Abstract: A variable guide vane assembly for a gas turbine engine stator is provided. The variable guide vane assembly includes a plurality of vanes and a plurality of RT mechanisms. The vanes extend between a shroud and hub. The vanes are circumferentially disposed and spaced apart from one another. Each vane includes inner and outer radial ends, and inner and outer radial posts. Each vane is pivotally mounted to rotate about its rotational axis. Each RT mechanism is in communication with the inner or outer radial post of a respective vane. The RT mechanism includes a pin connected to the vane that is disposed in a ramp slot non-rotational relative to the pivotable vane. The ramp slot extends between first and second lengthwise ends. Rotation of the vane relative to the ramp slot causes the pin to travel within the ramp slot and the vane to translate linearly.

Abstract: A gas turbine engine apparatus includes an engine flowpath, a protuberance and a variable vane. The protuberance projects into the engine flowpath. The variable vane extends across the engine flowpath. The variable vane includes a pivot axis and an airfoil. The variable vane is configured to pivot about the pivot axis between a first position and a second position. The airfoil extends spanwise along a span line between a first end and a second end. The airfoil extends chordwise along a chord line between a leading edge and a trailing edge. A recess extends spanwise into the airfoil from the first end. The airfoil, at the first end, is spaced from the protuberance when the variable vane is in the first position. The airfoil, at the first end, is aligned with the protuberance and the protuberance projects into the recess when the variable vane is in the second position.

Abstract: A variable guide vane assembly for a gas turbine engine stator is provided. The variable guide vane assembly includes a plurality of vanes and a plurality of RT mechanisms. The vanes extend between a shroud and hub. The vanes are circumferentially disposed and spaced apart from one another. Each vane includes inner and outer radial ends, and inner and outer radial posts. Each vane is pivotally mounted to rotate about its rotational axis. Each RT mechanism is in communication with the inner or outer radial post of a respective vane. The RT mechanism includes a pin connected to the vane that is disposed in a ramp slot non-rotational relative to the pivotable vane. The ramp slot extends between first and second lengthwise ends. Rotation of the vane relative to the ramp slot causes the pin to travel within the ramp slot and the vane to translate linearly.

Abstract: A variable guide vane assembly for a gas turbine engine stator is provided. The variable guide vane assembly includes a plurality of vanes and a plurality of RT mechanisms. The vanes extend between a shroud and hub. The vanes are circumferentially disposed and spaced apart from one another. Each vane includes inner and outer radial ends, and inner and outer radial posts. Each vane is pivotally mounted to rotate about its rotational axis. Each RT mechanism is in communication with the inner or outer radial post of a respective vane. The RT mechanism includes a pin connected to the vane that is disposed in a ramp slot non-rotational relative to the pivotable vane. The ramp slot extends between first and second lengthwise ends. Rotation of the vane relative to the ramp slot causes the pin to travel within the ramp slot and the vane to translate linearly.

Abstract: A gas turbine engine apparatus includes an engine flowpath, a protuberance and a variable vane. The protuberance projects into the engine flowpath. The variable vane extends across the engine flowpath. The variable vane includes a pivot axis and an airfoil. The variable vane is configured to pivot about the pivot axis between a first position and a second position. The airfoil extends spanwise along a span line between a first end and a second end. The airfoil extends chordwise along a chord line between a leading edge and a trailing edge. A recess extends spanwise into the airfoil from the first end. The airfoil, at the first end, is spaced from the protuberance when the variable vane is in the first position. The airfoil, at the first end, is aligned with the protuberance and the protuberance projects into the recess when the variable vane is in the second position.

Abstract: A variable guide vane assembly for a gas turbine engine stator is provided. The variable guide vane assembly includes a plurality of vanes and a plurality of RT mechanisms. The vanes extend between a shroud and hub. The vanes are circumferentially disposed and spaced apart from one another. Each vane includes inner and outer radial ends, and inner and outer radial posts. Each vane is pivotally mounted to rotate about its rotational axis. Each RT mechanism is in communication with the inner or outer radial post of a respective vane. The RT mechanism includes a pin connected to the vane that is disposed in a ramp slot non-rotational relative to the pivotable vane. The ramp slot extends between first and second lengthwise ends. Rotation of the vane relative to the ramp slot causes the pin to travel within the ramp slot and the vane to translate linearly.

Abstract: A variable guide vane (VGV) assembly for a gas turbine engine, has: variable guide vanes circumferentially distributed about a central axis, the variable guide vanes rotatable about respective spanwise axes; and a unison member rollingly engageable to a casing of the gas turbine engine for rotation about the central axis, the unison member operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, the unison member having: a first ring extending around the central axis, a second ring spaced apart from the first ring and extending around the central axis, and connecting members connecting the first ring to the second ring.

Abstract: A variable guide vane (VGV) assembly, has: vanes distributed about a central axis, each of the vanes having an airfoil extending between first and second stems, the vanes rotatable about vane axes extending between the first and second stems; and a bushing ring supporting the first stems of the vanes, the bushing ring defining circumferentially distributed pockets receiving the first stems of the vanes, the bushing ring having a first ring body extending circumferentially around the central axis, a second ring body extending circumferentially around the central axis and removably secured to the first ring body, the second ring body defining at least one tab projecting axially to axially overlap at least a portion of the first ring body and defining a contact plane therebetween, and at least one locking member extending radially through the contact plane to removably secure the first ring body and the second ring body together.

Abstract: The variable vane arm mechanism can have an actuator ring defined around a main axis, a set of vanes having a plurality of vanes circumferentially distributed around the main axis, each vane having a vane axis extending from an inner end to an outer end and being rotatable around the vane axis, each vane having a vane arm, a plurality of pins circumferentially distributed around a main axis, slide blocks engaged with corresponding ones of the pins in a manner to rotate around the pins, and guide slots having a length extending away from corresponding ones of the vane axes, each guide slot slidingly receiving a corresponding slide block.

Abstract: A gas turbine engine, has: an annular gaspath extending around a central axis, the annular gaspath defined between a first casing and a second casing, the first casing defining pockets; and a variable guide vane assembly having: variable guide vanes circumferentially distributed around the central axis, the variable guide vanes having airfoils extending into the annular gaspath and extending between first and second pivot members at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes, bushings received within the pockets of the first casing, the first pivot members of the variable guide vanes rollingly engaged to the bushings, and resilient members disposed radially between surfaces of the first casing and the bushings relative to the spanwise axes, the resilient members in abutment against both of the surfaces of the first casing and the bushings.

Abstract: The variable vane arm mechanism can have an actuator ring defined around a main axis, a set of vanes having a plurality of vanes circumferentially distributed around the main axis, each vane having a vane axis extending from an inner end to an outer end and being rotatable around the vane axis, each vane having a vane arm, a plurality of pins circumferentially distributed around a main axis, slide blocks engaged with corresponding ones of the pins in a manner to rotate around the pins, and guide slots having a length extending away from corresponding ones of the vane axes, each guide slot slidingly receiving a corresponding slide block.

Abstract: A gas turbine engine has: an annular gaspath extending around a central axis and defined between a first casing and a second casing; and a variable guide vane (VGV) assembly having: variable guide vanes, the variable guide vanes having airfoils extending between first and second stems at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes; a unison ring rotatable about the central axis, the unison ring operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, and a segmented bushing having bushing segments circumferentially distributed around the central axis, the bushing segments radially supported and axially constrained by the first casing, the unison ring rollingly engaged to the first casing via the bushing segments, the unison ring axially and radially constrained to the first casing via the bushing segments.

Abstract: A variable guide vane (VGV) described herein includes an airfoil for interacting with a fluid inside a gas path of a gas turbine engine. The airfoil is mounted to a button and rotatable with the button about an axis. The button includes a platform surface defining part of the gas path adjacent the airfoil during use. The platform surface of the button includes a depression for receiving therein part of an adjacent VGV and providing clearance between adjacent VGVs at aggressive vane angles.

Abstract: A gas turbine engine, has: an annular gaspath extending around a central axis, the annular gaspath defined between a first casing and a second casing, the first casing defining pockets; and a variable guide vane assembly having: variable guide vanes circumferentially distributed around the central axis, the variable guide vanes having airfoils extending into the annular gaspath and extending between first and second pivot members at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes, bushings received within the pockets of the first casing, the first pivot members of the variable guide vanes rollingly engaged to the bushings, and resilient members disposed radially between surfaces of the first casing and the bushings relative to the spanwise axes, the resilient members in abutment against both of the surfaces of the first casing and the bushings.

Abstract: A variable guide vane (VGV) assembly for a gas turbine engine has: vanes distributed about a central axis and having airfoils between stems at respective ends of the airfoils; a unison ring; sliders protruding from the unison ring; and vane arms engaged to first stems and defining respective slots, each of the slots extending in a direction having a radial component relative to a respective one of the spanwise axes, the sliders received within respective ones of the slots, a slot extending from a proximal end to a distal end along a slot axis, the vane arm defining the slot having an end wall at the distal end, the end wall extending in a direction having a component transverse to the slot axis such that a slider abuts against the end wall when the slider is at the distal end to prevent the sliders from moving out of the slots.

Abstract: A variable guide vane (VGV) described herein includes an airfoil for interacting with a fluid inside a gas path of a gas turbine engine. The airfoil is mounted to a button and rotatable with the button about an axis. The button includes a platform surface defining part of the gas path adjacent the airfoil during use. The platform surface of the button includes a depression for receiving therein part of an adjacent VGV and providing clearance between adjacent VGVs at aggressive vane angles.

Abstract: A variable guide vane (VGV) assembly for a gas turbine engine has: vanes distributed about a central axis and having airfoils between stems at respective ends of the airfoils; a unison ring; sliders protruding from the unison ring; and vane arms engaged to first stems and defining respective slots, each of the slots extending in a direction having a radial component relative to a respective one of the spanwise axes, the sliders received within respective ones of the slots, a slot extending from a proximal end to a distal end along a slot axis, the vane arm defining the slot having an end wall at the distal end, the end wall extending in a direction having a component transverse to the slot axis such that a slider abuts against the end wall when the slider is at the distal end to prevent the sliders from moving out of the slots.

Abstract: A variable guide vane (VGV) assembly for a gas turbine engine, has: variable guide vanes circumferentially distributed about a central axis, the variable guide vanes rotatable about respective spanwise axes; and a unison member rollingly engageable to a casing of the gas turbine engine for rotation about the central axis, the unison member operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, the unison member having: a first ring extending around the central axis, a second ring spaced apart from the first ring and extending around the central axis, and connecting members connecting the first ring to the second ring.

Abstract: A gas turbine engine has: an annular gaspath extending around a central axis and defined between a first casing and a second casing; and a variable guide vane (VGV) assembly having: variable guide vanes, the variable guide vanes having airfoils extending between first and second stems at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes; a unison ring rotatable about the central axis, the unison ring operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, and a segmented bushing having bushing segments circumferentially distributed around the central axis, the bushing segments radially supported and axially constrained by the first casing, the unison ring rollingly engaged to the first casing via the bushing segments, the unison ring axially and radially constrained to the first casing via the bushing segments.

Abstract: A variable guide vane (VGV) assembly, has: vanes distributed about a central axis, each of the vanes having an airfoil extending between first and second stems, the vanes rotatable about vane axes extending between the first and second stems; and a bushing ring supporting the first stems of the vanes, the bushing ring defining circumferentially distributed pockets receiving the first stems of the vanes, the bushing ring having a first ring body extending circumferentially around the central axis, a second ring body extending circumferentially around the central axis and removably secured to the first ring body, the second ring body defining at least one tab projecting axially to axially overlap at least a portion of the first ring body and defining a contact plane therebetween, and at least one locking member extending radially through the contact plane to removably secure the first ring body and the second ring body together.