A system includes a turbine exhaust section. The turbine exhaust section includes an exhaust flow path. The turbine exhaust section also includes an inner exhaust wall radially disposed along the exhaust flow path and an outer exhaust wall disposed along the exhaust flow path and radially outward from the inner exhaust wall. The turbine exhaust section includes an inner flow control vane configured to selectively extend radially outward from the inner exhaust wall. An inner radial extent of the inner flow control vane is less than a radial distance between the inner exhaust wall and the outer exhaust wall. The inner flow control vane is disposed downstream of a last stage blade of a turbine and upstream of an exhaust diffuser strut of the turbine exhaust section.

A number of variations may include a product comprising: a vane lever comprising a first end, a second end, a top surface, and a bottom surface; an opening which extends through the second end and which is defined by an inner surface, and wherein a perimeter of the inner surface comprises a plurality of vertical flutes which extend a length of the inner surface and which are constructed and arranged to displace a material of a vane shaft.

An air modulating system for a gas turbine engine includes a fixed plate with a fluid passage inlet, a floating plate with a first side adjacent to the fluid passage inlet, an actuated mount configured to move the floating plate relative to the fixed plate, and a linkage element for connecting the floating plate to the actuated mount. The linkage element includes a mounting flange configured to slidably engage the floating plate.

A turbine assembly comprising a housing comprising first and second volutes which define a respective first and second flow passage. A circumferential outlet portion of each volute is defined by first and second tongues. The housing further comprises a first aperture in which a vane assembly is received. The vane assembly comprises a plurality of vanes circumferentially distributed about a turbine wheel-receiving bore, each vane comprising a leading edge and a trailing edge. Each vane has a fixed orientation. The vanes comprise a first vane and a second vane. The first vane having its leading edge disposed in closest proximity to a tip of the first tongue. The second vane having its leading edge disposed in closest proximity to a tip of the second tongue. The leading edge of each vane at least partly overlaps the tip of the proximate tongue circumferentially.

An inlet guide vane assembly is disclosed, which comprises: a housing, configured with a first penetration part and a plurality of first grooves; at least one fixing ring, each configured with a second penetration part and a plurality of second grooves; at least one rotary ring, each configured with a third penetration part and a plurality of sliding chutes, wherein the first, the second and the third penetration parts are arranged in communication with one another; a plurality of vane units, each vane unit is composed of a vane, a linkage and a sliding block; and at least one driving unit, for driving one vane of the plural vanes to swing, thus driving the rotary ring to rotate simultaneously, bringing along the other vanes to swing, enabling the sliding blocks to slide inside corresponding sliding chutes, and consequently flipping the vane from a first state to a second state.

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.

Nozzle rings for variable geometry turbines comprise: a generally annular wall; an inner flange; an outer flange; and two protrusions. Inner flange is generally perpendicular to the generally annular wall, from which a radially inner edge extends. Outer flange is generally perpendicular to the generally annular wall and extends from a radially outer edge of the generally annular wall. The two protrusions extend from one of the inner or outer flange towards the other one of the inner or outer flange. At least one of the two protrusions extends only partially towards the other one of the inner or outer flange. The two protrusions define a first gap therebetween. Generally annular wall and the two protrusions define a second gap therebetween to receive a support arcuate head portion during use. First gap receives a support intermediate portion. The nozzle rings may be suitable for use in variable geometry turbochargers.

A method for managing mismatches in feedback from guide vane sensors of a turbine engine with variable guide vanes includes selectively muting individual feedback channels and obtaining time series turbine performance data of the turbine engine associated with individual feedback channels. The feedback channel of the guide vane sensor associated with the best performing time series performance data can be selected as sole feedback channel following detection of a mismatch condition.

An assembly for an aircraft propulsion system includes a propulsor rotor and a guide vane structure. The guide vane structure includes a plurality of guide vanes. The guide vane structure is disposed axially next to the propulsor rotor. The guide vanes include a first guide vane. The first guide vane includes a camber line, a leading edge, a trailing edge, an inner end, an outer end, at least one leading edge section and a trailing edge section. The first guide vane extends longitudinally along the camber line from the leading edge to the trailing edge. The leading edge section forms a respective portion of the leading edge and is arranged radially along the trailing edge section between the inner end and the outer end. The trailing edge section forms the trailing edge. The leading edge section is configured to translate longitudinally along the camber line.