The invention relates to a profiled structure elongated in a direction in which the structure has a length exposed to an airflow and transversely to which the structure has a leading edge and/or a trailing edge, at least one of which is profiled and has, along said direction of elongation, geometric serration patterns defined by a succession of peaks and troughs. Along the profiled leading edge and/or trailing edge, the serration patterns have a geometric pattern that is repeated in the direction of elongation, the shape of which is stretched and/or contracted transversely to the direction of elongation and/or in the direction of elongation.

An engine section stator for a gas turbine engine having a compressor, a combustor, and a turbine. The engine section stator includes an inner band, an outer band spaced radially outwardly from the inner band, and a series of spaced apart aerofoils extending the inner and outer bands. The engine section stator includes a stiffness feature that extends away from one of the inner and outer bands of the engine section stator. The stiffness feature configured to increase the high cycle fatigue strength of the aerofoils without impeding airflow passing between the inner and outer bands.

The present invention relates to a blower, the blower according to an embodiment of the present invention comprising: a lower case having a suction hole formed therein through which air is introduced; an upper case arranged on the upper side of the lower case and having a discharge hole formed therein through which air is discharged; and a fan arranged in the lower case and including a plurality of blades. Each of the plurality of blades includes a plurality of airfoils respectively extending along different camber lines from one another, and a leading edge of connecting the leading ends of the plurality of airfoils. Entrance angles formed by the respective camber lines of the plurality of airfoils and the rotation directions of the blades are different from one another. Thus, due to the curved shape of the leading edge and the design of a recessed notch, a flow separating from the leading edge is reduced, and thus, there is an advantage in that air volume performance is improved.

Provided is a gas turbine vane and blade assembly in which lattice structures are installed between an impingement plate and an effusion plate. The gas turbine vane and blade assembly is capable of enhancing cooling efficiency in an impingement/effusion cooling technique.

In addition, the gas turbine vane and blade assembly can be manufactured using an additive manufacturing technique, and the lattice structures are capable of replacing supports that are used during an additive manufacturing process, and improving not only structural rigidity and stability but also cooling performance.

A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner diameter to an outer diameter and having an airfoil-shaped cross section having a leading edge and a trailing edge, and a pressure side and a suction side each of which extends from the leading edge to the trailing edge, wherein the turbine nozzle may include a hollow airfoil including a plurality of cavities positioned in the airfoil, an insert positioned in one or more of the plurality of cavities of the hollow airfoil, a plurality of cover plates, at least one of which is positioned at one of the inner diameter and at the outer diameter, and a plurality of impingement pans, at least one of which is positioned at one of the inner diameter and at the outer diameter.

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 gas turbine has blades. A blade may have a leading edge; a trailing edge; a pressure side and a suction side, which extend between the leading edge and the trailing edge. The blade has, along the leading edge, a leading edge profile with profile portions, each of which, along its profile portion length, transitioning, proceeding from a depression, into an elevation via a first transition portion and back into a next depression via a second transition portion. An apex of the elevation of a profile portion is arranged in an asymmetric manner in relation to the profile portion length, in such a way that the first transition portion has a first transition length and the second transition portion has a second transition length. The first transition length and the second transition length are different lengths.

A gas turbine has blades. A blade may have a leading edge; a trailing edge; a pressure side and a suction side, which extend between the leading edge and the trailing edge. The blade has, along the leading edge, a leading edge profile with profile portions, each of which, along its profile portion length, transitioning, proceeding from a depression, into an elevation via a first transition portion and back into a next depression via a second transition portion. An apex of the elevation of a profile portion is arranged in an asymmetric manner in relation to the profile portion length, in such a way that the first transition portion has a first transition length and the second transition portion has a second transition length. The first transition length and the second transition length are different lengths.

An assembly includes a variable area inlet and an inlet duct. The variable area inlet includes an inlet structure and a center body structure. The inlet structure extends circumferentially about the center body structure with an outer inlet passage radially between the center body structure and the inlet structure. The center body structure includes an outer body and an inner body. The outer body extends circumferentially about the inner body with an inner inlet passage radially between the inner and outer bodies. The inner body is configured to move along a centerline relative to the outer body between a first position and a second position. The inlet duct is fluidly coupled with the outer inlet passage when the inner body is in the first position. The inlet duct is fluidly coupled with the outer inlet passage and the inner inlet passage when the inner body is in the second position.

A guide vane arrangement configured for use in a turbo pump, wherein the guide vane arrangement includes a first guide vane and a second guide vane, wherein the second guide vane is arranged adjacent to the first guide vane such that a flow channel is defined between a leading surface of the first guide vane and a trailing surface of the second guide vane. The trailing surface of the second guide vane comprises a trailing portion which is arranged adjacent to a trailing edge of the second guide vane and which is arranged at a first angle with respect to a virtual plane defined by a trailing edge of the first guide vane and the trailing edge of the second guide vane, a leading portion which is arranged adjacent to a leading edge of the second guide vane and which is arranged at a second angle with respect to the virtual plane defined by the trailing edge of the first guide vane and the trailing edge of the second guide vane, the second angle being larger than the first angle, and an intermediate portion which is arranged between the trailing portion and the leading portion and which is arranged at a third angle with respect to the virtual plane defined by the trailing edge of the first guide vane and the trailing edge of the second guide vane, the third angle being smaller than the first angle.