CPC F01D 17/162 (2013.01) [F02C 9/22 (2013.01); F05D 2220/32 (2013.01); F05D 2230/60 (2013.01); F05D 2240/12 (2013.01); F05D 2260/60 (2013.01)] | 20 Claims |
1. A vane adjustment assembly for a gas turbine engine, comprising a plurality of vanes extending radially outward relative to a central axis of the gas turbine engine,
an annular ring arranged radially outward of the central axis and coupled to the plurality of vanes, and
a ring adjustment assembly including (i) a first inclined plate having a first plate surface arranged on an axially facing surface of the annular ring and a second plate surface opposite the first plate surface that is inclined in a first circumferential direction, (ii) a second inclined plate having a first plate surface arranged on the second plate surface of the first inclined plate and a second plate surface opposite the first plate surface of the second inclined plate, the first plate surface of the second inclined plate being inclined in a second circumferential direction opposite the first circumferential direction, and (iii) a roller pin coupled to the second plate surface of the second inclined plate,
wherein the second inclined plate is adjustable in the first and second circumferential directions such that the first plate surface of the second inclined plate is configured to slide along the second plate surface of the first inclined plate during adjustment of the second inclined plate so as to adjust an axial position and a circumferential position of the roller pin relative to the annular ring.
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