Methods and apparatus for assembling gas turbine engines
First Claim
1. A method of assembling a gas turbine engine, said method comprising:
- providing a plurality of stator vane sectors that each include an equal number of stator vanes that are circumferentially-spaced such that a first circumferential spacing is defined between each pair of adjacent stator vanes within the sector; and
coupling the plurality of stator vane sectors together to form a stator vane assembly such that a second circumferential spacing is defined between each pair of adjacent stator vanes coupled to adjacent sectors, wherein the second circumferential spacing is different from the first circumferential spacing.
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Abstract
A method of assembling a gas turbine engine includes providing a plurality of stator vane sectors that each include an equal number of stator vanes that are circumferentially-spaced such that a first circumferential spacing is defined between each pair of adjacent stator vanes within the sector, and coupling the plurality of stator vane sectors together to form a stator vane assembly such that a second circumferential spacing is defined between each pair of adjacent stator vanes coupled to adjacent sectors, wherein the second circumferential spacing is different from the first circumferential spacing.
16 Citations
20 Claims
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1. A method of assembling a gas turbine engine, said method comprising:
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providing a plurality of stator vane sectors that each include an equal number of stator vanes that are circumferentially-spaced such that a first circumferential spacing is defined between each pair of adjacent stator vanes within the sector; and
coupling the plurality of stator vane sectors together to form a stator vane assembly such that a second circumferential spacing is defined between each pair of adjacent stator vanes coupled to adjacent sectors, wherein the second circumferential spacing is different from the first circumferential spacing. - View Dependent Claims (2, 3, 4)
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- 5. A stator vane assembly for a gas turbine engine, said stator vane assembly comprising a plurality of stator vane sectors, each of said plurality of stator vane sectors comprising an equal number of circumferentially-spaced stator vanes oriented such that a first circumferential spacing is defined between each pair of adjacent stator vanes within each said sector, said plurality of stator vane sectors coupled together such that a second circumferential spacing is defined between each pair of adjacent stator vanes coupled to adjacent sectors, said second circumferential spacing is different from said first circumferential spacing.
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14. A gas turbine engine comprising:
a compressor, said compressor defining an annular flow path, said compressor comprising;
a rotor disk positioned in said flow path, said rotor disk comprising a plurality of circumferentially-spaced rotor blades; and
a stator vane assembly positioned in said flow path downstream of said rotor disk, said stator vane assembly comprising a plurality of stator vane sectors, each of said plurality of stator vane sectors comprising an equal number of circumferentially-spaced stator vanes oriented such that a first circumferential spacing is defined between each pair of adjacent stator vanes within each said sector, said plurality of stator vane sectors coupled together such that a second circumferential spacing is defined between each pair of adjacent stator vanes coupled to adjacent sectors, said second circumferential spacing is different from said first circumferential spacing. - View Dependent Claims (15, 16, 17, 18, 19, 20)
Specification