A variable vane system including an actuator; a harmonic drive driven by the actuator, a multi-planar drive gear driven by the harmonic drive, a first actuator gear mounted to a first variable vane of a first variable vane stage, the first actuator gear driven by the multi-planar drive gear, the first actuator gear comprises a drive arm, and a second actuator gear mounted to a second variable vane of a second variable vane stage, the second actuator gear driven by the multi-planar drive gear.

A blade for an axial flow machine having a pressure surface, suction surface and trailing edge. The blade has a cross-sectional aerofoil profile including: a region of maximum curvature corresponding to the trailing edge of the blade and defining a trailing edge radius of curvature r; a trailing edge region extending from the trailing edge and having a chordwise extent equal to curvature r's trailing edge radius; a taper region adjacent the trailing edge region, the taper region having a chordwise extent greater than the curvature r's trailing edge radius and no more than 15% of the blade's chord; a body region adjacent the taper region; a pressure surface boundary corresponding to the blade's pressure surface; and a suction surface boundary corresponding to the blade's suction surface. A thickness between the pressure and suction surface boundaries reduces within the taper region towards the trailing edge by at least 50%.

A method of forming a strengthened component includes providing a duct body having an interior surface and an exterior surface forming a fluid passageway. The method also includes forming an attachment structure over at least a portion of the exterior surface of the duct body, where the attachment structure can include a metallic layer.

Disclosed is a flutter damper, including an acoustic liner in fluid communication with a fluid flow the acoustic liner being configured for peak acoustical energy absorption at a frequency range greater than a frequency range associated with fan flutter, and a plurality of modular chambers configured for peak acoustical energy absorption at a frequency range associated with one or more fan flutter modes, the plurality of modular chambers disposed radially outside the acoustic liner, the plurality of modular chambers including a circumferential gap between proximate circumferential ends of at least one adjacent pair of modular chambers, and the plurality of modular chambers each including a plurality of circumferentially aligned and connected chamber segments, and wherein at least one of the chambers in the plurality of modular chambers has a mutually unique length, width and/or height or shape.

An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings.

A turbine blade having a labyrinth of internal channels for circulation of coolant received through an inlet formed in a terminal portion of a blade root. A labyrinth geometry includes: (i) the inlet arranged on an axially upstream face of the terminal portion leading to an upstream duct portion having a first section adjacent the inlet and a second section having a reduced cross-section compared to the first section, (ii) a leading edge passage intersecting with the first section and extending through a blade body towards a tip of the blade, where a proximal end of the leading edge passage is angled towards a direction of incoming air flow, (iii) a main blade passage intersecting with a downstream duct portion arranged in axial alignment with, and separate from, the upstream duct portion, and (iv) a restrictor passage intersecting with a mid-blade passage and extending towards a mid-blade duct portion.

An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.

An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.

An inlet cone for an aircraft turbomachine, having at least one first portion made of a first material, referred to as rigid material, and at least one second portion made of a second material which has a hardness less than that of said first material and which is referred to as flexible material, these second portions being configured to deform elastically in the radial direction with respect to the axis when the cone is being driven to rotate.

A blended wing aircraft including a blended wing fuselage and at least one embedded gas turbine engine in the fuselage. The gas turbine engine includes an inlet duct formed with a generally elliptical shape that includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct. The inlet duct includes a vertical centerline. The first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections. The area of the second set of ellipse sections increases toward a downstream end of the inlet duct. A fan section has an axis of rotation that is spaced from the vertical centerline and is disposed within an inlet duct orifice. The inlet duct is upstream of the fan section.