This composite material blade, which is formed using a composite material including reinforcing fibers and resin, and which has a positive pressure surface and a negative pressure surface, is provided with a ventral part, being the part on the positive pressure surface side in a blade thickness direction, which is the direction joining the positive pressure surface and the negative pressure surface, a dorsal part, being the part on the negative pressure surface side in the blade thickness direction, and a metal shield portion which is provided on the leading edge side, being the upstream side in a flow direction in which a fluid flows, wherein: the metal shield portion includes a main body portion provided on the leading edge side, and an embedded portion which is provided on the trailing edge side, being the downstream side in the flow direction, of the main body portion, and which is provided between the ventral part and the dorsal part; and the plate thickness of the metal shield portion in the blade thickness direction decreases from the main body portion toward the embedded portion.

An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.

A gas turbine engine includes: a fan rotating about an engine main axis; a core duct; an engine core; an Engine Section Stator (ESS) including a plurality of ESS vanes and arranged in the core duct downstream of the fan; and a plurality of variable inlet guide vanes (VIGV) adapted to rotate about a pivot axis and arranged in the core duct downstream of the ESS. The VIGV vanes are arranged angularly rotated with respect to the ESS vanes such that the VIGVs are shielded by the ESS, thereby protecting the VIGVs from icing and from ice shedding from the ESS vanes.

A nozzle guide vane for a gas turbine engine having a combined side wall thickness value which varies within a cavity region so as to provide a point with a maximum value of combined side wall thickness, which is advantageous for capturing debris travelling through the engine core.

An air turbine starter comprising a housing defining an inlet, an outlet, and a flow path, a turbine having a rotor with circumferentially spaced blades extending into the flow path, a drive shaft operably coupled to and rotating with the rotor, and at least one vane located within the flow path, upstream of the blades. The at least one blade being defined by an acute axial angle and an acute tangential angle.

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

An airfoil includes a root and a tip, which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The airfoil also includes a thermal barrier coating on the pressure side surface and the suction side surface. The thermal barrier coating includes a base layer and a top coat. A thickness of the base layer varies across each of the pressure side surface and the suction side surface with a maximum thickness of the base layer at the leading edge.

Airfoil for gas turbine engines are described. The airfoils have internal walls and internal cavities. A leading edge cavity is defined within the airfoil body along a leading edge and a leading edge feed cavity is arranged aft of the leading edge cavity. A bent leading edge rib is arranged between the leading edge cavity and the leading edge feed cavity. A main body cavity is arranged aft of the leading edge feed cavity and defined at least in part by two interior ribs that define a part of the leading edge feed cavity. The main body cavity is fluidly connected to the leading edge feed cavity by an interior fluid connection through the intersection of the two interior ribs. A shield cavity is arranged to thermally shield the leading edge feed cavity from heat pickup along the suction side of the airfoil body.

Embodiments of the present disclosure provide a blade-stator system and the vertical take-off and landing flight apparatus comprising the blade-stator system, the blade-stator system including a duct disposed inside a flight body, upper and lower sides of the duct being open, and an inside of the duct being hollow; a blade assembly installed rotatably inside the duct and including a blade body of which an angle is changeable; a stator assembly connected to the blade assembly and the duct, supporting the blade assembly, and rotatable by a predetermined angle; a controller electrically connected to the blade assembly and the stator assembly and configured to control driving of the blade body and the stator assembly, wherein the angle of the stator assembly is changed in response to receiving an electrical signal from the controller so as to be interlocked with a change of the angle of the blade body.

The disclosure relates to a gas turbine engine and a method of controlling an upstream extent of a bow wave from an airfoil having a pressure side and a suction side in the turbine engine. In one aspect, the method includes forming a vortex at a leading edge of the airfoil.