초록 ▼

A method facilitates assembling a rotor assembly for gas turbine engine. The method comprises providing a first rotor blade that includes an airfoil, a platform, a shank and a dovetail, coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor

A method facilitates assembling a rotor assembly for gas turbine engine. The method comprises providing a first rotor blade that includes an airfoil, a platform, a shank and a dovetail, coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor shaft such that a shank cavity is defined between the first and second blades. The method also comprises inserting a seal pin into the horizontal platform seal pin slot such that a gap defined between the first and second rotor blade platforms are substantially sealed wherein the seal pin includes a first end, a second end and a substantially cylindrical body extending therebetween and sized to frictionally engage the slot, wherein at least one of the first and second ends has a cross-sectional area that is smaller than a cross-sectional area of the body.

대표청구항 ▼

What is claimed is: 1. A method for assembling a rotor assembly for gas turbine engine, said method comprising: providing a first rotor blade that includes an airfoil, a platform, a shank that extends radially inward from the platform and includes a horizontal platform seal pin slot and a dovetail

What is claimed is: 1. A method for assembling a rotor assembly for gas turbine engine, said method comprising: providing a first rotor blade that includes an airfoil, a platform, a shank that extends radially inward from the platform and includes a horizontal platform seal pin slot and a dovetail that extends radially inward from the shank; coupling the first rotor blade to a rotor shaft using the dovetail; coupling a second rotor blade to the rotor shaft such that a shank cavity is defined between the first and second blades; and inserting a seal pin into the horizontal platform seal pin slot such that a gap defined between the first and second rotor blade platforms are substantially sealed wherein the seal pin includes a first end, a second end and a substantially cylindrical body extending therebetween and sized to frictionally engage the slot, at least one of the first and second ends has a cross-sectional area that is smaller than a cross-sectional area of the body, wherein at least one of the first and second ends includes a radius portion that is tapered from an outer peripheral surface of the body and is configured to substantially engage a shank sidewall. 2. A method in accordance with claim 1 wherein providing a first rotor blade comprises providing a first rotor blade that includes a horizontal platform seal pin slot that is formed adjacent the platform and in a radially outward portion of a sidewall of the shank. 3. A method in accordance with claim 1 wherein inserting a seal pin into the horizontal platform seal pin slot comprises inserting the seal pin into the horizontal platform seal pin slot such that the seal pin extends substantially parallel to a longitudinal axis of the rotor. 4. A method in accordance with claim 1 wherein inserting a seal pin into the horizontal platform seal pin slot comprises inserting a seal pin into the horizontal platform seal pin slot wherein at least one of the seal pin first and second ends includes at least one flat. 5. A method in accordance with claim 4 wherein inserting a seal pin into the horizontal platform seal pin slot comprises using a seal pin that includes a chamfer portion, wherein the radius portion and the chamfer portion are tapered between the flat and the outer peripheral surface of the body. 6. A method in accordance with claim 5 wherein inserting a seal pin into the horizontal platform seal pin slot comprises inserting the seal pin into the horizontal platform seal pin slot such that the chamfer portion facilitates enhancing radial pin sealing between adjacent said rotor blades. 7. A method in accordance with claim 5 wherein inserting a seal pin into the horizontal platform seal pin slot comprises using a seal pin wherein at least one of the seal pin first and second ends includes at least one flat. 8. A method in accordance with claim 5 wherein inserting a seal pin into the horizontal platform seal pin slot comprises using a seal pin wherein at least one of the seal pin first and second ends includes at least two flats. 9. A method in accordance with claim 8 wherein inserting a seal pin into the horizontal platform seal pin slot comprises using a seal pin wherein the first flat extends a first distance axially toward the second end and the second flat extends a second distance axially toward the second end, the first distance being different than the second distance. 10. A method in accordance with claim 5 wherein inserting a seal pin into the horizontal platform seal pin slot comprises using a seal pin wherein at least one of the seal pin first and second ends includes at least two flats that are substantially parallel to each other. 11. A method in accordance with claim 5 wherein inserting a seal pin into the horizontal platform seal pin slot comprises using a seal pin wherein the seal pin first and second ends each include a pair of flats. 12. A method in accordance with claim 5 wherein inserting a seal pin into the horizontal platform seal pin slot comprises using a seal pin wherein the seal pin first and second ends each include a pair of flats that are substantially parallel with respect to each other. 13. A gas turbine engine rotor assembly comprising: a rotor shaft; a first blade coupled to said rotor shaft, said first blade comprising a first platform and a first shank extending radially inward from said platform, said first shank comprising a sidewall comprising a seal pin slot; a second blade comprising a second platform and a second shank extending radially inward from said second platform, said second blade coupled to said rotor shaft adjacent said first blade such that a gap is defined between said first and second platforms, and such that a shank cavity is defined between said first and second shanks; and a seal pin inserted within said seal pin slot, said seal pin comprising a first end, a second end, and a substantially cylindrical body extending therebetween, at least one of said first end and said second end has a cross-sectional area that is smaller than a cross-sectional area of said body, wherein at least one of the first and second ends comprises a radius portion that is tapered from an outer peripheral surface of the body and is configured to substantially engage a shank sidewall. 14. A gas turbine engine rotor assembly in accordance with claim 13 wherein said seal pin slot is formed adjacent to said platform and extends substantially parallel to a longitudinal axis of said rotor. 15. A gas turbine engine rotor assembly in accordance with claim 13 wherein at least one of said first end and said second end comprises a flat. 16. A gas turbine engine rotor assembly in accordance with claim 15 wherein said body comprises a chamfer portion, said chamfer portion and said radius are tapered between said flat and said outer peripheral surface of said body. 17. A gas turbine engine rotor assembly in accordance with claim 16 wherein said chamfer portion facilitates sealing circumferentially between said rotor blades. 18. A gas turbine engine rotor assembly in accordance with claim 15 wherein said first end and said second end each comprise a flat. 19. A gas turbine engine rotor assembly in accordance with claim 15 wherein at least one of said first end and said second end comprises at least two flats. 20. A gas turbine engine rotor assembly in accordance with claim 19 wherein at least one of said first end and said second end comprises at least a pair of flats that are substantially parallel to each other. 21. A gas turbine engine rotor assembly in accordance with claim 20 wherein said first flat extends a first distance axially toward said second end, said second flat extends a second distance axially toward said second end, the first distance is different than the second distance. 22. A gas turbine engine rotor assembly in accordance with claim 15 wherein said first end and said second end each comprise at least two flats. 23. A gas turbine engine rotor assembly in accordance with claim 22 wherein said first end and said second end each comprise at least a first flat and a second flat that is substantially parallel to said first flat. 24. A gas turbine engine rotor assembly in accordance with claim 23 wherein said first flat extends a first distance axially toward said second end and said second flat extends a second distance axially toward said second end, the first distance being different than the second distance. 25. A gas turbine engine rotor assembly in accordance with claim 13 wherein said gap defines a fluid flow path, said seal pin substantially seals the fluid flow path defined between said first and second platforms. 26. A rotor blade seal pin for a gas turbine engine rotor assembly including a rotor shaft and a plurality of circumferentially-spaced rotor blades coupled to said rotor shaft, each rotor blade includes a platform and a shank, wherein the shank extends radially inward from the platform, said rotor blade seal pin comprising: a first end and a second end; and a substantially cylindrical body having a first cross-sectional area sized for frictional engagement with a rotor blade seal pin slot formed adjacent to the platform, at least one of said first end and said second end having a second cross-sectional area that is smaller than said body first cross-sectional area, wherein at least one of the first and second ends includes a radius portion that is tapered from an outer peripheral surface of the body and is configured to substantially engage a shank sidewall. 27. A rotor blade seal pin in accordance with claim 26 wherein at least one of said first end and said second end comprises a flat. 28. A rotor blade seal pin in accordance with claim 27 wherein said body comprises a chamfer portion, said radius portion and said chamfer portion are tapered between said flat and said outer peripheral surface of said body. 29. A rotor blade seal pin in accordance with claim 28 wherein said chamfer portion facilitates sealing between adjacent said rotor blades. 30. A rotor blade seal pin in accordance with claim 27 wherein said first end and said second end comprises a flat. 31. A rotor blade seal pin in accordance with claim 30 wherein said first end and said second end each comprise at least two flats. 32. A rotor blade seal pin in accordance with claim 31 wherein said first end and said second end each comprise at least at least a pair of flats that are substantially parallel to each other. 33. A rotor blade seal pin in accordance with claim 32 wherein said first flat extends a first distance axially toward said second end and said second flat extends a second distance axially toward said second end, the first distance being different than the second distance. 34. A rotor blade seal pin in accordance with claim 27 wherein at least one of said first end and said second end comprises at least two flats. 35. A rotor blade seal pin in accordance with claim 34 wherein at least one of said first end and said second end comprises at least a first flat and a second flat that is substantially parallel to said first flat. 36. A rotor blade seal pin in accordance with claim 35 wherein said first flat extends a first distance axially toward said second end and said second flat extends a second distance axially toward said second end, the first distance being different than the second distance. 37. A rotor blade seal pin in accordance with claim 26 wherein said rotor blade seal pin substantially seals a fluid flow path defined between adjacent platforms and a shank cavity defined between adjacent rotor blades.