Abstract: Provided is a protective cover system including a first protective cover and a second protective cover, both include a polymer and being pre-formed into a curved shape so as to accommodate at least a part of a wind turbine blade to be protected, each of the first and second protective covers has a tip end and a root end, wherein the first protective cover includes a first overlap portion at the root end, and the second protective cover includes a second overlap portion at the tip end, wherein the shape of the first overlap portion is substantially complementary to the shape of the second overlap portion such that when overlapping the first and second overlap portions, the resulting cross section of the overlapped overlap portions substantially corresponds to the cross sections of at least one of the first and second protective covers outside the overlap portions.

Abstract: An air moving device according to the present disclosure can include a housing and an installation hub. The housing can be connected to the installation hub via one or more adjustable supports. An impeller can be installed at least partially in the housing and configured to direct air out of the housing. In some embodiments, the adjustable supports can be adjusted to move the housing with respect to the installation hub. For example, the adjustable supports can be configured to modify the tilt of the housing and/or the overall distance between the housing and the installation hub. The installation hub can be installed on a ceiling, wall, or other mounting surface. Adjustment of the adjustable supports can permit vertical alignment of the air moving device housing, even when the installation hub is mounted to a slanted or sloped (e.g., non-horizontal) ceiling or wall.

Abstract: A gas turbine engine includes rotor having a hub, and a plurality of blades extending generally radially from the hub. Each of the blades has an airfoil portion. The airfoil portion has a leading edge and a trailing edge defining a chordwise direction, and a root and a tip defining a spanwise direction. Only a sub-set of the blades has a cutback at at least one of the trailing edge and the leading edge. A method of designing and a method of assembling a rotor having noise reduction properties in a gas turbine engine is also presented.

Abstract: A gas turbine nozzle assembly of a gas turbine is provided. The turbine nozzle assembly may include a turbine nozzle extending from an inner platform to an outer platform 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 plurality of vanes attached to the inner and outer platforms and the inner platform having an attached first and second endfaces and a flow surface surrounding opposing ends of a vane of the plurality of vanes, the flow surface terminating circumferentially at the first and second endfaces and terminating axially at forward and aft edges, and the inner platform may include a platform corner portion comprising the flow surface attached to the first endface at the forward edge and attached to the second endface at the aft edge.

Abstract: There is provided a method of operating a wind turbine which has at least two rotor blades. A first ice detection method is performed by a first ice accretion detection unit. A first warning signal is output if an ice accretion which exceeds a first threshold value is detected at one of the rotor blades by the first ice detection method. A second ice detection method is performed by a second ice accretion detection unit. A second warning signal is output if an ice accretion which exceeds a second threshold value is detected at one of the rotor blades by the second ice detection method. An enable signal is output if a freedom from ice is detected at the at least two rotor blades by the second ice detection method. Intervention in the operation of the wind turbine is effected by a control unit if the first or second warning signal has been detected.

Abstract: A nacelle for housing a fan within a gas turbine engine having a longitudinal centre line includes a leading edge and a trailing edge. A nacelle length (Lnac) is defined as an axial distance between the leading edge and the trailing edge. An azimuthal angle (?) is defined about the longitudinal centre line. The nacelle length (Lnac) varies azimuthally. The nacelle length (Lnac) decreases azimuthally from an inboard end of the nacelle to an outboard end of the nacelle.

Abstract: A vane for use in a gas turbine engine includes an airfoil having a suction side and a pressure side, and a transpirational flow acoustic liner disposed in the airfoil. The liner includes a face sheet defining a portion of an outer surface of the airfoil and having a plurality of first apertures, a segmented member coupled to the face sheet, and a backing sheet coupled to the segmented member the segmented member such that the segmented member is positioned between the face sheet and the backing sheet. The segmented member includes a plurality of chambers in fluid communication with the outer surface via the plurality of first apertures. The backing sheet has a plurality of second apertures.

Abstract: Disclosed is a wind turbine blade having a blade de-icing system. The blade de-icing system comprises: a first channel longitudinally extending from a first position to a second position, wherein the second position is between the tip end and the first position; and a heating channel longitudinally extending from the second position to the first position along the leading edge of the wind turbine blade, the heating channel and the first channel being in fluid connection. The blade de-icing system is arranged to provide a flow of heated fluid through the first channel and the heating channel, the flow of heated fluid through the heating channel having a main flow direction along a longitudinal direction of the wind turbine blade, and wherein the blade de-icing system is configured to affect the flow of heated fluid through the heating channel resulting in a rotational flow of the heated fluid about the main flow direction.

Abstract: An air circulator includes a blower unit that is provided with an airflow opening on its front side, and a support unit that supports the blower unit. A grill is provided in the airflow opening. The grill is provided with plural airflow guide blades in a spiral manner. Inner end portions thereof closer to the center of the spiral of the airflow guide blades are protruded from outer end portions thereof in an airflow direction. The blower unit has a cover for forming an outer panel thereof, and the cover has a spherical shape.

Abstract: A steam turbine 1 includes a turbine body 11 which includes a rotor 5 which is configured to rotate around an axis Ac, and a casing 6 which covers the rotor 5 to form a flow path through which steam flows in an axis Ac direction, together with the rotor 5, a thermal insulation member 12 which is provided to be in contact with an outer surface of the casing 6 in a high-pressure side region 61 out of the high-pressure side region 61 and a low-pressure side region 62 of the steam in the axis Ac direction of the casing 6, and a soundproof cover 13 which covers the low-pressure side region 62 out of the high-pressure side region 61 and the low-pressure side region 62 via a space between the outer surface of the casing 6 and the soundproof cover 13.

Abstract: A turbo machine, a computer-implemented method, and a computer system for operating a compressor assembly are provided. The method includes comparing a first data set and a second data set to determine a first correlation factor, comparing the first correlation factor to a first threshold that at least partially determines whether a stall precursor exists, removing mean values from the first data set and the second data set, comparing the first data set and the second data set each removed of mean values to determine a second correlation factor, and comparing the second correlation factor to the first threshold, and classifying the stall precursor as either a spike stall precursor, a modal stall precursor, or a combination stall precursor.

Abstract: A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.

Abstract: The invention relates to a lead-through arm (30) for the auxiliaries of a turbomachine, intended to be mounted in a substantially radial direction of the turbomachine. The lead-through arm (30) comprises two fairing walls (32) connected at one of the axial ends thereof by a connecting element (34) and a transverse firewall (38) connecting the two fairing walls (32), characterised in that it comprises a firebreak member (36) disposed in the radial direction, said member (36) being elastically deformable and being inserted axially, and constrained elastically, between an axial end of the firewall (38) and the connecting element (34).

Abstract: Protective coatings on an aerospace component are provided. An aerospace component includes a surface containing nickel, nickel superalloy, aluminum, chromium, iron, titanium, hafnium, alloys thereof, or any combination thereof, and a coating disposed on the surface, where the coating contains a nanolaminate film stack having two or more pairs of a first deposited layer and a second deposited layer. The first deposited layer contains chromium oxide, chromium nitride, aluminum oxide, aluminum nitride, or any combination thereof, the second deposited layer contains aluminum oxide, aluminum nitride, silicon oxide, silicon nitride, silicon carbide, yttrium oxide, yttrium nitride, yttrium silicon nitride, hafnium oxide, hafnium nitride, hafnium silicide, hafnium silicate, titanium oxide, titanium nitride, titanium silicide, titanium silicate, or any combination thereof, and the first deposited layer and the second deposited layer have different compositions from each other.

Abstract: A gooseneck hinge assembly includes a first gooseneck hinge portion having a first portion first end coupled to a first surface, a first portion second end having a first portion aperture to receive a pin, and a first gooseneck curve between the first portion first end and the first portion second end. The assembly further includes a second gooseneck hinge portion being a mirror image of the first hinge portion and having a second portion first end coupled to the first surface, a second portion second end having a second portion aperture to receive the pin, and a second gooseneck curve between the second portion first end and the second portion second end. The assembly further includes the pin coupled to a second surface and to extend through the first portion aperture and the second portion aperture to facilitate rotation of the second surface relative to the first surface.

Abstract: An airfoil profile for a second stage turbine nozzle of a gas turbine is provided. The turbine nozzle may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

Abstract: In a rotary machine and a seal member, a casing, a rotor, a stator blade, a rotor blade, and a seal device disposed between the casing and a tip portion of the rotor blade are provided, in which a blade attachment groove is provided in the inner peripheral portion of the casing, and a caulking groove is provided adjacent to the blade attachment groove, in which a base end portion of the stator blade is mounted in the blade attachment groove and a caulking member is locked to the caulking groove and a blade root portion of the stator blade, so that the stator blade is fixed to the inner peripheral portion of the casing, and in which a seal ring as a seal device is mounted in the inner peripheral portion of the casing, and the seal ring covers at least a part of the caulking groove.

Abstract: A turbine shroud segment for a gas turbine engine having an annular gas path extending about an engine axis. The engine has a turbine rotor mounted for rotation about the axis and having a plurality of blades extending into the gas path. The turbine shroud segment includes a body extending axially between a leading edge and a trailing edge and circumferentially between a first and second lateral edges. The body has a radially outer surface and a radially inner surface. The radially outer surface includes a textured surface exposed to a cooling flow. The radially inner surface defines an outer flow boundary surface of the gas path next to a tip of one of the blades. A cooling flow passageway is defined in the body and extends axially between one or more cooling inlets receiving the cooling flow from the textured surface and one or more cooling outlets.

Abstract: A temperature destratification assembly can include an outer housing. An impeller can be positioned within the outer housing between the inlet and outlet of the outer housing. The impeller can have an impeller hub and a plurality of impeller blades extending radially outward from the impeller hub. The assembly can include an impeller motor configured to rotate the impeller blades about an axis of rotation. A stator can be positioned within the outer housing between the impeller and the outlet of the outer housing. The stator can include a plurality of vanes. The stator vanes can include an upstream edge at the upstream end of the stator, a first surface extending from the upstream edge to the downstream edge of the vane, and a second surface opposite the first surface and extending from the upstream edge to the downstream edge of vane. A plurality of the vanes can have a downstream edge at the outlet of the outer housing.

Abstract: An abradable coating includes a matrix and particles that are dispersed in the matrix, the particles being made of a material switching into a fluid phase under the effect of the increase in temperature upon contact between a tip of a blading and the abradable coating.