초록

An example stator vane assembly of a turbomachine includes a shroud having a leading edge, a trailing edge, and at least one circumferential edge. The leading edge is circumferentially offset relative to the trailing edge when installed within the turbomachine.

대표청구항 ▼

1. A stator vane assembly of a turbomachine, comprising: a shroud having a leading edge, a trailing edge, and a circumferential edge, wherein the leading edge is circumferentially offset relative to the trailing edge when installed within the turbomachine,wherein the at least one circumferential edg

1. A stator vane assembly of a turbomachine, comprising: a shroud having a leading edge, a trailing edge, and a circumferential edge, wherein the leading edge is circumferentially offset relative to the trailing edge when installed within the turbomachine,wherein the at least one circumferential edge extends from the leading edge to the trailing edge, and a first portion of the circumferential edge is aligned with, and circumferentially offset from, a second portion of the circumferential edge,wherein the circumferential edge comprises an angled edge portion extending between the first portion and the second portion,wherein the shroud is configured to contact a circumferentially adjacent shroud exclusively through portions of the circumferential edge other than the angled edge portion when loaded during operation of the turbomachine. 2. The stator vane assembly of claim 1, wherein the circumferential edge includes a portion that is aligned with an axis of the turbomachine. 3. The stator vane assembly of claim 1, including a vane extending radially from the shroud. 4. The stator vane assembly of claim 3, wherein the vane is a cantilevered vane. 5. The stator vane assembly of claim 4, wherein the vane extends exclusively from the shroud such that the stator vane assembly includes no more than one shroud. 6. The stator vane assembly of claim 1, wherein the angled edge portion has an angle that is offset from the first portion and the second portion, the angled edge portion configured to be spaced from an angled edge portion of a circumferentially adjacent vane. 7. The stator vane assembly of claim 1, wherein the circumferential edge has a step area. 8. The stator vane assembly of claim 1, wherein the at least one circumferential edge includes a first and a second circumferential edge of the shroud, the first circumferential edge mimicking a profile of the second circumferential edge. 9. The stator vane assembly of claim 1, wherein the shroud is an outer diameter shroud. 10. The stator vane assembly of claim 1, wherein the shroud is configured to contact the circumferentially adjacent shroud exclusively through the first portion and the second portion, the first portion upstream from the angled edge portion, the second portion downstream from the angled edge portion. 11. A turbine engine, comprising: a stator vane array including a plurality of stator vanes distributed circumferentially about an axis, each of the plurality of stator vanes including a shroud and a vane extending from the shroud toward the axis,wherein each of the plurality of stator vanes is circumferentially loaded against a circumferentially adjacent stator blade during operation,wherein at least one of the shrouds has a leading edge, a trailing edge, and a circumferential edge, wherein the leading edge is circumferentially offset relative to the trailing edge,wherein the shroud is configured to contact a circumferentially adjacent shroud exclusively through portions of the circumferential edge other than an angled edge portion when loaded during operation of the turbomachine. 12. The turbine engine of claim 11, wherein the plurality of stator vanes are cantilevered stator vanes. 13. The turbine engine of claim 11, wherein the shroud is a radially outer shroud. 14. The turbine engine of claim 11, wherein each of the plurality of stator vanes includes a single shroud and a single vane. 15. The turbine engine of claim 11, wherein the stator vane array is a nonrotating array. 16. The turbine engine of claim 11, further comprising a fan and a compressor that contains the stator vane array. 17. The turbine engine of claim 16, wherein a bypass ratio of the volume of air that passes through the fan and that does not pass through the compressor to the volume of air that passes through the fan and through the compressor is greater than 10. 18. The turbine engine of claim 11, wherein the at least one circumferential edge extends from the leading edge to the trailing edge, and a first portion of the circumferential edge is aligned with, and circumferentially offset from, a second portion of the circumferential edge,wherein the circumferential edge comprises an angled edge portion extending between the first portion and the second portion. 19. The turbine engine of claim 11, wherein the shroud of each of the plurality of stator vanes is the exclusive shroud of each of the plurality of stator vanes such that each of the plurality of stator vanes is directly attached to no more than one shroud. 20. The turbine engine of claim 11, wherein the shroud is configured to contact a circumferentially adjacent shroud exclusively through portions of the circumferential edge other than an angled edge portion when loaded during operation of the turbomachine such that a gap is provided between the shroud and the adjacent shroud, the gap having a perimeter defined entirely by the shroud and the circumferentially adjacent shroud.