said plurality of continuous fiber damper retaining plies extending from said dovetail to said platform, said plurality of continuous fiber damper retaining plies being split apart to define an upper at least one ply and a lower at least one ply near the leading edge and the trailing edge; said upper at least one ply extending from said leading edge to said trailing edge and from said dovetail to said platform; said lower at least one ply disposed at said leading edge and said trailing edge opposite said upper at least one ply and extending continuously radially outward from said dovetail, said lower at least one ply forming a damper retaining tab extending from said dovetail and defining a damper pocket near the leading edge and the trailing edge; a c-shaped at least one ply located within said damper pocket between said upper at least one ply and said lower at least one ply; and a sheet metal damper disposed in said damper pocket. 14. The rotor blade assembly according to claim 13, wherein the sheet metal damper is disposed between ends of said c-shaped at least one ply. 15. The rotor blade assembly according to claim 1, wherein said plurality of continuous fiber damper retaining plies form a single element at a proximal end at said dovetail and split apart at a distal end to define said upper at least one ply, said lower at least one ply, and a separation therebetween. 16. The rotor blade assembly according to claim 6, wherein said plurality of continuous fiber damper retaining plies form a single element at a proximal end at said dovetail and split apart at a distal end to define said upper at least one ply, said lower at least one ply, and a separation therebetween. 17. The rotor blade assembly according to claim 6, further comprising: a c-shaped at least one ply located within said damper pocket between said upper at least one ply and said lower at least one ply. 18. The rotor blade assembly of claim 17, said at least one support ply disposed between said flow path plies and said angel wing plies at each of leading edge and said trailing edge. 19. The rotor blade assembly according to claim 10, further comprising: a c-shaped at least one ply located within said damper pocket between said upper at least one ply and said lower at least one ply. 20. The rotor blade assembly of claim 19, said retaining tabs further comprising said plurality of laid-up CMC retaining tab plies extending in a direction from said leading edge axially toward said trailing edge, and from said trailing edge axially toward said leading edge from between said laid-up continuous fiber CMC angel wing plies and at least one flow path ply.
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이 특허에 인용된 특허 (23)
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