Abstract: A gas turbine engine including a compressor has a first compressor section and a second compressor section, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. The turbine includes a first turbine section and a second turbine section. A first shaft connects the first compressor section and the first turbine section. A second shaft connects the second compressor section and the second turbine section. A fan is connected to the first shaft via a geared architecture. The first shaft includes at least one magnetic section. An electromagnet is disposed radially outward of the first shaft at an axial location of the at least one magnetic section, relative to an axis defined by the gas turbine engine.

Abstract: A rotating component includes an airfoil section with a free end, the airfoil section being formed of a composite core with a metallic skin and an abrasive coating applied to the free end.

Abstract: A fan blade structure of a convection fan includes a fan blade body. The fan blade body includes a central disk secured to the rotating shaft of the motor and multiple blades evenly distributed in a circumferential direction of the central disk. The fan blade body further includes an outer edge frame, the outer edge frame is connected to an outmost side of each of the blades in a radial direction of the central disk. The outer edge frame is connected to an outmost side of the blade in the radial direction of the central disk through the outer edge frame, which makes all the outmost sides of all the blades secured to the outer edge frame, thus the stability of the blade is strengthened, blade deformation in harsh environments is avoided, thereby the balance performance of the fan blade is improved, and the vibration or noise is reduced.

Abstract: A stationary blade includes a main unit having a hollow blade structure formed from a metal plate by plastic forming. The stationary blade includes a blade tail section. In a blade tail upper portion, the metal plate has a concave-shaped recess and a rib formed on an inner surface side thereof and the metal plate further has slits formed by slitting on a blade pressure side thereof, so that droplets affixed on a blade surface can be guided into an inside of the hollow blade when the blade tail section is joined to the hollow blade main unit. The recess in the metal plate is covered so as to be lidded by a suction-side protrusion of a suction-side metal plate from a blade suction side to thereby form a hollow blade tail section. The metal plates are welded together to the main unit.

Abstract: A turbocharger, with a turbine for expanding a first medium that includes a turbine rotor and a turbine housing, a compressor for compressing a second medium that includes a compressor rotor coupled to the turbine rotor via a shaft and a compressor housing, a bearing housing in which the shaft is mounted, a bearing housing cap delimiting the bearing housing facing the turbine, and a turbine cover delimiting the turbine on a side facing the bearing housing and has a section projecting into a recess of the bearing housing cap. On a section of the bearing housing cap delimiting the recess of the bearing housing cap on the outside, which on the outside follows the section of the turbine cover projecting into the recess of the bearing housing cap, an oil trapping lip is formed on a side of the bearing housing cap facing the turbine rotor.

Abstract: The invention relates to a side-channel machine having a housing, located in the housing a side-channel for guiding a gas, and at least one gas inlet opening which is formed in the housing and is fluidically connected to the side-channel. Furthermore, the side-channel machine has at least one gas inlet pipe which connects to the at least one gas inlet opening. The side-channel machine further comprises at least one gas outlet opening and at least one gas outlet pipe which connects to the at least one gas outlet opening. Furthermore, the side-channel machine has an impeller that can be made to rotate in the housing, with impeller blades, which bound impeller cells arranged in the side-channel, for delivering the gas in the impeller cells from the at least one gas inlet opening to the at least one gas outlet opening. The side-channel machine further has at least one interrupter arranged between the at least one gas inlet opening and the at least one gas outlet opening.

Abstract: A field of turbomachine rotor blades, and in particular a turbomachine rotor blade including a blade root and a blade tip spaced apart by a blade height, together with at least one intermediate segment presenting a negative tangential slope, and a distal segment situated between the intermediate segment and the blade tip and presenting a positive tangential slope, wherein the distal segment extends over at most 30% of said blade height.

Abstract: Airfoils for gas turbine engines are provided. The airfoils include an airfoil body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction, a first shielding sidewall cavity located adjacent one of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, a second shielding sidewall cavity located adjacent the other of the pressure and suction sides proximate the root of the airfoil body and extending radially toward the tip, and a shielded sidewall cavity located between the first shielding sidewall cavity and the second shielding sidewall cavity, wherein the shielded sidewall cavity is not adjacent either of the pressure or suction sides proximate the root and transitions to be proximate at least one of the pressure and suction sides proximate the tip.

Abstract: A fan module includes a housing, a bearing, a rotating shaft, and a fan wheel. The housing includes a bottom covering plate, a top covering plate, and a side wall connected between the bottom covering plate and the top covering plate and surrounding to form a housing space. The bearing is disposed on the bottom covering plate and includes a supporting pillar. The supporting pillar extends from the bottom covering plate toward the top covering plate. The rotating shaft has a first through hole therein. The rotating shaft is rotatably sleeved onto the supporting pillar by the first through hole. The fan wheel is connected to an outer edge of the rotating shaft.

Abstract: A ceramic matrix composite (CMC) component including a subcomponent, such as a band flowpath, a load bearing wall and a wall support, each comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The CMC component further including at least one mechanical joint joining the subcomponent, the load bearing wall and the wall support to form the CMC component. The reinforcing fibers of the load bearing wall are oriented substantially normal to the reinforcing fibers of the subcomponent and the wall support. Methods are also provided for joining the subcomponent, the load bearing wall and the wall support to form a mechanical joint.

Abstract: A rotor device of a turbomachine, having a disc wheel and a plurality of rotor blades that are arranged circumferentially inside recesses of the disc wheel and that are fixed at the disc wheel in the axial direction by means of a securing appliance. At least one flow channel that extends at least substantially in the axial direction is assigned to each recess. The securing appliance has a plurality of recesses, wherein a number and arrangement of the recesses is chosen such that the entire cross-sectional surface of the securing appliance passable by the flow, which is defined as the sum of an overlap of the recesses with at least one flow channel as viewed in the axial direction, is substantially independent of a circumferential position of the securing appliance relative to the disc wheel.

Abstract: A gas turbine guide vane segment has a first guide vane part with an aerofoil and a first platform section and a second guide vane part with a second platform section. The first guide vane part and the second guide vane part are separately manufactured parts joined together such that the second platform section defines a leading edge of the gas turbine guide vane segment and such that the first platform section and the second platform section form an aligned common platform surface of the gas turbine guide vane segment. The first platform section includes slots in the first platform section for guiding cooling fluid along a surface of the first platform section for film cooling of the surface, the slots being provided at an upstream bend of the first platform section and the slots are provided on a side of the first platform section facing the working fluid.

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil body having an internal passage for conveying a fluid flow, the internal passage including first and second passage sections coupled at a turn section. A baffle includes an elongated body arranged in the second passage section to define a pair of cooling flow paths respectively established along a pair of opposed walls of the elongated body such that the pair of cooling flow paths extend from the turn section along a common length of the second passage section, and a first wedge region extending from the elongated body into the first passage section such that the fluid flow is directed through the turn section between the first passage section and the pair of cooling flow paths.

Abstract: A vane (18) has an airfoil section (19) that extends in a radial direction and an outer shroud (20) that is disposed on the radially outward side of the airfoil section (19), and is supported inside a casing by means of a vane support member (24). The outer shroud (20) has a shroud body (31), radial protrusions (36, 37), and a hook section (32) including the radial protrusions (36, 37) and engaging parts (39, 40). A recessed part (50), which is recessed in an axial direction or in the radial direction, is provided in at least a part of the circumference of the hook section (32). The engaging part (39) has a sealing surface that continues along the entire circumference thereof, the sealing surface coming into contact with the vane support member (24) in the radial direction.

Abstract: An airfoil for a gas turbine engine comprises at least three successive sections defined between a root and a tip. A first decrease of maximum thickness-to-chord ratios defined by a difference between a maximum thickness-to-chord ratio at the root and a maximum thickness-to-chord ratio at a first spanwise position, a second decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the first spanwise position and a maximum thickness-to-chord ratio at a second spanwise position, a third decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the second spanwise position and a maximum thickness-to-chord ratio at the tip, the second decrease being greater than the corresponding first and third decreases.

Abstract: A fan is configured to generate an air flow by rotating together with a rotation shaft. The fan includes multiple blades arranged radially about a central axis of the rotation shaft and a boss portion that connects the blades to the rotation shaft. The boss portion has an end face portion located on one end side of the rotation shaft. The end face portion has an annular region concentric with the central axis of the rotation shaft. One part of the annular region in a circumferential direction has an optical refractive index different from an optical refractive index of another part of the annular region in the circumferential direction.

Abstract: A blade includes a blade body having a surface and a hole extending through the surface of the blade body. The hole defines a hole axis and a plane perpendicular to the hole axis. The hole has an elongated hole perimeter within the plane. The hole perimeter includes a plurality of non-linear perimeter sections to minimize stress concentration around the elongated hole perimeter while maximizing the usable opening area. A rotor system includes a rotor hub and a blade as recited above. The blade extends radially outward from the rotor hub. The blade defines a root end proximate to the rotor hub, a tip end opposite the root end.

Abstract: An apparatus is provided for modifying the geometry of at least one part of a turbine, which can include a shell assembly that includes an outer shell that is shaped to modify the shape of a pre-existing element of a turbine. The outer shell of the shell assembly can be composed of a fiber-reinforced polymeric material and can at least partially define an inner cavity. The outer shell can be bonded to a structure to modify the geometrical shape of that structure. Thereafter, a polymer casting can be injected into the inner cavity via at least one injection port attached to the shell assembly. In some embodiments, one or more stiffeners and/or a core can be positioned within the inner cavity to help improve the bonding of the polymer casting to the shell and/or improve a structural property of the apparatus.

Abstract: A conformal heat shield for a gas turbine engine may comprise a first section including a first arcuate segment and a second arcuate segment circumferentially adjacent to the first arcuate segment. The first arcuate segment and the second arcuate segment may each comprise a distal metal layer including a plurality of loops extending radially outward from the distal metal layer. A proximal metal layer may be located radially inward of the distal metal layer. An insulating material may be located between the distal metal layer and the proximal metal layer. A first strap may be located through the loops.

Abstract: The present invention relates to a centrifugal fan comprising a fan housing with a radial outlet opening arranged in a radial peripheral wall thereof, a rotor arranged rotatably in the fan housing and provided close to an axial rotation axis thereof with a rotor inflow opening, wherein the fan housing is provided close to the rotation axis of the rotor with an axial inlet opening, and a tube part which extends in the fan housing from the radial outlet opening arranged in the radial peripheral wall and inward along the radial peripheral wall. The invention further relates to a heating device comprising a burner with a fuel mixture infeed opening, a centrifugal fan according to the invention, and wherein a fluid connection is provided between the fuel mixture infeed opening of the burner and the outlet opening of the centrifugal fan.