Claims
- 1. A turbine vane segment, comprising:
inner and outer walls spaced from one another; a vane extending between said inner and outer walls and having leading and trailing edges, said vane including a plurality of discrete cavities between the leading and trailing edges and extending lengthwise of said vane for flowing a cooling medium; an insert sleeve within one said cavity and spaced from interior wall surfaces thereof, said insert sleeve having an inlet end through which cooling medium flows into said insert sleeve, said insert sleeve having a plurality of openings therethrough for flowing the cooling medium through said openings into said space between said sleeve and said interior wall surfaces for impingement against said interior wall surfaces of said vane; and at least one tab defined at at least one longitudinal end of the insert for limiting radial displacement of the insert with respect to the vane.
- 2. A turbine vane segment as in claim 1, wherein said tab is disposed on said insert and extends in a radial direction, generally parallel to a longitudinal axis of the insert, for abutting a component facing thereto to limit radial displacement of the insert.
- 3. A turbine vane segment as in claim 1, wherein said tab is disposed on said insert and projects in a direction generally transverse to a longitudinal axis of the insert for engaging a radial face of a wall of said cavity to limit radial displacement of the insert.
- 4. A turbine vane segment as in claim 3, wherein said radial face is a radial face of an internal rib defined on said wall.
- 5. A turbine vane segment as in claim 4, wherein said tab is mechanically secured to the internal rib.
- 6. A turbine vane segment as in claim 3, wherein said tab is mechanically secured to said wall of said cavity.
- 7. A turbine vane segment as in claim 1, wherein said tab is defined by an outer peripheral edge of a metering plate mounted to an end of the insert.
- 8. A turbine vane segment as in claim 1, wherein said tab is formed by a part of said insert and is distorted with respect to a plane of the wall of the insert to define a retention tab for engaging a radial face of a wall of said cavity to limit radial displacement of the insert.
- 9. A turbine vane segment as in claim 8, wherein said retention tab is mechanically secured to said wall.
- 10. A turbine vane segment as in claim 9, wherein said wall is a radial wall disposed between adjacent cavities of said vane.
- 11. A turbine vane segment as in claim 8, wherein said retention tab is mechanically secured to an internal rib defined on said wall.
- 12. A turbine vane segment as in claim 11, wherein the retention tab is brazed to the internal rib.
- 13. A turbine vane segment as in claim 1, wherein said tab is disposed on a component facing said inlet end of said insert, and extends from said component in a radial direction, generally parallel to a longitudinal axis of the insert, for selectively abutting a wall of said insert to limit radial displacement of the insert.
- 14. A turbine vane segment as in claim 13, wherein said component is an impingement plate disposed to overlie said inner wall of said vane.
- 15. A turbine vane segment as in claim 1, further comprising an internal rib defined about at least a portion of the periphery of said vane adjacent said inlet end of said insert sleeve, said insert sleeve being secured at said inlet end thereof to said internal rib.
- 16. A turbine vane segment as in claim 1, wherein said impingement holes are defined in first and second walls of the insert sleeve that face, respectively, pressure end suction sides of the vane.
- 17. A turbine vane segment as in claim 1, wherein said insert is disposed in an intermediate cavity of said vane through which cooling medium flows from said inner wall towards said outer wall.
- 18. An impingement insert sleeve for being disposed in a coolant cavity defined through a stator vane, having a generally open inlet end and first and second pairs of diametrically opposed side walls, and having at least one tab defined at said inlet end for limiting radial displacement of the insert with respect to the stator vane.
- 19. An impingement insert sleeve as in claim 18, wherein at least one said tab extends in a radial direction from an end edge of a main body of said insert, generally parallel to a longitudinal axis of the insert, for abutting a component facing thereto to limit radial displacement of the insert.
- 20. An impingement insert sleeve as in claim 18, wherein at least one said tab projects in a direction generally transverse to a longitudinal axis of the insert.
- 21. An impingement insert sleeve as in claim 18, wherein said at least one tab is formed as a part of at least one of said sidewalls and is distorted with respect to a plane of said at least one sidewall to define a bent-over, retention tab.
- 22. A turbine vane segment, comprising:
inner and outer walls spaced from one another; a vane extending between said inner and outer walls and having leading and trailing edges, said vane including a plurality of discrete cavities between the leading and trailing edges and extending lengthwise of said vane for flowing a cooling medium; an insert sleeve within one said cavity and spaced from interior wall surfaces thereof, said insert sleeve having an inlet end through which cooling medium flows into said insert sleeve, said insert sleeve having a plurality of openings therethrough for flowing the cooling medium through said openings into said space between said sleeve and said interior wall surfaces for impingement against said interior wall surface of said vane; an internal rib being defined about at least a portion of a periphery of said cavity, said insert being mounted to said internal rib by a braze or weld joint; and a metering plate having at least one opening for cooling medium flow defined therethrough, said metering plate being mounted to said inlet end of said insert sleeve and projecting laterally beyond an outer periphery of said insert so as to at least partially overlie said internal rib, whereby radial displacement of said insert with respect to said vane in the event of joint failure is substantially limited.
- 23. A turbine vane segment as in claim 22, wherein there are a plurality of flow openings defined through said metering plate.
- 24. A turbine vane segment as in claim 22, further comprising at least one standoff tab projecting radially from a surface of said metering plate, for abutting engagement with an adjacent structure to limit radial displacement of the insert sleeve.
- 25. An impingement insert sleeve for being disposed in a coolant cavity defined through a stator vane, having an inlet end, first and second pairs of diametrically opposed side walls, a collar mounted to said inlet end, and a metering plate having at least one opening for cooling medium flow defined therethrough, said metering plate being mounted to said inlet end of said insert sleeve and including a portion projecting laterally beyond an outer periphery of said insert and said collar.
- 26. An impingement insert sleeve as in claim 25, further comprising at least one standoff tab projecting radially from a surface of said metering plate, for abutting engagement with an adjacent structure to limit radial displacement of the insert sleeve.
FEDERAL RESEARCH STATEMENT
[0001] [Federal Research Statement Paragraph]The Government may have certain rights in this invention pursuant to Contract No. DE-FC21-95MC31176 awarded by the U.S. Department of Energy.