Abstract: An adjustable stator blade position maintaining structure for an aero-engine compressor, which keeps an adjustable stator blade at a preset position when a compressor works. The adjustable stator blade position maintaining structure includes a positioning section, a limiting section and a force transmission section The positioning section is mounted in a mounting hole in a casing; the limiting section is cone-shaped and thus fits into a conical hole in the top of a journal of the adjustable stator blade; and the force transmission section is connected between the positioning section and the limiting section so as to transmit a load from the limiting section to the positioning section.

Abstract: A turbine rotor includes a disc with cavities, a plurality of blades, each with a root received in one of the cavities, and an axial retention system including a first series and a second series of strips circumferentially distributed around an axis of the rotor, the first and the second series being axially superimposed and arranged such that at least two strips circumferentially adjacent to the first series are axially superimposed on a strip of the second series and each strip of the first and second series is arranged opposite a cavity of the disc so as to axially block the root of a blade.

Abstract: A blade fastening assembly and a gas turbine including the same are proposed. The blade fastening assembly includes a fastening key having a threaded hole, a rotor disk including a disk slot into which a root member is inserted, the rotor disk having a first groove with a shape corresponding to a portion of the fastening key, a first portion of a second groove adjacent to the first groove, and a pin groove connected with the first groove, a platform having a second portion of the second groove formed in communication with the first portion of the second groove and the first groove and forming a shape corresponding to a remaining portion of the fastening key in a state of being inserted into the disk slot, and a fastening pin inserted into the threaded hole and the pin groove.

Abstract: A proactive method and related wind turbine system are provided for reducing vibrations in the rotor blades when the rotor hub is locked against rotation. The method includes determining an initial blade orientation to wind direction and wind parameters for wind impacting the rotor blades. Based on the wind parameters and blade orientation, an angle of attack is determined for the rotor blades that will at least reduce vibrations expected to be induced in the blades from the current wind conditions. With a controller, the rotor blades are pitched to achieve the angle of attack using a pitch control system. The angle of attack is determined and the rotor blades are pitched from the initial blade orientation to the new angle of attack prior to vibrations being induced in the rotor blades.

Abstract: A combination structure of a fan guard and static blades is disclosed. The fan guard includes an annular plate, multiple radial ribs, and multiple circumferential ribs. The annular plate is fixed on a motor base. The radial ribs arranged around the annular plate extend radially. The circumferential ribs are arranged concentrically and spacedly and connected with radial ribs in series. Each of the static blades includes a blade body, an inner and an outer coupling plate. The inner coupling plate and the outer coupling plate are arranged on two ends of the blade body respectively. The blade body is fixed on one side of the fan guard through the inner coupling plate being combined with one end of the radial rib and through the outer coupling plate being combined with another end of the radial rib to make the static blades be combined on the fan guard.

Abstract: A propulsor fan and drive system having reduced noise emission is disclosed. The propulsor fan includes a blade fan having a plurality of blades. The blade fan is tensioned at the tips of the plurality of blades. By tensioning the tips of the blades, an angle of the blades is maintained during operation of the propulsor fan thereby reducing noise that may result from changes in the angle of the blades.

Abstract: A low pressure compressor section of a gas turbine engine includes low pressure compressor stages spaced apart along an axis of rotation of the low pressure compressor section. The low pressure compressor section includes at least one of a fluid conduit extending between an air inlet of the gas turbine engine and the low pressure compression stages. The fluid conduit having at least one flow diverter displaceable between a first position and a second position to modulate air through the low pressure compressor stages. And/or a compressor stage disabler is engageable with at least one of the low pressure compressor stages and configured to reduce a rotation thereof.

Abstract: A centrifugal blower includes a box, a filter, an impeller, a scroll casing, a bell mouth, a partition wall, and a separation tube. The scroll casing defines an air passage gradually increasing from a nose portion in a circumferential direction. The partition wall divides the air passage into an upper passage and a lower passage. The separation tube includes an air introducing plate to partially cover the impeller and defining an air inlet portion and a tubular portion that extends from the air inlet portion through the impeller. On a virtual plane parallel to a rotational axis of the impeller, an outer edge of the air introducing plate extends and a passage between the filter and the upper passage is divided by the separation tube into a first passage cross-section closer to the nose portion and a second passage cross-section that is smaller than the first passage cross-section.

Abstract: An energy conversion system for converting wind energy into electrical energy includes at least one rotor having a substantially horizontal rotational axis and a plurality of rotor blades extending radially with respect to the rotational axis; a rotor mantle which fully surrounds the rotor; a plurality of wind funnels, including a first wind funnel arranged upstream of the rotor mantle and tapering towards the rotor mantle, and a second wind funnel arranged downstream of the rotor mantle and widening in a direction leading away from the rotor mantle; and a fixed frame which supports the rotor mantle and/or the plurality of wind funnels, wherein at least one adjustment device is provided, which is arranged and configured to orient the energy conversion system in a position corresponding to a prevailing wind direction.

Abstract: An improved efficiency propeller for aircraft includes a blade structure mounted onto a propeller hub, a servo unit, and a cantilevered base. A distinctive feature of the disclosure is that the blade structure includes a main mast, which is mounted onto a propeller hub and forms the spine of the leading edge of the blade structure, and at least one secondary mast aligned with the main mast, and turning spacers with struts are mounted onto the main mast, and the struts are covered by lateral pieces of a skin module, and the overlapping and flexible lateral pieces of the skin module form a skin.

Abstract: A method for operating a wind farm having a first wind power installation and a second wind power installation, to an associated wind power installation and to an associated wind farm. The second wind power installation is located in the wake of the first wind power installation in at least one wake wind direction. A tip-speed coefficient is determined from the ratio of a second tip-speed ratio of the second wind power installation and a first tip-speed ratio of the first wind power installation and a pitch-angle coefficient is determined from the ratio of a second pitch angle of the second wind power installation and a first pitch angle of the first wind power installation.

Abstract: A control system for an engine operatively coupled with a propeller and methods for controlling an engine operatively coupled with a propeller are provided. In one example aspect, the control system includes a controller and an electric propeller governor. The electric propeller governor includes a motor operatively coupled with a flyweight governor spring. The motor is communicatively coupled with the controller. The controller is operable to receive data indicative of the speed of the propeller, determine if the measured speed exceeds a propeller speed threshold, and if the threshold is exceeded, the controller is configured to change a propeller speed set point. Particularly, the controller can cause the motor to change the preload on the flyweight governor spring, which in turn causes adjustment of the propeller speed set point. In this way, propeller speed overshoot is prevented during fast acceleration of the engine.

Abstract: A rotor blade control system includes a main control valve having an inlet for receiving liquid and an outlet for issuing liquid to a rotor pitch change actuator. The main control valve is configured to control flow of liquid from the inlet to the outlet to modify pitch angle of rotor blades. A feathering system has a first conduit in fluid communication with the outlet of the main control valve, a second conduit in fluid communication with the rotor pitch change actuator, and a drain conduit in fluid communication with a liquid return system. The feathering system has a normal operation mode for supplying liquid from the main control valve to the rotor pitch change actuator, and a feathering mode for allowing drainage from the rotor pitch change actuator to the drain conduit across a range of flow rates.

Abstract: A method of designing a modified aerofoil shape, the method comprising the steps of: determining a plurality of resonant frequencies of a baseline aerofoil shape; determining that one of the resonant frequencies falls within a predetermined range of frequencies; providing a plurality of aerofoil sections defining the baseline aerofoil shape; and defining a modified aerofoil shape by displacing at least one of the plurality of aerofoil sections relative to its baseline position in the baseline aerofoil shape until one of the plurality of resonant frequencies previously falling within the range of frequencies is shifted outside the range of frequencies.

Abstract: Provided is a rotor blade configured to be implanted in a disc of a rotating body, the rotor blade including a blade root, wherein in a cross-sectional shape of the blade root, the blade root includes at least one stage of protruding parts protruding toward opposite sides with respect to a direction containing a circumferential component, the protruding parts being configured to lock the blade root to the disc, each of the protruding parts has a contact surface configured to come into contact with the disc and inclined so as to extend toward a center part of the blade root from radially inside to radially outside, and each of the protruding parts has a non-contact surface configured not to come into contact with the disc and inclined so as to extend toward the center part of the blade root from the radially inside to the radially outside.

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: A bracket assembly for securing a tower section to a deck includes a lower support bracket, columns, and a pair of upper upper support brackets, which all have vertical plates with circular apertures. Each circular aperture spans at least two tower flange bolt holes. Attachment yokes are inserted into the circular apertures, and each have at least two bolt apertures, which match the bolt holes size and spacing. The yokes are rotated to align the holes for insertion of bolts. Specific yokes are provided to fit various tower sizes. The brackets can be stacked, and the yoke arrangement substantially reduces bolt torque requirements.

Abstract: A blade is provided. The blade comprises a plurality of a first composite fiber plies and a plurality of a second composite fiber plies. Ends of the second fiber plies are staggered such that interlock between the first composite fiber plies and the second composite fiber plies is formed in a region where the second composite fiber plies end and meet with the first composite fiber plies. The blades are used for an engine of an aircraft.

Abstract: A turbocharger includes a housing and a rotating group supported for rotation within the housing. The rotating group includes a compressor wheel disposed within a compressor section of the turbocharger, and the rotating group includes a turbine wheel disposed within a turbine section of the turbocharger. The turbine wheel includes a bleed pressure surface. The turbocharger further includes a bleed passage that extends at least partly through the housing to fluidly connect the compressor section to the turbine section. The bleed passage is configured to direct a bleed flow of fluid from the compressor section to the bleed pressure surface to supply a thrust counterbalance load to the bleed pressure surface.

Abstract: An aeroderivative gas turbine provided with a casing, a compressor including a rotor mounted on a generator shaft supported for rotation in the casing, a high pressure turbine arranged in the casing and with a rotor mounted on the generator shaft for co-rotation with the compressor rotor, a combustor, a power turbine arranged in the casing and including a rotor mounted on a turbine shaft to drive a load, wherein a thermal insulation coating is present to reduce heat dispersion through the casing.