The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud segment. The first and the second shroud segments define a gap
The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud segment. The first and the second shroud segments define a gap therebetween, and the first and the third shroud segments define a gap therebetween. A first seal portion is positioned at least partially on the first and the third shroud segments and at least partially covers the gap defined by the first and the third shroud segments. A second seal portion is positioned at least partially on the first and the second shroud segments and at least partially covers the gap defined by the first and the second shroud segments. A third seal portion extends between and couples the first and the second seal portions.
대표청구항▼
1. A shroud assembly for a gas turbine engine defining a circumferential direction C, comprising: a first shroud segment extending between a first end and a second end along the circumferential direction C;a second shroud segment spaced from the first shroud segment along the circumferential directi
1. A shroud assembly for a gas turbine engine defining a circumferential direction C, comprising: a first shroud segment extending between a first end and a second end along the circumferential direction C;a second shroud segment spaced from the first shroud segment along the circumferential direction C and defining a gap with the first end of the first shroud segment;a third shroud segment spaced from the first shroud segment along the circumferential direction C and defining a gap with the second end of the first shroud segment; anda seal comprising: a first seal portion positioned at least partially on the first shroud segment and the third shroud segment and at least partially covering the gap defined by the first shroud segment and the third shroud segment;a second seal portion positioned at least partially on the first shroud segment and the second shroud segment and at least partially covering the gap defined between the first shroud segment and the second shroud segment; anda third seal portion extending between and coupling the first seal portion and the second seal portion; where the seal has a first end and a second end where the first end and second end are on different shroud segments. 2. The shroud assembly of claim 1, wherein the first shroud segment comprises a first circumferential surface at the first end and a second circumferential surface at the second end, wherein the first seal portion comprises a first circumferential edge and a second circumferential edge spaced apart along the circumferential direction C, and wherein the first circumferential surface of the first shroud segment is positioned circumferentially between the first circumferential edge of the first seal portion and the second circumferential edge of the first seal portion. 3. The shroud assembly of claim 1, wherein the second seal portion comprises a first circumferential edge and a second circumferential edge spaced apart along a circumferential direction, wherein the second circumferential surface of the first shroud segment is positioned circumferentially between the first circumferential edge of the second seal portion and the second circumferential edge of the second seal portion. 4. The shroud assembly of claim 1, wherein the first shroud segment comprises a radially inner surface and a radially outer surface spaced apart from the radially inner surface, and wherein the seal is positioned on the radially outer surface of the first shroud segment. 5. The shroud assembly of claim 4, further comprising: a mounting projection extending radially outwardly from the radially outer surface of the first shroud segment, wherein the mounting projection is circumferentially positioned between a second circumferential edge of the first seal portion and the second circumferential edge of a second seal portion. 6. The shroud assembly of claim 1, wherein the seal comprises a wall projecting radially outwardly from the third seal portion. 7. The shroud assembly of claim 1, wherein the first shroud segment comprises a first axial surface and second axial surface spaced apart along an axial direction A from the first axial surface, wherein the third seal portion comprises a first axial surface and second axial surface spaced apart along the axial direction A from the first axial surface of the third seal portion, and wherein the first axial surface of the first shroud segment is positioned axially between the first axial surface of the third seal portion and the second axial surface of the third seal portion. 8. The shroud assembly of claim 7, wherein the second axial surface of the third seal portion is perpendicular to a second circumferential surface of the first seal portion and a second circumferential surface of the second seal portion. 9. The shroud assembly of claim 1, wherein the second shroud segment comprises a first circumferential surface and a second circumferential surface spaced along the circumferential direction, wherein a first circumferential edge of the second seal portion is positioned circumferentially between the first circumferential surface of the second shroud segment and the second circumferential surface of the second shroud segment, and wherein a second circumferential edge of the second seal portion is positioned circumferentially between a first circumferential surface of the first shroud segment and a second circumferential surface of the first shroud segment. 10. The shroud assembly of claim 9, wherein the seal further comprises: a fourth seal portion comprising a first circumferential surface and a second circumferential surface spaced apart along the circumferential direction C from the first circumferential surface, wherein the second circumferential surface of the second shroud segment is positioned circumferentially between the first circumferential surface of the fourth seal portion and the second circumferential surface of the fourth seal portion; anda fifth seal portion coupling the second seal portion and the fourth seal portion. 11. The shroud assembly of claim 1, wherein the third seal portion is formed integrally with the first seal portion and the second seal portion. 12. The shroud assembly of claim 1, wherein the seal is planar. 13. The shroud assembly of claim 1, wherein the first seal portion defines an axial length, wherein the second seal portion defines an axial length, wherein the first shroud segment defines an axial length, and wherein the axial length of the first seal portion and the axial length of the second seal portion are at least half of the axial length of the first shroud segment. 14. A gas turbine engine defining a circumferential direction C, comprising: a compressor section;a combustion section;a turbine section, comprising: a first shroud segment extending between a first end and a second end along the circumferential direction C;a second shroud segment spaced from the first shroud segment along the circumferential direction C and defining a gap with the second end of the first shroud segment;a third shroud segment spaced from the first shroud segment along the circumferential direction C and defining a gap with the first end of the first shroud segment; anda seal comprising: a first seal portion positioned at least partially on the first shroud segment and the third shroud segment and at least partially covering the gap defined by the first shroud segment and the third shroud segment;a second seal portion positioned at least partially on the first shroud segment and second shroud segment and at least partially covering the gap defined between the first shroud segment and the second shroud segment; anda third seal portion extending between and coupling the first seal portion and the second seal portion. 15. The gas turbine of claim 14, wherein the first shroud segment comprises a first circumferential surface at the first end and a second circumferential surface at the second end, wherein the second seal portion comprises a first circumferential edge and a second circumferential edge spaced apart along the circumferential direction C, and wherein the second circumferential surface of the first shroud segment and a first circumferential surface of the second shroud segment are positioned circumferentially between the first circumferential edge of the second seal portion and the second circumferential edge of the second seal portion. 16. The gas turbine engine of claim 15, wherein the first seal portion comprises a first circumferential edge and a second circumferential edge spaced apart along the circumferential direction C from the first circumferential edge, and wherein the first circumferential surface of the first shroud segment is positioned circumferentially between the first circumferential edge of the first seal portion and the second circumferential edge of the first seal portion. 17. The gas turbine engine of claim 16, further comprising: a first mounting projection extending radially outwardly from the first shroud segment, wherein the first mounting projection is circumferentially positioned between the second circumferential edge of the first seal portion and the second circumferential edge of the second seal portion; anda second mounting projection extending radially outwardly from the second shroud segment, wherein the first circumferential edge of the second seal portion and the second circumferential edge of the second seal portion are circumferentially positioned between the first mounting projection and the second mounting projection. 18. The gas turbine engine of claim 16, wherein the seal comprises: a fourth seal portion comprising a first circumferential edge and a second circumferential edge spaced apart along the circumferential direction C from the first circumferential edge, wherein the second circumferential surface of the second shroud segment is positioned circumferentially between the first circumferential edge of the fourth seal portion and the second circumferential edge of the fourth seal portion; anda fifth seal portion coupling the second seal portion and the fourth seal portion. 19. The gas turbine engine of claim 18, wherein the first circumferential edge of the first seal portion, the first circumferential edge of the second seal portion, and the first circumferential edge of the fourth seal portion are parallel. 20. The gas turbine engine of claim 18, wherein the third seal portion comprises a first axial edge and second axial edge spaced apart along an axial direction A from the first axial edge, wherein the fifth seal portion comprises a first axial edge and second axial edge spaced apart along an axial direction A from the first axial edge, and wherein the first axial edge of the third seal portion and the first axial edge of the fifth seal portion are coplanar.
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이 특허에 인용된 특허 (13)
Bailey Mark J. (Cincinnati OH) Bonner Kurt J. (Maineville OH), Compressor liner spacing device.
Bagepalli Bharat Sampathkumar ; Aslam Sami ; Bedell Leslie Boyd ; Aksit Mahmut Faruk, Turbine spline seal and turbine assembly containing such spline seal.
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