Stress-relieved wire seal assembly for gas turbine engines
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/30
F01D-025/00
F01D-011/00
출원번호
US-0485491
(2012-05-31)
등록번호
US-9140136
(2015-09-22)
발명자
/ 주소
Corcoran, Kevin L.
Boyington, Kimberly Pash
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Kinney & Lange, P.A.
인용정보
피인용 횟수 :
0인용 특허 :
32
초록▼
A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining
A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining the first sidewall, and a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis.
대표청구항▼
1. A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis of rotation of the gas turbine engine, the assembly comprising: a circumferential groove defined in the disk, the groove including: a first sidewall;a base portion adjoining the first sidewall; anda seco
1. A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis of rotation of the gas turbine engine, the assembly comprising: a circumferential groove defined in the disk, the groove including: a first sidewall;a base portion adjoining the first sidewall; anda second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall adjoins the base portion at a location where a concave curvature of the base portion terminates, wherein the second sidewall includes a smooth convex curve, and wherein the entire second sidewall is angled away from the base portion such that the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis; andan annular wire seal positioned at least partially within the groove. 2. The assembly of claim 1, wherein the first sidewall is angled at approximately 90° with respect to the axis. 3. The assembly of claim 2, wherein the first sidewall is substantially planar. 4. The assembly of claim 1 and further comprising: a ramped circumferential ridge that extends radially outward from the disk, wherein the first sidewall adjoins and forms a part of an edge of the ramped circumferential ridge. 5. The assembly of claim 1 and further comprising: an airfoil retention slot defined in the disk, wherein the circumferential groove is located upstream of the airfoil retention slot. 6. The assembly of claim 1 and further comprising: an airfoil retained by the disk, the airfoil having a platform and a notch at an edge of the platform; anda circumferential ridge extending radially outward from the disk and at least partially into the notch. 7. The assembly of claim 1, wherein the wire seal comprises a full hoop split ring having a substantially circular cross-sectional shape. 8. The assembly of claim 7, wherein a radius of the base portion of the groove is approximately equal to a cross-sectional radius of the split ring wire seal. 9. A method of making a sealing assembly for a gas turbine engine, the method comprising: creating a circumferential groove adjacent in a structure to an airfoil retention slot, wherein the groove is created with a first sidewall, a base portion adjoining the first sidewall, a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall adjoins the base portion at a location where a concave curvature of the base portion terminates, wherein the second sidewall includes a smooth convex curve, and wherein the entire second sidewall is angled away from the base portion such that the second sidewall is angled in a range greater than 0° and less than 90° with respect to an engine axis of rotation; andpositioning an annular wire seal at least partially within the groove. 10. The method of claim 9 and further comprising: creating a ramped circumferential ridge that extends radially outward from the structure, such that the first sidewall adjoins and forms a part of an edge of the ramped circumferential ridge. 11. The method of claim 9 and further comprising: creating a notch at an edge of a platform of an airfoil;creating a circumferential ridge extending radially outward from the structure adjacent to the airfoil retention slot; andinserting the airfoil into the airfoil retention slot such that the circumferential ridge at least partially extends into the notch. 12. A sealing assembly for use in a gas turbine engine, the assembly comprising: a retention structure arranged relative to an axis of rotation of the gas turbine engine;an airfoil retention slot defined in the retention structure;an airfoil retained by the airfoil retention slot;a circumferential groove defined in the retention structure adjacent to the airfoil retention slot, the groove including: a first sidewall;a base portion adjoining the first sidewall; anda second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall adjoins the base portion at a location where a concave curvature of the base portion terminates, wherein the second sidewall includes a smooth convex curve, and wherein the entire second sidewall is angled away from the base portion such that the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis; andan annular wire seal positioned at least partially within the groove. 13. The assembly of claim 12, wherein the first sidewall is angled at approximately 90° with respect to the axis. 14. The assembly of claim 13, wherein the first sidewall is substantially planar. 15. The assembly of claim 12 and further comprising: a ramped circumferential ridge that extends radially from the retention structure, wherein the first sidewall adjoins and forms a part of an edge of the ramped circumferential ridge. 16. The assembly of claim 12, wherein the groove is located upstream of the airfoil retention slot. 17. The assembly of claim 12, wherein the airfoil further includes a platform and a notch at an edge of the platform, and wherein the retention structure further includes a circumferential ridge extending radially and at least partially into the notch. 18. The assembly of claim 12, wherein the wire seal comprises a full hoop split ring having a substantially circular cross-sectional shape, and wherein a radius of the base portion of the groove is approximately equal to a cross-sectional radius of the split ring wire seal.
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이 특허에 인용된 특허 (32)
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