초록 ▼

A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within each respective casing rail, and cou

A gas turbine engine compressor including a stator assembly and a method of assembling the same are provided. The method includes providing a compressor casing including at least two stator vane casing rails extending from the casing, coupling a rail liner within each respective casing rail, and coupling a stator vane assembly including two dovetails, and at least two stator vanes coupled together within the casing rails within the liner such that a first dovetail is received within a first casing rail and a first rail liner, and a second dovetail is received within a second casing rail and a second rail liner.

대표청구항 ▼

What is claimed is: 1. A method for assembling a gas turbine engine compressor including a stator assembly, said method comprising: providing a compressor casing including at least two stator vane casing rails extending from the casing; coupling a rail liner within each respective casing rail; and

What is claimed is: 1. A method for assembling a gas turbine engine compressor including a stator assembly, said method comprising: providing a compressor casing including at least two stator vane casing rails extending from the casing; coupling a rail liner within each respective casing rail; and coupling a stator vane assembly including two dovetails, and at least two stator vanes coupled together within the casing rails within the liner such that a first dovetail is received within a first casing rail and a first rail liner, and a second dovetail is received within a second casing rail and a second rail liner. 2. A method in accordance with claim 1 further comprising coupling at least two stator vanes together at an outer platform of each stator vane to form the stator vane assembly. 3. A method in accordance with claim 2 wherein coupling at least two stator vanes together comprises brazing the stator vane platforms together. 4. A method in accordance with claim 2 wherein coupling at least two stator vanes together comprises: nickel plating at least a portion of abutting surfaces of the platforms of each stator vane; and brazing the stator vane platforms together. 5. A method in accordance with claim 4 wherein brazing the stator vane platforms together comprises brazing the vane platforms using a gold-nickel braze alloy. 6. A method in accordance with claim 2 further comprising restoring metallurgical properties of the stator vane assembly after coupling the stator vane platforms together using a brazing operation. 7. A stator vane assembly for a gas turbine engine, said vane assembly comprising a plurality of circumferentially-spaced stator vane doublets, each said doublet comprising a pair of stator vanes coupled together at a respective outer stator vane platform of each said vane, each said stator vane platform includes two dovetails configured to slidably couple within at least two vane rails extending from a compressor casing that extends at least partially circumferentially around said stator vane assembly, said stator vane assembly further comprises at least two vane rail liners coupled within said at least two vane rails, said vane doublets configured to slidably couple within said vane rail liners. 8. A stator vane assembly in accordance with claim 7 wherein said pair of stator vanes are coupled together through a brazing operation. 9. A stator vane assembly in accordance with claim 7 wherein said pair of stator vanes are coupled together using a nickel braze. 10. A stator vane assembly in accordance with claim 7 wherein said pair of stator vane platforms define a portion of an outer flow path boundary through a compressor. 11. A stator vane assembly in accordance with claim 7 wherein said stator vane doublet is configured to facilitate reducing relative movement between said stator vane platforms and said at least two vane rails. 12. A compressor for a gas turbine engine, said compressor comprising: a casing comprising a plurality of stator vane rails, said casing defining an axial flow path therethrough; a rotor positioned within said flow path, said rotor comprising a plurality of rows of circumferentially-spaced rotor blades; and a stator vane assembly extending between adjacent rows of said plurality of rows of rotor blades, each said stator vane assembly comprising a plurality of circumferentially-spaced stator vane doublets including two dovetails received within at least two of said vane rails, each said stator vane doublet comprising a pair of stator vanes coupled together at a respective outer stator vane platform of each said vane. 13. A compressor in accordance with claim 12 further comprising at least two vane rail liners coupled within said at least two vane rails, each said vane platform is configured to slidably couple each said doublet within said vane rail liners. 14. A compressor in accordance with claim 12 wherein said stator vane doublet is configured to facilitate reducing relative movement between said vane platforms and said at least two vane rails. 15. A compressor in accordance with claim 12 wherein said stator vane platforms define a portion of an outer flow path boundary through said compressor, said stator vanes extend radially inward from said stator vane platform. 16. A compressor in accordance with claim 12 wherein said rotor defines a portion of an inner flow path boundary through said compressor. 17. A compressor in accordance with claim 12 wherein adjacent stator vane platforms define a bleed hole. 18. A stator vane assembly in accordance with claim 12 wherein said stator vane platforms are joined together by brazing.