Blade tip clearance control apparatus with shroud segment position adjustment by unison ring movement

Claim 2

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) at least one shroud segment defining a circumferential portion of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly of at least one of said rotor blade tips; (b) at least one mounting structure on said stationary casing defining a passage between exterior and interior sides of said casing, said mounting structure being spaced radially outwardly from said shroud segment; (c) a positioning mechanism supported by said mounting structure, connected to said shroud segment, and being movable toward and away from said rotor blade tip; and (d) an actuating mechanism coupled to said positioning mechanism and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanism and said shroud segment connected therewith radially relative to said rotor axis to a position between inner and outer positions which define maximum and minimum clearance between said shroud segment and said rotor blade tip; said actuating mechanism being in the form of an annular member having at least one slot defined therethrough extending in a transverse inclined relation to the respective directions of movement of said actuating and positioning mechanisms and having spaced opposite ends defining said first and second angularly displaced limit positions of said annular member at said slot therethrough.

Claim 3

The apparatus as recited in claim 1, wherein said positioning mechanism includes: an elongated support member mounted through said passage defined by said mounting structure for movement relative thereto and radially toward and away from said rotor axis, said support member having a longitudinal axis and opposite inner and outer end portions, said shroud segment being connected to said inner end portion of said support member at said interior side of said casing; and means for coupling said outer end portion of said support member at said exterior side of said casing to said actuating mechanism.

Claim 4

The apparatus as recited in claim 2, wherein: said mounting structure is a cylindrical boss formed on said casing, defining said passage, and projecting from said exterior side of said casing; and said support member is a cylindrical shaft mounted through said passage of said boss for slidable movement toward and away from said rotor axis relative to said boss.

Claim 5

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) at least one shroud segment defining a circumferential portion of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly of at least one of said rotor blade tips; (b) at least one mounting structure on said stationary casing defining a passage between exterior and interior sides of said casing, said mounting structure being spaced radially outwardly from said shroud segment; (c) a positioning mechanism supported by said mounting structure, connected to said shroud segment, and being movable toward and away from said rotor blade tip; and (d) an actuating mechanism coupled to said positioning mechanism and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanism and said shroud segment connected therewith radially relative to said rotor axis to a position between inner and outer positions which define maximum and minimum clearance between said shroud segment and said rotor blade tips, said actuating mechanism being in the form of an annular member having at least one slot extending in a transverse inclined relation to the respective directions of movement of said actuating and positioning mechanisms and having spaced opposite ends defining said first and second angularly displaced limit positions of circumferential movement of said annular member, said positioning mechanism being coupled to said annular member at said slot therein; said positioning mechanism including (i) an elongated support member mounted through said passage defined by said mounting structure for movement relative thereto and radially toward and away from said rotor axis, said support member having a longitudinal axis and opposite inner and outer end portions, said shroud segment being connected to said inner end portion of said support member at said interior side of said casing, and (ii) means for coupling said outer end portion of said support member at said exterior side of said casing to said actuating mechanism.

Claim 6

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) at least one shroud segment defining a circumferential portion of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly of at least one of said rotor blade tips; (b) at least one mounting structure on said stationary casing defining a passage between exterior and interior sides of said casing, said mounting structure being spaced radially outwardly from said shroud segment; (c) a positioning mechanism supported by said mounting structure, connected to said shroud segment, and being movable toward and away from said rotor blade tip; and (d) an actuating mechanism coupled to said positioning mechanism and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanism and said shroud segment connected therewith radially relative to said rotor axis to a position between inner and outer positions which define maximum and minimum clearance between said shroud segment and said rotor blade tips, said actuating mechanism being in the form of an annular member having at least one slot extending in a transverse inclined relation to the respective directions of movement of said actuating and positioning mechanisms and having spaced opposite ends defining said first and second angularly displaced limit positions of circumferential movement of said annular member, said positioning mechanism being coupled to said annular member at said slot therein; said positioning mechanism including (i) an elongated support member mounted through said passage defined by said mounting structure for movement relative thereto and radially toward and away from said rotor axis, said support member having a longitudinal axis and opposite inner and outer end portions, said shroud segment being connected to said inner end portion of said support member at said interior side of said casing, and (ii) means for coupling said outer end portion of said support member at said exterior side of said casing to said actuating mechanism.

Claim 7

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) at least one shroud segment defining a circumferential portion of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly of at least one of said rotor blade tips; (b) at least one mounting structure on said stationary casing defining a passage between exterior and interior sides of said casing, said mounting structure being spaced radially outwardly from said shroud segment; (c) a positioning mechanism supported by said mounting structure, connected to said shroud segment, and being movable toward and away from said rotor blade tip; and (d) an actuating mechanism coupled to said positioning mechanism and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanism and said shroud segment connected therewith radially relative to said rotor axis to a position between inner and outer positions which define maximum and minimum clearance between said shroud segment and said rotor blade tip; said positioning mechanism including (i) an elongated support member mounted through said passage defined by said mounting structure for movement relative thereto and radially toward and away from said rotor axis, said support member having a longitudinal axis and opposite inner and outer end portions, said shroud segment being connected to said inner end portion of said support member at said interior side of said casing, and (ii) means for coupling said outer end portion of said support member at said exterior side of said casing to said actuating mechanism, said coupling means including a pin mounted to said outer end of said support member and within said slot of said annular member for translating circumferential movement of said annular member into linear radial movement of said support member.

Claim 8

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) at least one shroud segment defining a circumferential portion of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly of at least one of said rotor blade tips; (b) at least one mounting structure on said stationary casing defining a passage between exterior and interior sides of said casing, said mounting structure being spaced radially outwardly from said shroud segment; (c) a positioning mechanism supported by said mounting structure, connected to said shroud segment, and being movable toward and away from said rotor blade tip; and (d) an actuating mechanism coupled to said positioning mechanism and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanism and said shroud segment connected therewith radially relative to said rotor axis to a position between inner and outer positions which define maximum and minimum clearance between said shroud segment and said rotor blade tip; said positioning mechanism including (i) an elongated support member mounted through said passage defined by said mounting structure for movement relative thereto and radially toward and away from said rotor axis, said support member having a longitudinal axis and opposite inner and outer end portions, said shroud segment being connected to said inner end portion of said support member at said interior side of said casing, and (ii) means for coupling said outer end portion of said support member at said exterior side of said casing to said actuating mechanism, said coupling means including a pin mounted to said outer end of said support member and within said slot of said annular member for translating circumferential movement of said annular member into linear radial movement of said support member.

Claim 9

The apparatus as recited in claim 5, wherein said coupling means further includes a roller bearing disposed between said pin and one of said support member or said annular member for providing rolling contact therebetween.

Claim 10

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) a plurality of shroud segments defining circumferential portions of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly from said rotor blade tips; (b) a plurality of mounting structures on said stationary casing defining passages between exterior and interior sides of said casing, said mounting structures being circumferentially spaced from one another about said rotor axis and spaced radially outwardly from said shroud segments; (c) a plurality of positioning mechanisms supported by said mounting structures, rigidly connected to said shroud segments, and being movable toward and away from said rotor axis for moving said shroud segments toward and away from said rotor blade tips; and (d) an actuating mechanism coupled to said positioning mechanisms and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanisms and said shroud segments connected therewith radially relative to said rotor axis to positions between inner and outer positions which define maximum and minimum clearances between said shroud segments and said rotor blade tips; said actuating mechanism being in the form of an annular member having a plurality of circumferentially spaced slots defined therethrough each extending in a transverse inclined relation to the respective directions of movement of said actuating and positioning mechanisms and having spaced opposite ends defining said first and second angularly displaced limit positions of said annular member, said positioning mechanisms being coupled to said annular member at said slots therethrough.

Claim 11

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) a plurality of shroud segments defining circumferential portions of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly from said rotor blade tips; (b) a plurality of mounting structures on said stationary casing defining passages between exterior and interior sides of said casing, said mounting structures being circumferentially spaced from one another about said rotor axis and spaced radially outwardly from said shroud segments; (c) a plurality of positioning mechanisms supported by said mounting structures, rigidly connected to said shroud segments, and being movable toward and away from said rotor axis for moving said shroud segments toward and away from said rotor blade tips; and (d) an actuating mechanism coupled to said positioning mechanisms and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanisms and said shroud segments connected therewith radially relative to said rotor axis to positions between inner and outer positions which define maximum and minimum clearances between said shroud segments and said rotor blade tips; said actuating mechanism being in the form of an annular member having a plurality of circumferentially spaced slots defined therethrough each extending in a transverse inclined relation to the respective directions of movement of said actuating and positioning mechanisms and having spaced opposite ends defining said first and second angularly displaced limit positions of said annular member, said positioning mechanisms being coupled to said annular member at said slots therethrough.

Claim 12

The apparatus as recited in claim 7, wherein each of said positioning mechanisms includes: an elongated suport member mounted through said passage defined by one of said mounting structures for movement relative thereto and radially toward and away from said rotor axis, said support member having a longitudinal axis and opposite inner and outer end portions, one of said shroud segments being rigidly connected to said inner end portion of said support member at said interior side of said casing; and means for coupling said outer end portion of said support member at said exterior side of said casing to said actuating mechanism.

Claim 13

The apparatus as recited in claim 8, wherein: each of said mounting structures is a cylindrical boss formed on said casing, defining said passage, and projecting from said exterior side of said casing; and each of said support members is a cylindrical shaft mounted through said passage of one of said bosses for slidable movement toward and away from said rotor axis relative to said boss.

Claim 14

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) a plurality of shroud segments defining circumferential portions of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly from said rotor blade tips; (b) a plurality of mounting structures on said stationary casing defining passages between exterior and interior sides of said casing, said mounting structures being circumferentially spaced from one another about said rotor axis and spaced radially outwardly from said shroud segments; (c) a plurality of positioning mechanisms supported by said mounting structures, rigidly connected to said shroud segments, and being movable toward and away from said rotor axis for moving said shroud segments toward and away from said rotor blade tips; and (d) an actuating mechanism coupled to said positioning mechanisms and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanisms and said shroud segments connected therewith radially relative to said rotor axis to positions between inner and outer positions which define maximum and minimum clearances between said shroud segments and said rotor blade tips, said actuating mechanism being in the form of an annular member having a plurality of circumferentially spaced slots defined therethrough each extending in a transverse inclined relation to the respective directions of movement of said actuating and positioning mechanisms and having spaced opposite ends defining said first and second angularly displaced limit positions of said annular member, said positioning mechanisms being coupled to said annular member at said slots therethrough; each of said positioning mechanisms including (i) an elongated support member mounted through said passage defined by one of said mounting structures for movement relative thereto and radially toward and away from said rotor axis, said support member having a longitudinal axis and opposite inner and outer end portions, one of said shroud segments being rigidly connected to said inner end portion of said support member at said interior side of said casing; and (ii) means for coupling said outer end portion of said support member at said exterior side of said casing to said actuating mechanism.

Claim 15

In a gas turbine engine including a rotatable rotor having a central axis and a row of blades with outer tips and a stationary casing with a shroud disposed in concentric relation with said rotor, an apparatus for controlling the clearance between said rotor blade tips and casing shroud, said apparatus comprising: (a) a plurality of shroud segments defining circumferential portions of said casing shroud and being separate from and spaced radially inwardly of said casing and outwardly from said rotor blade tips; (b) a plurality of mounting structures on said stationary casing defining passages between exterior and interior sides of said casing, said mounting structures being circumferentially spaced from one another about said rotor axis and spaced radially outwardly from said shroud segments; (c) a plurality of positioning mechanisms supported by said mounting structures, rigidly connected to said shroud segments, and being movable toward and away from said rotor axis for moving said shroud segments toward and away from said rotor blade tips; and (d) an actuating mechanism coupled to said positioning mechanisms and being operable to move circumferentially relative to said rotor axis between first and second angularly displaced limit positions to cause nonrotatable, linear movement of said positioning mechanisms and said shroud segments connected therewith radially relative to said rotor axis to positions between inner and outer positions which define maximum and minimum clearances between said shroud segments and said rotor blade tips, said actuating mechanism being in the form of an annular member having a plurality of circumferentially spaced slots defined therethrough each extending in a transverse inclined relation to the respective directions of movement of said actuating and positioning mechanisms and having spaced opposite ends defining said first and second angularly displaced limit positions of said annular member, said positioning mechanisms being coupled to said annular member at said slots therethrough; each of said positioning mechanisms including (i) an elongated support member mounted through said passage defined by one of said mounting structures for movement relative thereto and radially toward and away from said rotor axis, said support member having a longitudinal axis and opposite inner and outer end portions, one of said shroud segments being rigidly connected to said inner end portion of said support member at said interior side of said casing; and (ii) means for coupling said outer end portion of said support member at said exterior side of said casing to said actuating mechanism.

Claim 16

The apparatus as recited in claim 10, wherein said means for coupling each of said support members to said actuating mechanism includes a pin mounted to said outer end of said support member and within one of said slots of said annular member for translating circumferential movement of said annular member into linear radial movement of said support members.

Claim 17

The apparatus as recited in claim 11, wherein said coupling means further includes a roller bearing disposed between said pin and one of said support member or said annular member for providing rolling contact therebetween.