초록 ▼

Vane assemblies for gas turbine engines and methods for assembling vane assemblies are disclosed. The vane assemblies may include at least one shroud having at least one vane-receiving portion, at least one vane having at least one end portion received in the vane-receiving portion, and at least one

Vane assemblies for gas turbine engines and methods for assembling vane assemblies are disclosed. The vane assemblies may include at least one shroud having at least one vane-receiving portion, at least one vane having at least one end portion received in the vane-receiving portion, and at least one sealing member having an uncompressed cross-section that is substantially circular. The sealing member(s) are disposed between and in contact with the end portion of the vane and the vane-receiving portion of the shroud.

대표청구항 ▼

1. A compressor vane assembly for use in a gas turbine engine, the assembly comprising: at least one shroud having at least one vane-receiving portion;at least one compressor vane having an airfoil defining a span-wise axis and an end portion received in the at least one vane-receiving portion of th

1. A compressor vane assembly for use in a gas turbine engine, the assembly comprising: at least one shroud having at least one vane-receiving portion;at least one compressor vane having an airfoil defining a span-wise axis and an end portion received in the at least one vane-receiving portion of the at least one shroud, the end portion having an outer peripheral surface, a peripheral groove formed in the outer peripheral surface and extending about an entire perimeter of the end portion, the peripheral groove having a bottom surface and radially inner and outer walls extending from the bottom surface and being radially spaced-apart from each other to define a groove cross-sectional shape, the bottom surface of the peripheral groove forming a groove perimeter profile that, when viewed in a plan view normal to the span-wise axis, has a positive curvature about the entire perimeter of the end portion and the groove perimeter profile is free of concave regions about said entire perimeter; andat least one sealing member being annular and lying in a first plane, the sealing member being resilient and formed of an elastomeric material, the sealing member having a cross-sectional shape taken through a second plane transverse to the first plane, a portion of the sealing member being disposed in the peripheral groove and in contact with the bottom surface thereof, the sealing member follows said groove profile, the cross-sectional shape of the sealing member being different from the groove cross-sectional shape of the peripheral groove;wherein the sealing member is in contact with both the peripheral groove of the end portion of the compressor vane and the vane-receiving portion of the shroud, the cross-sectional shape of the sealing member being substantially circular when the sealing member is in an uncompressed state and in contact with the peripheral groove and the vane-receiving portion, the cross-sectional shape of the sealing member in the uncompressed state being substantially uniform along a substantially entire sealing length about the annular sealing member. 2. The compressor assembly as defined in claim 1, wherein the at least one vane-receiving portion comprises at least one opening for receiving the at least one end portion of the compressor vane and at least one contact surface configured to contact the at least one sealing member. 3. The compressor assembly as defined in claim 2, wherein the at least one contact surface is provided by at least one sheet metal member attached to the at least one shroud. 4. The compressor assembly as defined in claim 2, wherein the at least one contact surface is provided by at least one injection molded plastic member attached to the at least one shroud. 5. The compressor assembly as defined in claim 1, wherein the at least one vane-receiving portion of the at least one shroud comprises a groove configured to receive a portion of the at least one sealing member. 6. The compressor assembly as defined in claim 5, wherein the at least one vane-receiving portion of the at least one shroud is defined between at least one forward annular shroud portion and at least one aft annular shroud portion, and the groove extends circumferentially around at least one of the at least one forward annular shroud portion and the at least one aft annular shroud portion. 7. The compressor assembly as defined in claim 1, wherein the at least one sealing member is out of a gas path of the gas turbine engine. 8. The compressor assembly as defined in claim 1, wherein the sealing member of the compressor vane is made from an electrically insulating material. 9. The compressor assembly as defined in claim 1, wherein the at least one vane-receiving portion of the at least one shroud includes a radially inner vane receiving portion, the inner vane receiving portion having a groove with a cross-sectional shape being defined by an axially-extending back wall and radially-extending contact surfaces extending from the back wall, the contact surfaces being axially spaced-apart and parallel to each other, the at least one end portion of the at least one compressor vane including a radially-inner end portion being seated within the groove of the inner vane receiving portion, the radially-inner end portion abutting against the back wall of the groove. 10. A gas turbine engine comprising: at least one inlet, compressor, combustor and turbine section in serial flow communication; andat least one compressor vane assembly disposed within the compressor and downstream from the at least one inlet, the at least one compressor vane assembly including:at least one radially inner shroud having at least one inner vane-receiving portion;at least one radially outer shroud having at least one outer vane-receiving portion;at least one compressor vane having an inner end portion received in the at least one inner vane-receiving portion of the inner shroud and an outer end portion received in the outer vane-receiving portion of the at least one outer shroud, and an airfoil extending along a span-wise axis between the inner and outer end portions, a peripheral groove formed in at least one of the inner end portion and the outer end portion and extending about an entire perimeter thereof, the peripheral groove forming a groove perimeter profile that, when viewed in a plan view normal to the span-wise axis, has a positive curvature and is free of concave regions about said entire perimeter, the peripheral groove having a bottom surface and radially inner and outer walls extending from the bottom surface, the inner and outer walls being radially spaced-apart and parallel to each other; andat least one sealing member being annular and lying in a first plane, the sealing member being resilient and formed of an elastomeric material, the sealing member having a cross-sectional shape taken through a second plane transverse to the first plane, a portion of the sealing member being disposed in the peripheral groove, the peripheral groove having a groove cross-sectional shape defined in said second plane that is different from the cross-sectional shape of the sealing member, the sealing member being disposed in contact with both the peripheral groove in the compressor vane and the corresponding one of the inner vane-receiving portion of the inner shroud and the outer vane-receiving portion of the outer shroud, the cross-sectional shape of the sealing member being substantially circular when the sealing member is in an uncompressed state and in contact with the peripheral groove and the corresponding one of the inner vane-receiving portion and the outer vane-receiving portion, the cross-sectional shape of the sealing member in the uncompressed state being substantially uniform along a substantially entire sealing length about the annular sealing member. 11. The engine as defined in claim 10, wherein at least one of the at least one inner shroud and at least one outer shroud comprises a groove therein configured to receive a portion of the at least one sealing member. 12. The engine as defined in claim 11, wherein the groove extends circumferentially around the at least one of the at least one inner shroud and at least one outer shroud. 13. The engine as defined in claim 10, wherein the at least one sealing member is out of a gas path of the gas turbine engine. 14. The gas turbine engine as defined in claim 10, wherein the sealing member of the compressor vane is made from an electrically insulating material. 15. The engine as defined in claim 10, wherein the at least one inner vane receiving portion has a groove with a cross-sectional shape being defined by an axially-extending back wall and radially-extending contact surfaces extending from the back wall, the contact surfaces being axially spaced-apart and parallel to each other, the at least one inner end portion of the at least one compressor vane being seated within the groove of the at least one inner vane receiving portion, the at least one inner end portion abutting against the back wall of the groove. 16. A method for assembling a compressor vane assembly for use in a gas turbine engine wherein the compressor vane assembly comprises at least one compressor vane and at least one shroud, the method comprising: providing a pair of annular sealing members for each of the at least one compressor vanes, the sealing members being resilient and formed of an elastomeric material, each of the sealing members lying in a first plane, the sealing members having a cross-sectional shape taken through a second plane transverse to the first plane;installing one of the sealing members within a peripheral groove defined in each of an inner end portion and an outer end portion of the compressor vane, the peripheral groove extending about an entire perimeter of each of the inner and outer end portions, the peripheral groove having a groove cross-sectional shape defined in said second plane that is different from the cross-sectional shape of the sealing member, the groove cross-sectional shape being defined by a bottom surface of the peripheral groove and radially inner and outer walls extending from the bottom surface, the inner and outer walls being radially spaced-apart and parallel to each other, the bottom surface of the peripheral groove forming a groove perimeter profile that, when viewed in a plan view normal to the span-wise axis, has a positive curvature about the entire perimeter of the inner and outer end portions and the groove perimeter profile is free of concave regions about said entire perimeter, once installed within the peripheral groove the cross-sectional shape of the sealing members being substantially circular and in an uncompressed state; andinstalling the inner and outer end portions of the compressor vane in respective inner and outer vane-receiving portions of the at least one shroud to establish contact of each of the sealing members with the end portions of the compressor vane and the respective inner and outer vane-receiving portions. 17. The method as defined in claim 16, comprising installing the sealing members in a location out of a gas path of the gas turbine engine. 18. The method as defined in claim 16, comprising maintaining a tension on the sealing members once the sealing members are installed on the respective end portions of the at least one compressor vane. 19. The method as defined in claim 16, comprising installing the sealing members around the respective end portions of the at least one compressor vane. 20. The method as defined in claim 16, comprising installing the sealing members circumferentially around the at least one vane-receiving portion provided on the at least one shroud.