Abstract: In one exemplary embodiment of the present disclosure an airfoil is provided. The airfoil defines a spanwise direction, a root end, and a tip end. The airfoil includes: a body defining a pressure side and a suction side and extending along the spanwise direction between the root end and the tip end, the body formed of a composite material; and a spar enclosed in the body of the airfoil extending along the spanwise direction, the spar comprising a plurality of spar segments arranged in an overlapping configuration along the spanwise direction.

Abstract: The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.

Abstract: Acoustic structures for a gas turbine engine are disclosed. In various embodiments, the acoustic structures comprise a panel in the form of a cellular structure having a plurality of cells; and a housing configured to house the cellular structure, the housing including a first rail configured for attachment to a static structure within the gas turbine engine and a second rail configured for attachment to the static structure. In various embodiments, the acoustic structures comprise a liner in the form of a non-segmented or two-piece structure configured to extend about the inner barrel of a nacelle structure. The disclosed panels and liners are configured to maximize the operational area of the acoustic structures by eliminating obstructions from adjacent flow paths.

Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).

Abstract: Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.

Abstract: A centrifugal compressor includes: a housing including an intake flow path; a compressor impeller disposed in the intake flow path; an accommodation chamber formed upstream of the compressor impeller in the housing; a movable member disposed in the accommodation chamber and configured to be movable between a retracted position where the movable member is retracted from the intake flow path and a protruding position where the movable member protrudes from the accommodation chamber into the intake flow path, the protruding position being located closer to the intake flow path with respect to the retracted position, and a contacting portion and a non-contacting portion provided on an accommodation chamber opposing surface of the accommodation chamber, the accommodation chamber opposing surface being positioned upstream of the movable member, the contacting portion being contactable with the movable member, the non-contacting portion being non-contactable with the movable member.

Abstract: A fan assembly includes a fan duct, an inlet fan, an outlet guide vane assembly, and a control system. The inlet fan includes fan blades adapted to rotate about a central axis to force fan exit air toward an aft end of the fan duct. The outlet guide vane assembly is located in the fan duct downstream of the inlet fan and is configured to adjust a direction of the fan exit air. The outlet guide vane assembly includes a plurality of guide vanes that extend radially relative to the central axis and are configured to rotate to a first vane-pitch angle. The control system is configured to rotate the guide vanes redirect the fan exit air, vary a pressure downstream of the fan inlet, minimize intake flow distortion experienced by the inlet fan, reduce inlet fan vibratory response and/or improve fan operability margins.

Abstract: A control method for a centrifugal compressor and an air conditioning system. The control method for the centrifugal compressor includes: S100, when an inlet opening of the centrifugal compressor is below a first preset value, shutting down a drive motor of the centrifugal compressor; or S200, when the inlet opening of the centrifugal compressor is not below the first preset value, performing the following operations in a preset order: decreasing the inlet opening of the centrifugal compressor, and increasing a rotate speed of the centrifugal compressor.

Abstract: An assembly for a gas turbine engine according to an aspect of the present disclosure includes a metallic damper including a first contact surface and a gas turbine engine component. The gas turbine engine component includes a main body extending in a first direction between a gaspath surface and a second contact surface. The first and second contact surfaces oppose each other along an interface extending in a second direction. The first and second contact surfaces are dimensioned to contact each other along the interface in a hot assembly state. The main body is established by a composite including fibers in a matrix material. At least some of the fibers are arranged to establish a plurality of cooling passages aligned with the interface relative to the second direction. A method of damping for a gas turbine engine is also disclosed.

Abstract: A bearing assembly installed within a turbocharger housing between a turbine wheel and a compressor impeller mounted for rotation together on a turbocharger shaft may include a journal bearing disposed on a corresponding portion of the turbocharger shaft, a thrust bearing having a thrust bearing surface, and a bearing carrier. The bearing carrier may include a carrier body, a carrier body bore extending axially through the carrier body and receiving the journal bearing therein, and a thrust bearing seat on the exterior of the carrier body facing the turbine wheel. The thrust bearing seat may have a complimentary shape to the thrust bearing surface of the thrust bearing, the thrust bearing disposed between the carrier body and the turbine wheel and engaging the thrust bearing seat. The bearing assembly may further include an anti-thrust bearing surface facing the compressor impeller, and an anti-thrust bearing mounted to the anti-thrust bearing surface.

Abstract: Provided is a seal arranged about a tower aperture of a wind turbine nacelle, which seal includes an annular channel shaped to contain a liquid, and an annular lip extending downwards into the annular channel, which annular channel and annular lip are mounted at opposite sides of a gap between the nacelle and a wind turbine tower; and further including a volume of liquid in the annular channel, which liquid volume is sufficient to immerse the annular lip about its lower circumference to prevent a passage of air between nacelle interior and nacelle exterior. A seal maintenance arrangement including such a seal and a device for replenishing the liquid in the annular channel is also provided.

Abstract: A heat shield assembly adapted for use with gas turbine engines, airframes, and aircraft includes a carrier and a heat-shield tile. The carrier is adapted to couple to the gas turbine engine, airframe, or aircraft. The heat-shield tile includes material different than the carrier and is arranged to cover the carrier to protect the carrier from high-temperature gases surrounding the heat shield assembly.

Abstract: A centrifugal compressor includes a rotary shaft having a plurality of impellers and a casing having an intermediate discharge port. The casing has a plurality of diaphragms, an external casing, a return flow path that guides a flow direction of a working fluid to an inner side in a radial direction, and an intermediate scroll that guides part of the working fluid discharged from the impeller in an intermediate stage to the intermediate discharge port. The intermediate scroll has a scroll flow path formed on a second side in the axial direction with respect to the return flow path, and an introduction portion connecting the return flow path and the scroll flow path, and an outer flow path forming surface of the scroll flow path is formed by a casing inner peripheral surface facing an inner side of the external casing in the radial direction.

Abstract: A method of adjusting at least one rotor blade of a wind turbine which includes the steps of receiving a command for adjustment of the rotor blade at an adjustment speed, ascertaining a current moment of inertia of the rotor blade and acceleration of the rotor blade until reaching the adjustment speed, wherein the acceleration until reaching the adjustment speed is limited in dependence on the ascertained moment of inertia. A system and a wind turbine.

Abstract: A heating, ventilation, air conditioning, and refrigeration (HVACR) system includes a compressor with a gas bearing supplied with compressed gas and a controller. The controller is configured to determine an inlet pressure and outlet pressure of the gas bearing, determine a maximum speed limit based on the inlet pressure and the outlet pressure, and prevent the compressor from operating at a speed that is greater than the maximum speed limit. A method of controlling a compressor includes calculating a maximum speed limit based on an inlet pressure and an outlet pressure of the gas bearing. The method also includes in response to determining that a speed setting is greater than the maximum speed limit, adjusting operation of the compressor such that a speed of the compressor is at or below the maximum speed limit.

Abstract: A ceramic matrix composite blade includes a central core surrounded by an outer profile, the central core comprising layers of unidirectional layup having two dimension and three dimension fiber weaves; the outer profile comprises a biased weave layup that radiates toward a leading edge and a trailing edge of the blade; wherein the biased weave layup includes fibers that extend proximate an attachment region of the blade radially and axially along an airfoil portion of the blade toward the leading edge and trailing edge.

Abstract: Provided is a vacuum pump regarding which compression can be improved at low costs. Included is a plurality of Siegbahn exhaust mechanisms in which a helical groove is provided to a stator disc. The Siegbahn exhaust mechanisms are provided on both faces of an upstream side and a downstream side of the stator disc. An end portion of the helical groove provided on the upstream side and a start portion of the helical groove provided on the downstream side are situated at least partially overlapping in a circumferential direction. A width of a channel of a switchback portion of the upstream side and the downstream side is equivalent or less than a depth of a channel of the Siegbahn exhaust mechanisms.

Abstract: A turbine engine includes a compressor section, a combustion section, and a turbine section. Fuel combusted in the combustion section drive stages of airfoils in the turbine section to drive the compressor section. The airfoils can include a geometry near or at the trailing edge with a linear portion provided between the pressure side and a first curved portion, to reduce shock generated in the wake of the airfoils.

Abstract: A device for self-balancing a rotating part, such as a propeller, along a given axis is disclosed. The propeller 102 coupled to, a drive shaft with freedom for linear movement along longitudinal axis L-L; at least one pair of levers 614/616, comprising a first lever 614-1/616-1 and a second lever 614-2/616-2, that are pivotally mounted on mounting plate 606 at two diametrically opposite points 618; and at least one pair of weights 622 fixed at external ends of the levers 614/616. inner ends of levers 614/616 are operatively coupled to the propeller 102 such that when propeller 102 undergoes a linear movement in any direction along the longitudinal, axis L-L due to unbalance, inner ends of levers are, moved to cause the weights 622 to move to provide a balancing force to neutralize the unbalance in the propeller. An embodiment with only one pair of levers is also disclosed.

Abstract: A gas turbine is provided, the gas turbine engine including a turbomachine having an inlet splitter defining in part an inlet to a working gas flowpath and a fan duct splitter defining in part an inlet to a fan duct flowpath. The gas turbine engine also includes a primary fan driven by the turbomachine defining a primary fan tip radius R1, a primary fan hub radius R2, and a primary fan specific thrust rating TP; and a secondary fan downstream of the primary fan and driven by the turbomachine, the secondary fan defining a secondary fan tip radius R3, a secondary fan hub radius R4, and a secondary fan specific thrust rating TS; wherein the gas turbine engine defines an Effective Bypass Area, and wherein a ratio of R1 to R3 equals R 1 R 3 = ( E ? F ? P ) ? ( 1 - RqR Sec . - Fan 2 ) ( 1 - RqR Prim . - Fan 2 ) ? ( T P T S ) ? ( E ? B ? A ) .