Abstract: An actuation assembly for concentric variable stator vanes of a rotary component of a gas turbine engine. The actuation assembly includes an inner casing and an intermediate casing defining a first concentric flowpath extending between the inner casing and the intermediate casing. The actuation assembly includes an outer casing defining a second concentric flowpath extending between the intermediate casing and the outer casing. The actuation assembly includes a first variable stator vane extending radially inward from the intermediate casing into the first concentric flowpath. The actuation assembly includes a second variable stator vane extending radially within the second concentric flowpath between a distal end at the outer casing and proximate end at the inner casing and defining a cavity extending therebetween. A first trunnion extends radially inward from the outer casing through the cavity of the second variable stator vane and is drivingly coupled to the first variable stator vane.

Abstract: An apparatus for an aircraft engine that is configured for actively adjusting physical characteristics of an airfoil. The apparatus includes an airfoil that has a body and a filler that is embedded within the body. A source for electromagnetic energy is positioned in a portion of the engine and configured to generate electromagnetic energy having a predetermined range which encompasses the airfoil. A physical property of the filler is configured to change between a first state in the absence of electromagnetic energy and a second state in the presence of electromagnetic energy. The airfoil has a first airfoil characteristic when the filler is in the first state and the airfoil has a second airfoil characteristic when the filler is in the second state.

Abstract: An airfoil assembly for a turbo machine, the airfoil assembly including an airfoil defining a leading edge and a trailing edge, and further defining ends separated along a span of the airfoil; a shaft extended from the end of the airfoil; and a button surrounding at least a portion of the end of the airfoil, the button comprising a composite material.

Abstract: A system for operating a turbo machine is generally provided, the system including a variable vane assembly including a first plurality of vanes coupled together by a first unison member and a second plurality of vanes coupled together by a second unison member. An actuation system is coupled to each of the first unison member and the second unison member and a solenoid actuator is coupled to the variable vane assembly and the actuation system.

Abstract: A system for operating a turbo machine is generally provided, the system including a variable vane assembly including a first plurality of vanes coupled together by a first unison member and a second plurality of vanes coupled together by a second unison member. An actuation system is coupled to each of the first unison member and the second unison member and a solenoid actuator is coupled to the variable vane assembly and the actuation system.

Abstract: An airfoil assembly for a turbo machine, the airfoil assembly including an airfoil defining a leading edge and a trailing edge, and further defining ends separated along a span of the airfoil; a shaft extended from the end of the airfoil; and a button surrounding at least a portion of the end of the airfoil, the button comprising a composite material.

Abstract: A circular row of non-uniformally spaced vanes includes only one first group and only one second group of adjacent vanes, unequal first and second spacing between adjacent vanes in the first and second groups, and first spacing greater than second spacing. An embodiment with second group including only three adjacent vanes. Second spacing may be about 25%-35% smaller than a nominal uniform spacing used as a design parameter for designing spacing of the non-uniformly spaced stator vanes. Circular row may be sectored. A gas turbine engine section may include one or more rings or circular rows of fixed and/or variable non-uniformally spaced vanes. Method for designing non-uniform vane spacing for circular row includes determining nominal uniform spacing and forming first spacing and second spacing from nominal uniform spacing of vanes.

Abstract: An apparatus for an aircraft engine that is configured for actively adjusting physical characteristics of an airfoil. The apparatus includes an airfoil that has a body and a filler that is embedded within the body. A source for electromagnetic energy is positioned in a portion of the engine and configured to generate electromagnetic energy having a predetermined range which encompasses the airfoil. A physical property of the filler is configured to change between a first state in the absence of electromagnetic energy and a second state in the presence of electromagnetic energy. The airfoil has a first airfoil characteristic when the filler is in the first state and the airfoil has a second airfoil characteristic when the filler is in the second state.

Abstract: A circular row of non-uniformally spaced vanes includes only one first group and only one second group of adjacent vanes, unequal first and second spacing between adjacent vanes in the first and second groups, and first spacing greater than second spacing. An embodiment with second group including only three adjacent vanes. Second spacing may be about 25%-35% smaller than a nominal uniform spacing used as a design parameter for designing spacing of the non-uniformly spaced stator vanes. Circular row may be sectored. A gas turbine engine section may include one or more rings or circular rows of fixed and/or variable non-uniformally spaced vanes. Method for designing non-uniform vane spacing for circular row includes determining nominal uniform spacing and forming first spacing and second spacing from nominal uniform spacing of vanes.

Abstract: A guide vane assembly for a gas turbine engine includes: a strut having: a root, a tip, a leading edge, a trailing edge wall, and opposed sidewalls extending between the leading edge and the trailing edge wall; and a pair of spaced-apart prongs extending axially aft from the trailing edge wall, each prong having an outer wall that is flush with a respective one of the sidewalls; and a flap positioned axially aft of the strut, the flap having a root, a tip, a leading edge, a trailing edge, and opposed sides extending between the leading and trailing edge, wherein a portion of the leading edge is disposed between the prongs, and wherein a disk-like flap button is disposed at the tip of the flap adjacent its leading edge, the flap button including a pair of spaced-apart notches formed therein.

Abstract: A variable stator vane airfoil is mounted on a button centered about a rotational axis and includes circular leading and trailing edges circumscribed about the rotational axis at a button radius. Contoured pressure and suction sides extend from the circular leading edge to the circular trailing edge and are recessed inwardly from a perimeter circumscribed about the rotational axis at the button radius. One of upstream and downstream pressure side portions of the contoured pressure side is straight and another of the upstream and downstream pressure side portions is convexly curved. One of the upstream and downstream suction side portions is straight and another of the upstream and downstream suction side portions is convexly curved. One of the upstream pressure side portion and upstream suction side portion is straight and another of the upstream pressure side portion and upstream suction side portion is convexly curved.

Abstract: A variable stator vane airfoil is mounted on a button centered about a rotational axis and includes circular leading and trailing edges circumscribed about the rotational axis at a button radius. Contoured pressure and suction sides extend from the circular leading edge to the circular trailing edge and are recessed inwardly from a perimeter circumscribed about the rotational axis at the button radius. One of upstream and downstream pressure side portions of the contoured pressure side is straight and another of the upstream and downstream pressure side portions is curved. One of the upstream and downstream suction side portions is straight and another of the upstream and downstream suction side portions is curved. One of the upstream pressure side portion and upstream suction side portion is straight and another of the upstream pressure side portion and upstream suction side portion is curved.

Abstract: A turbofan gas turbine engine includes a forward fan section with a row of fan rotor blades, a core engine, and a fan bypass duct downstream of the forward fan section and radially outwardly of the core engine. The forward fan section has only a single stage of variable fan guide vanes which are variable fan outlet guide vanes downstream of the forward fan rotor blades. An exemplary embodiment of the engine includes an afterburner downstream of the fan bypass duct between the core engine and an exhaust nozzle. The variable fan outlet guide vanes are operable to pivot from a nominal OGV position at take-off to an open OGV position at a high flight Mach Number which may be in a range of between about 2.5-4+. Struts extend radially across a radially inwardly curved portion of a flowpath of the engine between the forward fan section and the core engine.

Abstract: A rotor assembly for a gas turbine engine operates with reduced circumferential rim stress. The rotor assembly includes a rotor including a plurality of rotor blades extending radially outward from an annular rim. A root fillet extends circumferentially around each blade between the blades and rim. The rim includes an outer surface including a plurality of concave indentations extending between adjacent rotor blades and forming a compound radius. Each indentation extends from a leading edge of the rotor blades towards a trailing edge of the rotor blades.