Split shroud compressor

Claim 2

A compressor for a gas turbine engine comprising: a multi-stage compressor rotor; an axially split compressor case surrounding said rotor; at least one stage of a plurality of variable pitch stator vanes, each vane rotatably secured to said case, each vane longitudinally restrained by said case; a plurality of inner shroud segments segments, each segment extending through an arc of between 45 degrees and 180 degrees; a seal land secured to the inner surface of each segment; a knife edge seal secured to said rotor and sealing against each of said seal lands; said stator vanes each rotatably secured to a shroud segment; and constraint means for longitudinally with respect to said vane constraining each of said shroud segments from inward movement toward said rotor on only those stator vanes located adjacent to the ends of each shroud segment.

Claim 3

A compressor as in claim 1: said means for longitudinally with respect to said vane constraining each of said shroud segments from inward movement comprising; said constraint means located on two stator vanes located adjacent to each end of each shroud segment, whereby load is shared after nominal wear and a backup vane exists.

Claim 4

A compressor as in claim 1: said inner shroud segment extending through an arc of substantially 180 degrees.

Claim 5

A compressor for a gas turbine engine comprising: a multi-stage compressor rotor; an axially split compressor case surrounding said rotor; at least one stage of a plurality of variable pitch stator vanes, each vane rotatably secured to said case, each vane longitudinally restrained by said case; a plurality of inner shroud segments, each segment extending through an arc of between 45 degrees and 180 degrees; a seal land secured to the inner surface of each segment; a knife edge seal secured to said rotor and sealing against each of said seal lands; said stator vanes each rotatably secured to a shroud segment; and constraint means for longitudinally with respect to said vane constraining each of said shroud segments from inward movement toward said rotor on only those stator vanes adjacent to the end of each shroud segment plus one vane located near the middle of each shroud segment.

Claim 6

A compressor for a gas turbine engine comprising: a multi-stage compressor rotor; an axially split compressor case surrounding said rotor; at least one stage of a plurality of variable pitch stator vanes, each vane rotatably secured to said case, each vane longitudinally restrained by said case; a plurality of inner shroud segments, each segment extending through an arc of between 45 degrees and 180 degrees; a seal land secured to the inner surface of each segment; a knife edge seal secured to said rotor and sealing against each of said seal lands; said stator vanes each rotatably secured to a shroud segment; and constraint means for longitudinally with respect to said vane constraining each of said shroud segments from inward movement toward said rotor on only those stator vanes adjacent to the end of each shroud segment plus one vane located near the middle of each shroud segment.

Claim 7

A compressor as in claim 4: said means for longitudinally with respect to said vane constraining each of said shroud segments from inward movement comprising; said constraint means located on two stator vanes located adjacent to each end of each shroud segment, whereby load is shared after nominal wear and a backup vane exists.

Claim 8

A compressor as in claim 5: said inner shroud segment extending through an arc of substantially 180 degrees.

Claim 9

A compressor for a gas turbine engine comprising: a multi-stage compressor rotor; an axially split compressor case surrounding said rotor; at least one stage of a plurality of variable pitch stator vanes, each vane rotatably secured to said case, each vane longitudinally restrained by said case; a plurality of inner shroud segments, each extending through an arc of between 45 degrees and 180 degrees; a seal land secured to the inner surface of each shroud segment; said stator vanes having a threaded inwardly longitudinal extension; a T-shaped cylindrical bushing threadedly engaged to said axial extension; locking means for locking said T-shaped bushing to said longitudinal extension; and said inner shroud segments each having an outwardly facing bearing surface abuttingly engaging an inwardly facing bearing surface of said T-shaped bushing.

Claim 10

A compressor for a gas turbine engine comprising: a multi-stage compressor rotor; an axially split compressor case surrounding said rotor; at least one stage of a plurality of variable pitch stator vanes, each vane rotatably secured to said case, each vane longitudinally restrained by said case; a plurality of inner shroud segments, each extending through an arc of between 45 degrees and 180 degrees; a seal land secured to the inner surface of each shroud segment; said stator vanes having a threaded inwardly longitudinal extension; a T-shaped cylindrical bushing threadedly engaged to said axial extension; locking means for locking said T-shaped bushing to said longitudinal extension; and said inner shroud segments each having an outwardly facing bearing surface abuttingly engaging an inwardly facing bearing surface of said T-shaped bushing.

Claim 11

A compressor for a gas turbine engine comprising: a multi-stage compressor rotor; an axially split compressor case surrounding said rotor; at least one stage of a plurality of variable pitch stator vanes, each vane rotatably secured to said case, each vane longitudinally restrained by said case; a plurality of inner shroud segments, each extending through an arc of between 45 degrees and 180 degrees; a seal land secured to the inner surface of each segment; a knife edge seal secured to said rotor and sealing against each of said seal lands; said stator vanes each rotatably secured to a shroud segment; said stator vanes having a cylindrical extension; said inner shroud segments having a slot adjacent to said stator vanes and elongated in a direction perpendicular to said cylindrical extension of said vanes; said cylindrical extension having a part depth vane slot perpendicular to its longitudinal axis and aligned with said shroud slot; and a Woodruff key located within said shroud slot and said vane slot for constraining said vanes from longitudinal movement with respect to said shroud segment.

Claim 12

A compressor for a gas turbine engine comprising: a multi-stage compressor rotor; an axially split compressor case surrounding said rotor; at least one stage of a plurality of variable pitch stator vanes, each vane rotatably secured to said case, each vane longitudinally restrained by said case; a plurality of inner shroud segments, each extending through an arc of between 45 degrees and 180 degrees; a seal land secured to the inner surface of each segment; a knife edge seal secured to said rotor and sealing against each of said seal lands; said stator vanes each rotatably secured to a shroud segment; said stator vanes having a cylindrical extension; said inner shroud segments having a slot adjacent to said stator vanes and elongated in a direction perpendicular to said cylindrical extension of said vanes; said cylindrical extension having a part depth vane slot perpendicular to its longitudinal axis and aligned with said shroud slot; and a Woodruff key located within said shroud slot and said vane slot for constraining said vanes from longitudinal movement with respect to said shroud segment.