Abstract: The present invention relates to a turbomachine assembly, comprising: a casing (10), a first rotor (12) which is movable in rotation with respect to the casing (10) about a longitudinal axis (X-X), and comprising: *a disk (120), and *a plurality of blades (122) capable of flapping with respect to the disk (120) during a rotation of the first rotor (12) with respect to the casing (10), a second rotor (140) which is movable in rotation with respect to the casing (10) about the longitudinal axis (X-X), and a damper (2) which is configured to damp a displacement of the first rotor (12) with respect to the second rotor (140) in a plane orthogonal to the longitudinal axis (X-X), the displacement being caused by a flapping of at least one blade (122) among the plurality of blades (122), the damper (2) comprising: o a first bearing part (21): *bearing against the first rotor (12), and *being configured to apply a first centrifugal force (C1) to the first rotor (12), o a second bearing part (22): *bearing against the

Abstract: Integrally geared centrifugal compressor systems are described that include eccentric cartridges that house bearings and seals to maintain rotor concentricity for a variety of pinons integrated in a fixed gearbox design to provide multiple impeller speeds with a single gearbox design. In an aspect, a system includes, but is not limited to, a pinion configured to be rotated by a bull gear about a rotational axis; a rotor coupled to the pinion; and an eccentric cartridge configured to house a bearing assembly through which the rotor extends to support rotation of the rotor, the eccentric cartridge having an outer surface and an inner surface, wherein the inner surface is eccentric relative to the outer surface to align the rotational axis with a center axis of the bearing assembly.

Abstract: A centrifugal blood pump includes a housing having a pumping chamber, an inlet having an inlet axis, and an outlet having an outlet axis. The inlet and the outlet are in fluid communication with the pumping chamber. The pump further includes an impeller rotatably disposed within the pumping chamber, and a strut connected to the housing at the inlet. The strut is connected to the housing at a circumferential position about the inlet axis such that a major axis of the strut and the outlet axis define a predetermined angle in a cross-sectional plane perpendicular to the inlet axis. The circumferential position of the strut relative the outlet axis reduces or eliminates damage to blood flowing around the strut.

Abstract: A centrifugal-to-axial mixed flow blower includes a blower enclosure defining a blower chamber and a centrifugal impeller supported on an impeller seat to suspend in the blower chamber. The centrifugal impeller includes a plurality of blades and a radially outward declined flow passage defined between any two adjacent blades and communicable with the blower chamber. The blower chamber is communicable with a rectangular air outlet of a heat dissipation system via a frame passage of a flow guide frame connected to below the blower enclosure. Air stream centrifugally drawn in by the centrifugal impeller passes through the declined flow passages to radially outward and downward flow into the blower chamber and then passes through the frame passage to flow axially through the rectangular air outlet into the heat dissipation system, so as to realize the effects of reduced noise, changing centrifugal vortical flow into axial flow, and decreased flow loss.

Abstract: A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.

Abstract: Provided is a method of manufacturing a wind turbine rotor blade, which method includes the steps of preparing a mold by forming a partial negative leading-edge profile in a first mold half, which partial negative leading-edge profile includes a plurality of first indentations along a leading edge region of the first mold half; forming a partial negative leading-edge profile in a second mold half, which partial negative leading-edge profile includes a complementary plurality of second indentations along a leading edge region of the second mold half; and wherein the combined shape of a first indentation and a complementary second indentation corresponds to the negative shape of a leading-edge fin that will extend radially outward from the body of the rotor.

Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.

Abstract: A cooling fan includes a fan frame and an impeller. The fan frame includes a substrate, a sidewall connected to the substrate, and a lid connected to the sidewall and opposite to the substrate. An air inlet is formed in the lid. The substrate, the sidewall, and the lid together define at least one air outlet. The impeller is rotatably mounted in the fan frame. A plurality of bulges protrudes from an inner face of the sidewall and/or an inner face of the lid.

Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 1.01-1.15 inch (25.7-29.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.54-0.66 inch (13.6-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2033 ± 15% Hz, a second mode with a frequency of 7023 ± 15% Hz, a third mode with a frequency of 12082 ± 15% Hz and a fourth mode with a frequency of 19769 ± 15% Hz.

Abstract: A bracket for mounting a first component to a second component, the bracket comprising at least one mounting boss defining a through-hole having an opening axis in axial direction for receiving a fixing used to attach the bracket to one of the first and second components; wherein the mounting boss comprises a fixing support face around the through-hole on a surface of the bracket, the fixing support face configured to bear a head of the fixing; the mounting boss is configured to resist compressive forces exerted on the bracket by the head of the fixing; and the mounting boss comprises a cavity in a space projected from the fixing support face in the axial direction of the through-hole.

Abstract: Provided is a composite material for a wind turbine blade, the composite material including a plurality of rigid elements and plurality of flexible elements, wherein each flexible element is arranged between two rigid elements and is connected thereto such that the rigid elements are flexibly connected to each other by the flexible elements. The flexibility of the composite material can be achieved by using the interspaces between the rigid elements. Therefore, when the composite material is placed on a curved surface, hollow spaces between the rigid elements may be reduced or avoided.

Abstract: Systems and methods for building predictive and prescriptive analytics of wind turbines generate a historical operational dataset by loading historical operational SCADA data of one or more wind turbines. Each sensor measurement is associated with an engineering tag and at least one component of a wind turbine. The system creates one or more performance indicators corresponding to one or more sensor measurements, and applies at least one data clustering algorithm onto the dataset to identify and label normal operation data clusters. The system builds a normal operation model using normal operational data clusters with Efficiency of Wind-To-Power (EWTP) and defines a statistical confidence range around the normal operation model as criterion for monitoring wind turbine performance. As real-time SCADA data is received by the system, the system can detect an anomalous event, and issue an alert notification and prescriptive early-action recommendations to a user, such as a turbine operator, technician or manager.

Abstract: A pump impeller, which can be part of a pump, has an impeller surface and blades being arranged on the impeller surface, wherein at least one of the blades is a blade of the first type which has a blade edge which is inclined toward the front in the rotational direction. The pump impeller can also have blades of a first type and of a second type, the blade geometries thereof differing from one another. A housing element for a pump or of a pump has a housing inner wall defining a flow channel for a fluid medium extending along a central axis. The cross section of the flow channel is greater in a main flow direction and the housing inner wall has a surface structure configured such that it counteracts a return flow counter to the main flow direction along the housing inner wall of the fluid medium.

Abstract: A radial turbomachine has a first housing part and a second housing part, which jointly form and delimit a flow channel. The first housing part forms a motor chamber for accommodating a drive motor, and the second housing part forms a gas inlet. Furthermore, a radial impeller is provided, which can be driven about an axis of rotation by the drive motor in order to suction a gas from outside the turbomachine through the gas inlet into the flow channel and to convey said gas out of the flow channel through a gas outlet to the outside. The first housing part or the second housing part forms the gas outlet at a radial distance from the axis of rotation and peripherally delimits the gas outlet.

Abstract: An induced draft fan includes a motor, a volute, a wind wheel, and a conversion interface. The volute includes a cavity for accommodating the wind wheel. The volute further includes a bottom surface and a side surface. The bottom surface includes an air inlet and the side surface includes an air outlet. The air inlet and the air outlet communicate with the cavity. The conversion interface includes a connection section, a transition section, and an exit section. The connection section and the exit section are disposed on two ends of the transition section, respectively. The transition section tilts upward so that the exit section and the connection section are staggered with each other. The connection section includes a rectangular hollow frame including an upper side plate, a lower side plate, a left side plate, and a right side plate.

Abstract: A composite impeller for a turbofan system is disclosed. The impeller includes a hub and a plurality of replaceable impeller blades coupled to the hub. Each replaceable impeller blade includes a root, a tip, a platform extending laterally from the root, and a shroud extending laterally from the tip to engage another tip of an adjacent impeller blade. The plurality of replaceable impeller blades and the hub define the enclosed centrifugal impeller.

Abstract: An insert for supplying a fluid within a drive shaft, the insert extending along an axis of rotation and comprising an insert wall having a rigid inner insert wall portion and an elastically deformable outer insert wall portion a reservoir defined by the insert wall for storing a fluid, a nozzle positioned at the first end of the insert wall, and wherein the elastically deformable outer insert wall portion is configured to move between an expanded state, when the fluid is supplied to the reservoir, and an unexpanded state, when rotation of the insert and supply of fluid to the reservoir are ceased, and movement of the elastically deformable outer insert wall portion to the unexpanded state forces the fluid to be discharged through the nozzle.

Abstract: The present disclosure relates to methods and systems for determining fatigue loads in a wind turbine. Such a method may comprise obtaining operational metadata representative for an operational situation, and determining whether the operational metadata corresponds to operational metadata from one of a plurality of previously defined operational situations for which fatigue loads are known, the plurality of previously defined operational situations being stored in an operational situations database. If the operational metadata representative for the operational situation substantially corresponds to operational metadata from the stored previous operational situation, then the fatigue loads for the stored previously define operational situation are summed to historically accumulated fatigue loads to determine total accumulated fatigue loads. Methods for registering an operational situation in a wind turbine are also provided.

Abstract: A diagonal fan wheel (1) has a cover disk (2) and a bottom disk (3). A plurality of three-dimensionally curved blades (S) are arranged between the cover disk (2) and bottom disk (3). The blades (S) are connected to the cover disk (2) and bottom disk (3) in a materially bonded manner.

Abstract: A valve for an air system in an aircraft engine, comprising: a housing defining a chamber having a valve axis circumscribed by a sealing surface; and a piston assembly within the chamber including: a sealing ring; and a body extending annularly about a piston axis collinear with the valve axis, having a first and a second piston surface axially spaced apart, a radially outer piston surface extending axially and located between the first and second piston surfaces, and an annular groove extending radially inwardly from the radially outer piston surface having first and second groove walls spaced apart and axially facing one another, the sealing ring within the annular groove, the body including: a first member defining the first piston surface and the first groove wall; and a second member defining the second piston surface and the second groove wall, the first member and the second member in mating engagement.