IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0331418
(2011-12-20)
|
등록번호 |
US-8905719
(2014-12-09)
|
발명자
/ 주소 |
- Kray, Nicholas Joseph
- McAfee, Christopher Lee
- Shim, Dong-Jin
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
8 |
초록
▼
A composite gas turbine engine structure includes a retention ring with airfoils mounted on, integral with, and extending radially away from retention ring. Retention ring includes annular composite plies, a circumferentially segmented airfoil ring including airfoil ring segments disposed around one
A composite gas turbine engine structure includes a retention ring with airfoils mounted on, integral with, and extending radially away from retention ring. Retention ring includes annular composite plies, a circumferentially segmented airfoil ring including airfoil ring segments disposed around one of outer and inner circumferences of retention ring. Airfoil ring segments include annular bases and radially extending clockwise and counter-clockwise airfoil segments at clockwise and counter-clockwise ends of annular base. Composite airfoils include circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments. A flowpath shell circumferentially disposed around segmented airfoil ring traps annular bases between flowpath shell and retention ring. Composite airfoils airfoils extend through slots in flowpath shell. Plies may be wrapped in a single spiral made from a continuous composite tape. Slots may be circumferentially angled. Circumferentially adjacent ones of clockwise and counter-clockwise airfoil segments may be stitched together.
대표청구항
▼
1. A composite gas turbine engine structure comprising: an annular composite retention ring circumscribed about a centerline axis,composite airfoils mounted on and integral with and extending radially away from the retention ring,the retention ring including annular composite plies,a circumferential
1. A composite gas turbine engine structure comprising: an annular composite retention ring circumscribed about a centerline axis,composite airfoils mounted on and integral with and extending radially away from the retention ring,the retention ring including annular composite plies,a circumferentially segmented airfoil ring including airfoil ring segments disposed around one of an outer and inner circumferences of the retention ring,each of the airfoil ring segments including an annular base and radially extending clockwise and counter-clockwise airfoil segments at clockwise and counter-clockwise ends of the annular base,each of the composite airfoils including circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments,a flowpath shell circumferentially disposed around the segmented airfoil ring and trapping the annular bases between the flowpath shell and the retention ring, andthe composite airfoils extending through slots in the flowpath shell. 2. The structure as claimed in claim 1, further comprising the annular composite plies wrapped in a single spiral. 3. The structure as claimed in claim 2, wherein the annular composite plies and the single spiral are made from a continuous composite tape. 4. The structure as claimed in claim 1, further comprising the retention ring, the composite airfoils, and the inner or outer flowpath shell made at least in part from a carbon fiber woven material. 5. The structure as claimed in claim 4, further comprising the annular composite plies wrapped in a single spiral. 6. The structure as claimed in claim 5, wherein the annular composite plies and the single spiral formed from a continuous composite tape. 7. The structure as claimed in claim 1, further comprising the circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments being stitched together. 8. The structure as claimed in claim 1, further comprising the slots being circumferentially angled or canted in a clockwise direction or a counter-clockwise direction. 9. A composite gas turbine engine structure comprising: an annular retention ring radially spaced apart and inwardly of an annular composite shroud,the retention ring and the shroud circumscribed about a centerline axis,composite airfoils integral with and extending radially between the retention ring and the shroud,the retention ring and the shroud including annular composite plies,a circumferentially segmented composite airfoil ring including airfoil ring segments disposed around an outer circumference of the retention ring,each of the airfoil ring segments including an annular base and radially extending clockwise and counter-clockwise airfoil segments at clockwise and counter-clockwise ends of the annular base,each of the composite airfoils including circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments,an inner flowpath shell circumferentially disposed around the segmented airfoil ring and trapping the annular bases between the inner flowpath shell and the retention ring, andthe composite airfoils and the clockwise and counter-clockwise airfoil segments extending through inner slots in the inner flowpath shell. 10. The structure as claimed in claim 9, further comprising: the annular composite shroud including an outer flowpath shell circumferentially disposed around and radially outwardly spaced apart from the outer flowpath shell,the clockwise and counter-clockwise airfoil segments extending radially outwardly through axially extending outer airfoil slots in the outer flowpath shell, andclockwise and counter-clockwise shroud segments extending circumferentially counter-clockwise and clockwise from the clockwise and counter-clockwise airfoil segments respectively along and around the outer flowpath shell. 11. The structure as claimed in claim 10, further comprising the annular composite plies wrapped in a single spiral in each of the retention ring and the annular composite shroud. 12. The structure as claimed in claim 11, wherein the annular composite plies and the single spirals are made from continuous composite tape. 13. The structure as claimed in claim 12, further comprising the retention ring, the annular composite shroud, and the composite airfoils made at least in part from a carbon fiber woven material. 14. The structure as claimed in claim 13, further comprising the circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments being stitched together. 15. The structure as claimed in claim 13, further comprising the slots being circumferentially angled or canted in a clockwise direction or a counter-clockwise direction. 16. A method for making a gas turbine engine component composite structure, the method comprising: forming an integral preform having airfoil panels extend radially outwardly from and integral with a ring section,forming the ring section by wrapping a composite tape made of carbon fiber woven material,providing airfoil coupons made from the carbon fiber woven material and including a middle section and clockwise and counter-clockwise sections extending away from the middle section,positioning the airfoil coupons around the ring section with the middle sections on the ring section,positioning a sock made from the carbon fiber woven material radially outwardly of and covering the middle sections of the airfoil coupons with the clockwise and counter-clockwise sections extending through sock slots in the sock,positioning the clockwise and counter-clockwise sections to extend radially away from the middle sections to form the airfoil panels, andintroducing resin into the preform and molding the preform and the resin to form the composite structure. 17. The method as claimed in claim 16 further comprising using resin transfer molding or vacuum-assisted resin transfer molding for the molding. 18. The method as claimed in claim 16 further comprising sewing or stitching together circumferentially adjoining ones of the clockwise and counter-clockwise sections before the molding. 19. The method as claimed in claim 16 further comprising providing the sock with the sock slots circumferentially angled or canted around the ring section. 20. The method as claimed in claim 19 further comprising sewing or stitching together circumferentially adjoining ones of the clockwise and counter-clockwise sections before the molding. 21. A method for making a gas turbine engine component composite structure, the method comprising: forming a preform integrally with airfoil panels extending radially between inner and outer ring sections,forming the integral stator preform with carbon fiber woven material,forming the inner and outer ring sections by wrapping composite tape made of the carbon fiber woven material,providing airfoil coupons made from the carbon fiber woven material and including a middle section and clockwise and counter-clockwise sections extending away from the middle section,each of the clockwise and counter-clockwise sections including a panel section attached to the middle section and a shroud section attached to the panel section,positioning the airfoil coupons around the inner ring sections,providing inner and outer socks made from the carbon fiber woven material,positioning the inner sock radially outwardly of and covering the middle sections of the airfoil coupons with the clockwise and counter-clockwise sections extending through inner sock slots in the inner sock,positioning the clockwise and counter-clockwise sections to extend radially away from the middle sections to form the airfoil panels,drawing or passing the shroud sections through outer sock slots in the outer sock,positioning the shroud sections of the clockwise and counter-clockwise sections extending circumferentially away from the panel sections in the clockwise and counter-clockwise directions respectively around an inner circumferences or inner diameter of the outer ring section, andintroducing resin into the preform and molding the preform and the resin to form the composite structure. 22. The method as claimed in claim 21 further comprising trapping the middle sections of the airfoil coupons between the inner sock and the inner ring section and trapping the shroud sections of the clockwise and counter-clockwise sections of the airfoil coupons between the outer sock and the outer ring section of the stator preform. 23. The method as claimed in claim 22 further comprising using resin transfer molding or vacuum-assisted resin transfer molding for the molding. 24. The method as claimed in claim 22 further comprising sewing or stitching together circumferentially adjoining ones of the panel sections of the clockwise and counter-clockwise sections before the molding. 25. The method as claimed in claim 24 further comprising providing the inner and outer socks with the inner and outer sock slots circumferentially angled or canted around the inner and outer ring sections.
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