A composite blade formed by laying up composite material layers in which reinforced fibers are impregnated with resin in a blade thickness direction includes a blade root provided on a base side, an airfoil extending from a tip side of the blade root, a metal member provided on the blade root, and a fastener configured to fasten the blade root and the metal member. The blade root includes a main body portion, a curved portion that is curved outward in the blade thickness direction from the main body portion, and an extending portion that extends outward in the blade thickness direction from the curved portion. The metal member is fixed to the extending portion with the fastener.

An airfoil cooling structure, an airfoil having the airfoil cooling structure, and a turbine blade/vane element including the airfoil are disclosed. The airfoil cooling structure includes a cooling path formed inside the airfoil and having a first surface and a second surface opposite to the first surface, and an additive manufactured (AM) feature disposed in the cooling path, manufactured by additive manufacturing, and including a plurality of column parts intersecting with each other so as to abut against the first surface and the second surface.

An ascertainment method for determining a final angle of vanes that are adjustable between an initial angle and the final angle and are part of a row of leading vanes which are arranged upstream of a row of trailing vanes of a compressor in a gas turbine, in order to prevent ice from forming in the compressor. During operation of the gas turbine, a current value of at least one process parameter is determined in a parameter ascertainment step, whereupon the final angle is defined in accordance with the value in a final-angle defining step, an aerodynamic speed being determined as the process parameter.

A gas turbine engine includes a core turbine engine and a fan mechanically coupled to the core turbine engine. The fan includes a plurality of fan blades, each fan blade defining a base and an inner end along a radial direction of the gas turbine engine. The fan also includes a hub covering the base of each of the plurality of fan blades. Further, the fan includes one or more bearings for supporting rotation of the plurality of fan blades. The one or more bearings define a fan bearing radius along a radial direction of the gas turbine engine. Similarly, the hub defines a hub radius along the radial direction of the gas turbine engine. The ratio of the hub radius to the fan bearing radius is less than about three, providing for desired packaging of the various components within the fan of the gas turbine engine.

A turbine housing includes: a housing body which includes a turbine housing part housing a turbine wheel, an inlet section forming an inlet flow passage for guiding exhaust gas to the turbine housing part, an outlet section forming an outlet flow passage for discharging the exhaust gas from the turbine housing part, and a waste-gate flow passage which brings the inlet flow passage and the outlet flow passage into communication so as to bypass the turbine housing part; and a sleeve disposed along an inner wall surface of the housing body forming the waste gate flow passage, at least on a downstream side of the waste-gate flow passage of the housing body with respect to a flow direction of the exhaust gas.

A gas turbine engine casing comprising: an inner circumferential wall; an outer circumferential wall spaced radially outwardly from the inner wall; wherein the inner and outer circumferential walls are formed by an axially repeating profile comprising an inner wall portion and an outer wall portion connected to one another by an intermediate portion, the axially repeating profile being arranged such that the inner wall portion abuts against and is connected to an adjacent inner wall portion to form the inner circumferential wall and the outer wall portion abuts against and is connected to an adjacent outer wall portion to form the outer circumferential wall.

A lightweight fan blade for use in turbofan gas turbine engines is disclosed. The fan blade includes a metallic airfoil connected to a root. The airfoil has a pressure side and a suction side. The suction side of the airfoil includes one or more cavities for weight reduction purposes. A cover is attached to the suction side of the body to cover or enclose the one or more cavities. In addition to the one or more cavities, through holes are formed from the inner face of the root into one or more of the cavities for further weight reduction. The through holes may be covered by a spacer and one or more through holes may be extended from the inner face of the root into each of the cavities.

In a structure for cooling a gas turbine engine, an open flange part encircling a fuel supply hole formed in a combustor includes a conical portion enlarging in a conical shape toward an outside of the combustor and a flat portion extending radially outward in a flat plate shape from an extremity of the conical portion, and a nozzle guide includes a cylindrical portion covering an outer periphery of a fuel nozzle for supplying fuel to the fuel supply hole and a bottom flange portion being bent radially outward from a corner portion at an extremity of the cylindrical portion and supported in a floating state on the flat portion. A cooling hole for supplying air that cools the open flange part and the nozzle is formed in the corner portion of the guide, and a direction of the cooling hole is inclined toward an axis of the nozzle.

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbinethe compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.