초록 ▼

The present invention provides a mounting arrangement for mounting a variable stator vane within a gas turbine engine. The mounting arrangement comprises an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot. The o

The present invention provides a mounting arrangement for mounting a variable stator vane within a gas turbine engine. The mounting arrangement comprises an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot. The or each insert has at least one bore for receiving a spindle portion of the variable stator vane. The at least one insert is formed of a plastics material and/or the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot and there being a smooth transition between the respective first and second widths.

대표청구항 ▼

1. A mounting arrangement for mounting a variable stator vane within a gas turbine engine, said mounting arrangement comprising an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot and has at least one bore for re

1. A mounting arrangement for mounting a variable stator vane within a gas turbine engine, said mounting arrangement comprising an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot and has at least one bore for receiving a spindle portion of the variable stator vane, wherein: the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot. 2. A mounting arrangement according to claim 1 wherein: there is a smooth transition between the respective first and second widths. 3. A mounting arrangement according to claim 1 wherein the inner shroud comprises axially- and circumferentially-extending frame portions projecting from adjacent the radially outermost portion of the slot. 4. A mounting arrangement according to claim 1 wherein the at least one insert is formed of a plastics material. 5. A mounting arrangement according to claim 1 wherein the or each insert has a plurality of bores, each for receiving a respective variable stator vane. 6. An axial compressor having a mounting arrangement according to claim 1 with a variable stator vane mounted in the at least one bore on the at least one insert. 7. A gas turbine engine comprising an axial compressor according to claim 6. 8. A gas turbine engine comprising a mounting arrangement according to claim 1. 9. A mounting arrangement according to claim 1 wherein the at least one insert is formed of a plastics material. 10. A mounting arrangement for mounting a variable stator vane within a gas turbine engine, said mounting arrangement comprising an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot and has at least one bore for receiving a spindle portion of the variable stator vane, wherein: the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is greater than and radially inwards from a respective second width, the first width of the at least one insert being greater than the second width of the slot and there being a smooth transition between the respective first and second widths. 11. A mounting arrangement according to claim 10 wherein the at least one insert is formed of a plastics material. 12. A mounting arrangement according to claim 10 wherein the inner shroud comprises axially- and circumferentially-extending frame portions projecting from adjacent the radially outermost portion of the slot. 13. A mounting arrangement according to claim 10 wherein the slot and the at least one insert each have a substantially trapezoidal axial cross section. 14. A mounting arrangement according to claim 10 wherein the or each insert has a plurality of bores, each for receiving a respective variable stator vane. 15. An axial compressor having a mounting arrangement according to claim 10 with a variable stator vane mounted in the at least one bore on the at least one insert. 16. A gas turbine engine comprising an axial compressor according to claim 15. 17. A gas turbine engine comprising a mounting arrangement according to claim 10. 18. A mounting arrangement for mounting a variable stator vane within a gas turbine engine, said mounting arrangement comprising an inner shroud having a radially- and circumferentially-extending slot and at least one insert which, in use, is retained within said slot and has at least one bore for receiving a spindle portion of the variable stator vane, wherein: the slot and the at least one insert each have a respective axial cross section with a respective first width (axial dimension) which is radially inwards from a respective second width, and there being a smooth transition between the respective first and second widths.