Abstract: A modular fan array includes a fan assembly having a fan wheel, a fan motor, and a mounting bracket. The fan wheel has a diameter. The assembly includes a frame having at least a pair of vertical members having a spacing therebetween. The spacing is greater than the fan wheel diameter. The mounting bracket includes a motor mount portion and a pair of rearwardly and outwardly extending legs. The motor mount portion includes an opening in which the motor is mounted. The rearwardly and outwardly extending legs each have a first angled section angled relative to the motor mount portion and second frame mount portion. The frame mount portions extend outwardly from the angled portions and parallel to the motor mount portion. The frame mount portions are removably secured to the frame.

Abstract: An aircraft engine having a turbine assembly including a bearing housing having a central axis, a first-stage vane ring and a second-stage vane ring. The first-stage vane ring is positioned in concentric relation with the bearing housing via a first circumferential array of lugs and slots between the bearing housing and the first-stage vane ring. The second-stage vane ring is positioned in concentric relation to the first-stage vane ring via a second circumferential array of lugs and slots between the first-stage vane ring and the second-stage vane ring.

Abstract: A bucket of a Pelton turbine with an outlet edge curved at least in segments. To achieve a particularly high efficiency the outlet edge forms a rear hump in a side view, wherein a center of curvature of the hump is positioned below the outlet edge in the side view and a peak of the hump is located closer to the cup base than to the bucket face.

Abstract: A noise elimination and vibration damping device for an air compressor and an air compressor are provided. An air compressor vent is provided with an inner sleeve therein, a fixed end of the inner sleeve is connected to an inner wall surface of the air compressor vent, a suspended end of the inner sleeve is in a suspended state. A groove is defined on the air compressor vent. A space between the groove and the inner sleeve defines a noise elimination chamber, the noise elimination chamber is provided with multiple noise elimination regions arranged at intervals, and each of the multiple noise elimination regions is filled with magnetic fluid. A first-stage noise elimination structure is disposed on the inner sleeve. The suspended end can generate radial oscillation to drive the magnetic fluid to generate tangential oscillation, thereby attenuating an acoustic energy of a sound entering the noise elimination chamber.

Abstract: A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.

Abstract: A radial expander having a rotor mounted in a housing and comprising multiple blades. The blades together with a radially inner hub contour of a rotor hub and a radially outer housing contour define flow channels for the process gas, which process gas to be expanded enters in a radial direction and from which expanded process gas exits in the axial direction. The radially inner hub contour of the rotor includes a curvature change at least in some circumferential positions seen in the meridional section such that adjacent to a flow leading side of the rotor, the radially inner hub contour, seen in the meridional section, is curved radially to the outside and adjacent to a flow trailing side of the rotor, the radially inner hub contour, seen in the meridional section, is curved radially to the inside.

Abstract: A gas turbine engine includes a propulsor, a geared architecture including a gearbox, a gas generator section including a compressor section having a first rotor rotationally mounted to a first spool. A front center body assembly defines a portion of a core flow path that is forward of the first rotor relative to an engine longitudinal axis. A front wall is mounted to the front center body assembly, which supports an output shaft of the gearbox that drives the propulsor. A bearing package is mounted to the front center body assembly to rotationally support the first spool. The bearing package is removable from the first spool without disassembly of the first rotor. The bearing package supports the first spool during at least one of a first period prior to installation of the geared architecture into the engine and a second period after removal of the geared architecture from the engine.

Abstract: A method of starting a submersible pump used for transferring liquefied gas. The method includes starting a submersible pump (1A) disposed in a suction container (2A) of a pump apparatus (100A) to deliver liquefied gas to a suction container (2B) of a pump apparatus (100B) through a flow-path switching device (5A) in the suction container (2A), passing the liquefied gas through a flow-path switching device (5B) in the suction container (2B) while the liquefied gas bypasses a submersible pump (1B) disposed in the suction container (2B), and then starting the submersible pump (1B).

Abstract: An offshore wind power plant designed to reduce a fatigue load of a wind turbine includes an offshore structure, a plurality of wind turbines which is installed above the offshore structure to be spaced apart from each other with a predetermined distance and is supplied with a power through wind to produce electrical energy; and a turbine controller which controls at least one of a pitch movement and a yaw movement for the plurality of wind turbines.

Abstract: The turbine nozzle includes a body having first and second sides defining a thickness between the first and second sides. Nozzle holes are formed through the thickness between the first and second sides. Each nozzle hole has an inlet on the first side of the body to receive fluid and an outlet on the second side of the body to direct the fluid to a turbine rotor. The nozzle holes are arranged in a plurality of circular patterns on the first side about a central axis. An inlet area of each nozzle hole is larger than an outlet area. Inlet areas of the nozzle holes arranged in the same circular pattern are the same, but inlet areas of the nozzle holes arranged in a circular pattern having a larger radius are larger than inlet areas of the nozzle holes arranged in a circular pattern having a smaller radius.

Abstract: An impeller (20, 120) for a ducted fan arrangement (10, 110), the impeller (20, 120) including a hub (24, 124) and a plurality of blades (26, 126) extending radially from the hub (24, 124), each of the plurality of blades (26, 126) including a root (28, 128) proximate the hub (24, 124) and a tip (30, 130). A camber of each of the plurality of blades (26, 126) is arranged to flatten or reduce between the root (28, 128) and the tip (30, 130). A fan arrangement (10, 110) including such an impeller (20, 120) is also disclosed.

Abstract: A cooling circuit of an airfoil for a gas turbine engine includes a serpentine channel having a plurality of fluidly connected radially extending flow passages and a tip flag channel disposed adjacent to the serpentine channel. The tip flag channel includes a first tip flag passage extending radially and a second tip flag passage extending axially from a terminal end of the first tip flag passage, the second tip flag passage disposed radially outward of the serpentine channel. The second tip flag passage is in direct fluid communication with each of the first tip flag passage and a final passage of the serpentine channel.

Abstract: A fan includes a main body of the fan and a bracket assembly. The main body is connected to the bracket assembly. The main body includes a blower part for blowing air, a rotating bracket and a main unit. The rotating bracket is arranged between the blower part and the main unit and is configured to connect the blower part and the main unit. The main unit is configured to control air blowing of the blower part. The bracket assembly includes at least one bendable and shapeable supporting leg configured to fix the fan to an external object. A rotating bracket is rotatably connected to both the blower part and the main unit, enabling vertical and horizontal rotation of the blower part. This configuration achieves multi-angle adjustment of the blower part, simplifies user control over airflow direction, and thereby significantly improves user experience.

Abstract: Disclosed is a dual-duct air pump, including a pump casing, a centrifugal fan, and a diaphragm pump. A first air opening and a second air opening that are interconnected, and an independent air opening are disposed on the pump casing, the first air opening is used for communication with the outside world, and the second air opening and the independent air opening are used for communication with independent inflation cavities of an inflatable product; and the centrifugal fan is arranged inside the pump casing, and an air inlet end of the centrifugal fan is communicated with the first air opening. Using the centrifugal fan and the diaphragm pump inside a same fan, the two independent inflation cavities may be inflated based on different pressure requirements.

Abstract: A return channel for a centrifugal turbo machine. The return channel includes a plurality of return channel vanes, arranged around a return channel axis. Each return channel vane includes: a leading edge at a first distance from the return channel axis, a trailing edge at a second distance from the return channel axis, the second distance being smaller than the first distance. A respective flow passage is defined between each pair of adjacently arranged return channel vanes. The return channel vanes are arranged with a non-constant pitch around the return channel axis.

Abstract: A blade for a turbine rotor wheel of an aircraft turbomachine, successively comprising a blade root, a stilt, a platform, as well as a vane, the blade root being intended to be housed in a blade housing groove provided on a peripheral portion of a turbine disc, the housing groove being defined between two directly consecutive disc teeth. According to the invention, on each of the two sides thereof, in the circumferential direction of the blade, the stilt is provided with a protrusion for radially retaining the blade, each protrusion comprising a stop surface which is radially inwardly directed and intended to cooperate with a radially outer surface of a disc tooth.

Abstract: A gas generator turbine blade for a gas turbine engine includes a platform and an airfoil. The airfoil extends in a spanwise direction from the platform to a tip. The airfoil has an external airfoil surface formed in conformance with multiple cross-section airfoil profiles described by a set of Cartesian coordinates.

Abstract: A turbomachinery engine can include a fan assembly with a plurality of variable pitch fan blades. The fan blades are configured such that they define a first VPF parameter and a second VPF parameter. The first VPF parameter is within a range of 0.10 to 0.40 and is defined as the hub-to-tip radius ratio divided by the fan pressure ratio. The second VPF parameter is within a range of 1-30 lbf/in2 and is defined as the bearing spanwise force divided by the fan area. In certain examples, the turbomachinery engine further includes a pitch change mechanism, a vane assembly, a core engine, and a gearbox.

Abstract: An open rotor gas turbine engine includes a gearbox and a fan blade system coupled to the gearbox. The fan blade system includes a hub and a plurality of fan blades affixed to the hub. At least one of the fan blades includes a blade body and a break line formed within the blade body at a location that divides the blade body into sections having parametrically defined masses. The break line has less rigidity than surrounding portions of the blade body that surround the break line. The blade body of at least one fan blade is configured to break into the sections when subjected to an excessive stress.

Abstract: An attachment assembly for a ceramic matrix composite (CMC) vane includes an inner diameter ring having a strut recess and a first flange on a downstream side configured for engaging an inner platform of the CMC vane, an outer diameter ring having a support structure disposed to form a gap relative to a portion of an outer platform of the CMC vane during a non-operating engine condition, and a strut cantilevered from an inner side of the outer diameter ring and disposed to pass through a hollow portion within an airfoil of the CMC vane to engage the strut recess in the inner diameter ring to support the inner diameter ring and the CMC vane. The inner and outer diameter rings and the strut may be metallic and carry the loads rather than the CMC carrying the loads.