A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil end. The airfoil includes a concave side surface, a convex side surface and a cavity. The concave and the c
A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil end. The airfoil includes a concave side surface, a convex side surface and a cavity. The concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge. The cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end. The flange is connected to the second airfoil end. The flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge. The shaft extends along the axis, and is connected to the second airfoil end.
대표청구항▼
1. A turbine engine stator vane that rotates about an axis, comprising: an airfoil extending axially between a first airfoil end and a second airfoil end, and comprising a concave side surface, a convex side surface and a cavity, wherein the concave and the convex side surfaces extend between an air
1. A turbine engine stator vane that rotates about an axis, comprising: an airfoil extending axially between a first airfoil end and a second airfoil end, and comprising a concave side surface, a convex side surface and a cavity, wherein the concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge, and the cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end;a flange connected to the second airfoil end, wherein the flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge, wherein the flange has a non-circular cross-sectional geometry which lies in a plane that is perpendicular to the axis of the stator vane; anda shaft extending along the axis, and connected to the second airfoil end. 2. The stator vane of claim 1, wherein the flange further extends radially from leading edge to the distal flange edge. 3. The stator vane of claim 1, wherein the airfoil further comprises one or more cooling apertures that respectively extend from the cavity to at least one of the concave side surface, the convex side surface, the leading edge and the trailing edge. 4. The stator vane of claim 1, wherein the airfoil further comprises a second cavity extending axially into the airfoil from a second cavity inlet in the end surface, and wherein the flange extends circumferentially around at least a portion of the second cavity inlet. 5. A turbine engine stator vane that rotates about an axis, comprising: an airfoil extending axially between a first airfoil end and a second airfoil end, and comprising a concave side surface, a convex side surface and a cavity, wherein the concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge, and the cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end;a flange connected to the second airfoil end, wherein the flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge; anda shaft extending along the axis, and connected to the second airfoil end;wherein the flange extends axially from the end surface to a cooling channel surface, and comprises a lip that extends substantially along the distal flange edge, and wherein a cooling channel extends radially between the airfoil and the lip adjacent to the cooling channel surface. 6. The stator vane of claim 5, further comprising one or more cooling apertures extending axially through the flange, and fluidly coupled with the cooling channel. 7. A turbine engine stator vane that rotates about an axis, comprising: an airfoil extending axially between a first airfoil end and a second airfoil end, and comprising a concave side surface, a convex side surface and a cavity, wherein the concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge, and the cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end;a flange connected to the second airfoil end, wherein the flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge; anda shaft extending along the axis, and connected to the second airfoil end;wherein the flange extends circumferentially around the cavity inlet between a first tab seal surface and a second tab seal surface, and the shaft is located adjacent to and between the first and the second tab seal surfaces. 8. The stator vane of claim 7, wherein the shaft comprises a notch that extends circumferentially around the axis between the first and the second tab seal surfaces, and the notch comprises a semi-annular seal surface. 9. The stator vane of claim 8, further comprising a seal with a semi-annular seal body that extends circumferentially between a first tab and a second tab, wherein the seal body engages the semi-annular seal surface, the first tab engages the first tab seal surface, and the second tab engages the second tab seal surface. 10. The stator vane of claim 1, wherein the shaft comprises a solid shaft. 11. The stator vane of claim 1, further comprising a second shaft that extends along the axis, and is connected to the first airfoil end. 12. The stator vane of claim 1, further comprising a vane actuation element connected to the flange, wherein the actuation element extends axially from the end surface to a distal actuation element end adapted to connect to a vane actuator. 13. A variable area vane arrangement, comprising: a stator vane first platform;a stator vane second platform comprising a vane aperture; anda stator vane that rotates about an axis, the stator vane comprising an airfoil extending axially between a first airfoil end and a second airfoil end, and comprising a concave side surface, a convex side surface and a cavity, wherein the concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge, and the cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end;a flange connected to the second airfoil end and seated within the vane aperture, wherein the flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge, and wherein the flange has a non-circular cross-sectional geometry which lies in a plane that is perpendicular to the axis of the stator vane;a first shaft extending along the axis, wherein the first shaft is connected to the second airfoil end and is rotatably connected to the second platform; anda second shaft extending along the axis, wherein the second shaft rotatably connects the first airfoil end to the first platform;wherein a gas path is formed between the first platform and the second platform, and wherein the second platform is disposed between the gas path and the flange. 14. The vane arrangement of claim 13, wherein the flange further extends radially from the leading edge to the distal flange edge. 15. The vane arrangement of claim 13, wherein the airfoil further comprises one or more cooling apertures that respectively extend from the cavity to at least one of the concave side surface, the convex side surface, the leading edge and the trailing edge. 16. A variable area vane arrangement, comprising: a stator vane first platform;a stator vane second platform comprising a vane aperture; anda stator vane that rotates about an axis, the stator vane comprising an airfoil extending axially between a first airfoil end and a second airfoil end, and comprising a concave side surface, a convex side surface and a cavity, wherein the concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge, and the cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end;a flange connected to the second airfoil end and seated within the vane aperture, wherein the flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge;a first shaft extending along the axis, wherein the first shaft is connected to the second airfoil end and is rotatably connected to the second platform; anda second shaft extending along the axis, wherein the second shaft rotatably connects the first airfoil end to the first platform;wherein the vane aperture comprises a semi-annular shelf with a seal surface;wherein the flange extends axially from the end surface to a cooling channel surface, and comprises a flange lip that extends substantially along the distal flange edge and is engaged with the seal surface; andwherein a cooling channel extends radially between the airfoil and the flange lip, and axially between the seal surface and the cooling channel surface. 17. The vane arrangement of claim 16, further comprising one or more cooling apertures extending axially through the flange, and fluidly coupled with the cooling channel. 18. The vane arrangement of claim 16, wherein the vane aperture further comprises a shelf lip that extends along an inner radial edge of the shelf and axially into the cooling channel from the seal surface. 19. The vane arrangement of claim 13, further comprising a fixed stator vane connected between the first platform and the second platform. 20. The vane arrangement of claim 13, wherein the first platform is one of a plurality of arcuate segments of an annular stator vane first platform;the second platform is one of a plurality of arcuate segments of an annular stator vane second platform;the stator vane is one of a plurality of stator vanes rotatably connected to the annular stator vane first platform and the annular stator vane second platform.
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이 특허에 인용된 특허 (12)
McCaffrey, Michael G.; Hudson, Eric A.; Hill, James D.; Magge, Shankar S.; Wagner, Joel H., 3D contoured vane endwall for variable area turbine vane arrangement.
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Savage Joseph W. ; Halila Ely E. ; Orlando Robert J. ; Boehm ; Jr. Valentine R. ; Martus James A. ; Wallace Thomas T. ; Shelton Monty L., Variable area turbine nozzle.
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