Variable inlet guide vanes for an axial flow compressor

Claim 2

In an axial flow compressor having a frame defining an annular path for axial flow of a fluid and a plurality of radially extending, circumferentially-spaced vanes, each of said vanes being rotatably mounted at its radially outer end, said compressor having means for rotating and positioning said vanes in unison about their respective axes of rotation between a first and a second position, each of said vanes having radially inner ends subject to deflection and vibration due to aerodynamic forces of said fluid, the improvement comprising: a frame portion disposed radially inward of each of said vanes arranged to limit movement of the radially inner end thereof, and a projection on the end of each of said vanes forming clearances with said frame portion, such that deflection of the vane inner ends under aerodynamic forces of the fluid on said vane is restrained by said projection contacting the frame portion, said projection being eccentrically offset with respect to the vane axis of rotation by a preselected amount and in a preselected direction to cause said projection to provide restraining force on the vane inner ends when the vane is rotated from the first position to the second position.

Claim 3

The combination according to claim 1, wherein said projection is arranged so that when the vane is rotated to the second position, said projection contacts said frame portion at substantially the same location as that toward which the vane is deflected by said fluid in said second position.

Claim 4

The combination according to claim 1 wherein said offset is in the range of 0.70 to 0.120 inches.

Claim 5

The combination according to claim 1 wherein said projection is substantially cylindrical and said frame portion includes a substantially cylindrical bushing for receiving said projection.

Claim 6

The combination according to claim 4 wherein an annular clearance between said projection and said bushing is provided in the range of 0.01 to 0.05 inches.

Claim 7

The combination according to claim 1 wherein said projection is offset from said vane axis of rotation in a downstream direction relative to fluid flow in the compressor.

Claim 8

In an axial flow compressor having a frame defining an annular path for axial flow of a fluid and a plurality of radially extending circumferentially-spaced guide vanes, each of said guide vanes having a spindle and being rotatably mounted on said spindle at the vane radially outer end, said compressor having means for rotating and positioning said vanes in unison about the axes of said spindles between an open and a closed position, each of said vanes having radially inner ends subject to deflection and vibration due to aerodynamic forces of said fluid, the improvement comprising: a bushing disposed in said frame radially inward of each of said vanes, and a button on the end of each of said guide vanes contained within and forming clearances with the bushing walls, whereby deflection of the vane inner ends under aerodynamic forces of the fluid on said guide vane in its closed position is limited by said button contacting the bushing walls, said button being eccentrically offset with respect to the guide vane spindle by a pre-selected amount and in a pre-selected direction to cause the button to provide restraining force on the vane inner ends when the vane is rotated to said open position similar to the restraining force produced by the aerodynamic forces on said guide vane in its closed position.

Claim 9

In an axial flow compressor having a frame defining an annular path for axial flow of a fluid and a plurality of radially extending circumferentially-spaced guide vanes, each of said guide vanes having a spindle and being rotatably mounted on said spindle at the vane radially outer end, said compressor having means for rotating and positioning said vanes in unison about the axes of said spindles between an open and a closed position, each of said vanes having radially inner ends subject to deflection and vibration due to aerodynamic forces of said fluid, the improvement comprising: a bushing disposed in said frame radially inward of each of said vanes, and a button on the end of each of said guide vanes contained within and forming clearances with the bushing walls, whereby deflection of the vane inner ends under aerodynamic forces of the fluid on said guide vane in its closed position is limited by said button contacting the bushing walls, said button being eccentrically offset with respect to the guide vane spindle by a pre-selected amount and in a pre-selected direction to cause the button to provide restraining force on the vane inner ends when the vane is rotated to said open position similar to the restraining force produced by the aerodynamic forces on said guide vane in its closed position.

Claim 10

The improvement according to claim 7, wherein said button is a cylindrical radially extending projection formed on the end of said guide vane, and wherein said bushing is a circular hole forming a substantially uniform annular clearance with the button in the absence of fluid flow, said button being offset from the vane axis in a downstream direction on the vane with respect to the fluid flow entering the compressor.

Claim 11

The combination according to claim 8, and wherein said annular clearance is in the range of 0.01 to 0.05 inches, and, wherein said offset is in the range of 0.070 to 0.120 inches.

Claim 12

In an axial flow compressor having a frame defining an annular path for axial flow of a fluid and a plurality of radially extending, circumferentiallyspaced vanes, each of said vanes being mounted at its radially outer end for rotation about a van axis, each of said vanes having radially inner ends subject to deflection and vibration due to aerodynamic forces of said fluid, the improvement comprising: a frame portion disposed radially inward of each of said vanes, arranged to limit movement of the radially inner end thereof, and a projection on the end of each of said vanes and receivable in said frame portion with a predetermined clearance, such that deflection of the vane inner ends under aerodynamic forces of the fluid on said vane is restrained by said projection contacting the frame portion, said projection being eccentrically offset with respect to the vane axis of rotation.

Claim 13

In an axial flow compressor having a frame defining an annular path for axial flow of a fluid and a plurality of radially extending, circumferentiallyspaced vanes, each of said vanes being mounted at its radially outer end for rotation about a van axis, each of said vanes having radially inner ends subject to deflection and vibration due to aerodynamic forces of said fluid, the improvement comprising: a frame portion disposed radially inward of each of said vanes, arranged to limit movement of the radially inner end thereof, and a projection on the end of each of said vanes and receivable in said frame portion with a predetermined clearance, such that deflection of the vane inner ends under aerodynamic forces of the fluid on said vane is restrained by said projection contacting the frame portion, said projection being eccentrically offset with respect to the vane axis of rotation.

Claim 14

The combination according to claim 10 wherein said offset is in the range of 0.70 to 0.120 inches.

Claim 15

The combination according to claim 10 wherein said projection is substantially cylindrical and said portion includes a substantially cylindrical bushing for receiving said projection.

Claim 16

The combination according to claim 12 wherein an annular clearance between said projection and said bushing is provided in the range of 0.01 to 0.05 inches.

Claim 17

The combination according to claim 10 wherein said projection is offset from said vane axis of rotation in a downstream direction relative to fluid flow in the compressor.

Claim 18

The combination according to claim 14 wherein said offset is in the range of 0.70 to 0.120 inches.