초록 ▼

Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distribut

Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.

대표청구항 ▼

What is claimed is: 1. An interstage seal comprising: a first rotor stage containing a plurality of outwardly extending blades; a second bladed rotor stage containing a plurality of outwardly extending blades, said second stage spaced axially from said first stage; a vane stage interposed between s

What is claimed is: 1. An interstage seal comprising: a first rotor stage containing a plurality of outwardly extending blades; a second bladed rotor stage containing a plurality of outwardly extending blades, said second stage spaced axially from said first stage; a vane stage interposed between said rotor stages, said vane stage containing at least one radially inwardly directed land; wherein each of said bladed rotor stages contains at least one ring projecting from a platform of said first and second rotor stage of blades, said rings radially cooperating with said at least one land to form the seal; wherein each ring is segmented circumferentially and each blade contains one segment of the ring; and wherein each segment of the ring contains a tongue and a groove and wherein the tongue and the groove of adjacent ring segments cooperate when installed. 2. The seal of claim 1 wherein each ring segment contains a pocket located circumferentially between said tongue and said groove. 3. The seal of claim 1 wherein each ring segment contains an aerodynamic sealing means. 4. A turbine blade comprising: a radially innermost attachment for engaging a rotor; a platform disposed radially outward from said attachment; an airfoil extending radially outward from said platform; at least one ring segment protruding axially from said platform; and wherein said ring segments contain a tongue and a groove. 5. The blade of claim 4 wherein said tongue is inclined in the outward radial direction. 6. The blade of claim 4 wherein said ring segments contain a pocket disposed circumferentially between said tongue and said groove. 7. The seal of claim 6 wherein said ring segments contain an aerodynamic sealing means. 8. A cooled rotor to stator interface seal for a gas turbine engine comprising: a first rotor stage containing a first disk and a plurality of first blades extending radially outward from said first disk; a second rotor stage containing a second disk and a plurality of second blades extending radially outward from said second disk, said first and second stages being spaced apart to form a chamber therebetween, said disks being joined by an axially spanning, annular coupling disposed radially inboard of said blades; a vane stage interposed between said first and second rotor stages, said vane stage containing at least one radially inwardly facing land; a ring projecting axially from each of said first and second blades and radially cooperating with the at least one land to form the seal; and at least one aperture through said coupling for radially introducing a cooling fluid to said chamber for use in cooling the seal. 9. The seal of claim 8 further comprising a plurality of apertures an said first disk for delivering a pressurized fluid into said chamber. 10. The seal of claim 9 further comprising a plurality of apertures in said second disk for removing a portion of the pressurized fluid from said chamber. 11. The seal of claim 9 wherein each ring contains exactly two runners. 12. The seal of claim 11 wherein each runner is canted at an angle towards the vane stage. 13. The seal of claim 12 wherein each runner is canted at an angle of between 22.5 degrees and 68 degrees in relation to said ring. 14. The seal of claim 13 wherein each runner is canted at an angle of 55 degrees in relation to said ring. 15. The seal of claim 8 wherein each of the rings contains a runner disposed radially between said ring and said land. 16. The seal of claim 8 wherein said rings are circumferentially segmented. 17. The seal of claim 16 wherein said ring segments contain a tongue and a groove. 18. The seal of claim 17 wherein each tongue is inclined in the outward radial direction. 19. The seal of claim 18 wherein said ring segments contain at least one pocket disposed circumferentially between said tongue and said groove. 20. The seal of claim 16 wherein said ring segments contain an aerodynamic sealing means. 21. The seal of claim 8 wherein a land is located radially inward of another land. 22. The seal of claim 8 wherein said coupling further comprises a ring protruding radially outward, said ring radially cooperating with the at least one land to form a portion of the seal. 23. The seal of claim 22 wherein said at least one aperture is disposed axially forward of said vane stage.