Abstract: A windmill, including a first end plate, a second end plate, and a plurality of primary blades disposed between the first end plate and the second end plate. The first end plate includes a central part provided with a base connected to a motor shaft. The second end plate includes a central part provided with an air inlet; the space between every two adjacent blades forms an air channel. The plurality of primary blades each includes an outmost end with respect to the central part of the first end plate, and the outmost end extends out of an outer edge of the second end plate. The connection line of every two adjacent outmost ends of the plurality of primary blades forms a circle, and the diameter D1 of the circle is larger than the diameter D2 of the second end plate.

Abstract: The present disclosure provides a centrifugal fan blade, an air treatment device and a fan; the centrifugal fan blade includes a hub and a plurality of fan blades; the plurality of fan blades are distributed around the periphery of the hub; each fan blade includes a first blade and a second blade; moreover, the first blade is in a backward blade form; and the second blade is in a forward blade form. The centrifugal fan blade can improve the flowing of the airflow and improve the air output efficiency.

Abstract: Provided is a compressor including: a compressor body that has a motor and compresses air; an aftercooler for cooling the compressed air supplied from the compressor body; a dryer for dehumidifying the compressed air flowing out from the aftercooler; a drain discharge valve for discharging a drain from the dryer; a first pressure sensor for measuring air pressure downstream of the aftercooler; and a control device having a rotation-speed adjusting unit that drives the motor at second acceleration smaller than first acceleration, the first acceleration being rated acceleration of the motor, when a pressure value measured by the first pressure sensor is less than a first threshold value predetermined at startup of the motor.

Abstract: In accordance with one aspect the present invention may comprise a regenerative blower comprising: a housing, a first port and second port in the housing, an airflow channel extending between the first and second ports for airflow between the ports, an impeller rotatable in an impeller channel to promote airflow in the airflow channel from the first port to the second port, a motor to drive the impeller, and an interrupter between the first and second ports to limit airflow from the second port to the first port.

Abstract: An inlet collector for a centrifugal fan and a centrifugal fan are provided. By arranging a tragus-shaped section in a guiding section, reverse flow caused by intersection of inlet leakage flow at a volute tongue side and inlet airflow is blocked by the tragus-shaped structure in movement process, and the leakage flow no longer collide with the inlet airflow. An inner curved surface of the tragus-shaped section controls backflow to change smoothly along an inner wall surface of the tragus-shaped section and re-enter a volute for circulation. A tragus profile is adopted to guide the airflow to change more smoothly in the velocity direction near the wall of the guiding section, so as to effectively reduce the impact of the inlet airflow on the guiding section. By using the inlet collector, energy loss of airflow is reduced, vortex formation is suppressed, and aerodynamic performance and fan noise are improved.

Abstract: A system and a method for inspecting components of a turbojet engine using RFID tags and an associated interrogator device. The inspection system includes at least one RFID tag associated with a component of the turbojet engine and an interrogator device arranged so as to be able to communicate with the RFID tag, the interrogator device being equipped with an RFID antenna arranged so as to be able to be inserted into a nacelle compartment of the turbojet engine through an inspection opening intended for the passage of an endoscope probe.

Abstract: A compressor for a heating, ventilating, air conditioning, and refrigeration (HVAC&R) unit includes an impeller, a shaft configured to rotate the impeller, and a fastener. The impeller includes an opening and does not include keys, splines, pins, or any combination thereof. The fastener is coupled to an end of the shaft and extends through the opening of the impeller, and the fastener is configured to stretch in an axial direction relative to the shaft via a tensioner during assembly of the compressor.

Abstract: A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and a gearbox efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include one or more compressor sections and one or more turbine sections. The gearbox includes an input and an output. The input is coupled to the one or more turbine sections of the core engine and comprises a first rotational speed, the output is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 4.1-14.0. The gearbox efficiency rating is 0.10-1.8.

Abstract: A gas turbine engine de-icing system includes a heat exchanger. A coolant loop is in fluid communication with the heat exchanger and is configured to circulate a heat transfer fluid. An engine oil loop is in fluid communication with the heat exchanger and is configured to transfer heat to the heat transfer fluid. A gas turbine engine inlet structure has at least one fan inlet guide vane. A spray bar is disposed at least partially in at least one fan inlet guide vane. The spray bar is in fluid communication with the coolant loop. The spray bar is configured to spray the heat transfer fluid onto an inner surface of the at least one fan inlet guide vane to de-ice the fan inlet guide vane.

Abstract: A gas turbine engine includes a rotor carrying a blade, a ceramic vane adjacent the blade, a seal carried on the rotor adjacent the tip of the ceramic vane, and a cooling passage circuit extending through the blade, the seal, and the ceramic vane. The cooling passage circuit is configured to provide cooling air into the blade, then from the blade into the seal, and then from the seal into the ceramic vane.

Abstract: A set of parts for a radial fan has a fan wheel (2), a main housing part (1), and a complementary housing part (3). They can be assembled to form a first housing that encloses the fan wheel (2). The housing has an inlet opening (27) and an outlet (23). At least one second complementary fan wheels (2?, 2?) (3?, 3?), the shape of which differs from the first fan wheel part (2), can be connected to the motor instead of the fan wheel (2).

Abstract: A blower for providing a supply of air at positive pressure in the range of approximately 2 cmH2O to 30 cmH2O includes a motor, at least one impeller, and a stationary component. The stationary component includes an inlet and an outlet. The motor, the impeller, the inlet and outlet are co-axial.

Abstract: A method and decoupler for disengaging an output member from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a shaft and a retention mechanism selectively coupling the output member to the shaft. In a backdrive event, the decoupler decouples the member from a drive shaft.

Abstract: A variable pitch propeller is designed to adjust the pitch of the propeller blade during flight to maximize the propeller efficiency. The propeller blade may comprise airfoil cross-sections. Each cross-section may be composed of different materials at the leading edge and trailing edge. In various embodiments, these materials are selected and oriented to achieve the necessary elastic moduli of the leading and trailing edge for the airfoil cross-section. During liftoff, the airfoil at the blade tip possesses a high blade pitch (e.g. 20 degrees), thereby increasing the generated lift on the propeller blades. During flight or hover conditions when maximal lift is no longer required, the trailing edge of the airfoil displaces upward and reduces the blade pitch to minimize the drag forces on the blade tip.

Abstract: A turbine engine of an aircraft includes: a primary air flow duct; a secondary air flow duct which is located around the primary duct, the secondary duct including a stator including a plurality of blades distributed around a main axis of the turbine engine and inter-blade platforms located between radially internal ends or between radially external ends of two adjacent blades, each platform including a wall partially delimiting the secondary duct; and a fluid circuit which includes a heat exchanger formed by at least one of the platforms. The platform includes a line that has an inlet port of the fluid and a fluid outlet port. The fluid circuit includes a distributor associated with each port of the at least one platform with the rest of the fluid circuit and of which each distributor is axially offset with respect to the platform along the main axis.

Abstract: A blade airfoil including a platform, concave pressure sidewall and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and outboard tip. The blade further includes at least one part-span shroud positioned on the airfoil defined by a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in at least one of TABLE I and TABLE II. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying values by a length of the at least one part-span shroud. X and Y values are connected by continuing arcs to define part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, profile sections at Z distances being joined with one another to form the nominal profile.

Abstract: A blower may include a motor; a centrifugal fan configured to rotate with rotation of the motor; a casing configured to guide air from a suction port to a discharge port; a trigger configured to be pressed; and a control board configured to control rotation of the motor. The control board may include a normal mode and a low speed mode. In the normal mode, the control board may be configured to adjust a rotation speed of the motor in accordance with a degree by which the trigger is pressed. In the low speed mode, the control board may be configured to adjust the rotation speed of the motor to a target rotation speed, wherein the target rotation speed is lower than a maximum rotation speed of the motor that is achieved when the degree by which the trigger is pressed is a maximum degree in the normal mode.

Abstract: A bladed rotor system includes first and second sets of blades with respective airfoils each having at least one internal cavity. The airfoils of both the first and second sets of blades have identical outer shapes defined by an outer surface of an outer wall of the respective airfoils. The airfoils of the first set of blades are distinguished from the airfoils of the second set of blades by a geometry and/or position of at the least one internal cavity, which is unique to blades of a given set. The natural frequency of a blade of the first set differs from the natural frequency of a blade of the second set by a predetermined amount. The blades of the first set and the second set are alternately arranged in a periodic fashion in said circumferential row, to provide a frequency mistuning to stabilize flutter of the blades.

Abstract: An inlet bleed heat (IBH) system for use in a turbine engine including a silencer assembly. The inlet bleed heat (IBH) system includes a feed pipe for delivering compressor discharge air. The feed pipe includes a plurality of orifices along at least a portion of a length of the feed pipe, and each orifice of the plurality of orifices extends through a wall of the feed pipe for allowing the compressor discharge air to exit the feed pipe. The system also includes a heat shielding component that extends across the feed pipe, wherein the heat shielding component is configured to reduce heat transfer between the feed pipe and the silencer assembly of the turbine engine.

Abstract: The present invention provides a centrifugal multistage compressor adapted to inhibit corrosion of an intermediate stage labyrinth. More particularly, the present invention provides a centrifugal multistage compressor adapted to inhibit carbon dioxide corrosion of the intermediate stage labyrinth.