Abstract: A method for managing communications involving a lockstep processing comprising at least a first processor and a second processor can include receiving, at a data synchronizer, a first signal from a first device. The method can also include receiving, at the data synchronizer, a second signal from a second device. In addition, the method can include determining, by the data synchronizer, whether the first signal is equal to the second signal. When the first signal is equal to the second signal, the method can include transmitting, by the data synchronizer, the first signal to the first processor and the second signal to the second processor. Specifically, in example embodiments, transmitting the first signal to the first processor can occur synchronously with transmitting the second signal to the second processor.

Abstract: A power system (150) operable to implement a power balancing control scheme is provided. In one aspect, a power system (150) includes multiple independent power supplies (182A, 182B) with independent batteries (172A, 172B) feeding onto a common power bus (180). The power supplies (182A, 182B) regulate the voltage on the common power bus (180) at the same time. The power balancing control scheme, when implemented, causes the load on the common power bus (180) to be shared among the individual power supplies (182A, 182B) with a specified load distribution. The specified load distribution can be set or determined to balance the State of Charge (SoC) of the batteries (172A, 172B) over time whilst taking into account the constraints or limits of the elements (172A, 172B, 182A, 182B) of the power system (150).

Abstract: A tube spacing and fastening system for a gas turbine engine includes a plurality of tubular structures, a wear sleeve, a spacer element, and a fastening element. The plurality of tubular structures provides a fluid flow to a component of the gas turbine engine. The wear sleeve is located around each of the plurality of tubular structures. The spacer element receives the plurality of tubular structures. The fastening element extends around the wear sleeves and is configured to secure the plurality of tubular structures to the spacer element. An interference between the fastening element and wear sleeves is configured to allow the fastening element to slide with respect to the wear sleeves and to provide a damping effect under gas turbine engine vibrations and operating conditions. A method of damping vibrations in the plurality of tubular structures includes allowing the fastening element to slide with respect to the wear sleeve.

Abstract: A hollow plank of a combustor liner defining a combustion chamber including an inner wall having a plurality of inner openings and one or more inner holes, an outer wall having one or more outer openings and a plurality of outer holes, a plurality of lateral walls coupled to the inner wall and the outer wall to define a cavity, and a partition wall connected to the plurality of lateral walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The one or more outer openings communicate with the first sub-cavity and communicate through a plurality of tubes with the second sub-cavity. The plurality of inner openings communicate with the second sub-cavity and communicate with the first sub-cavity through one or more bypass tubes. The first sub-cavity or the second sub-cavity, or both, are frequency tuned to reduce combustion dynamic frequencies.

Abstract: A method for controlling a power system having at least one inverter-based resource connected to an electrical grid includes monitoring, via at least one controller of the at least one inverter-based resource, one or more command signals issued by a system-level controller. The method also includes determining, via the at least one controller of the at least one inverter-based resource, whether the one or more command signals issued by the system-level controller includes oscillatory behavior characteristic of an instability. In response to determining that the one or more command signals issued by the system-level controller includes oscillatory behavior characteristic of the instability, the method includes reducing one or more gains of a volt-var regulator of the system-level controller to reduce the instability.

Abstract: Combustion turbine control systems are configured to operate combustion turbine systems in partial or no load while meeting emission targets. The combustion turbine system includes a combustion turbine, an electrical generator, a combustion turbine controller, a catalyst assembly, and/or other relevant equipment. Based on given operating constraints, such as load conditions and emission regulations, the combustion turbine controller may execute corresponding actions to control certain gas concentrations and/or gas mass flows in the exhaust gases in compliance with emission regulations. The corresponding actions may include, but are not limited to: controlling fuel and/or diluent injection(s) to combustor(s) to control combustion (e.g.

Abstract: A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.

Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly including a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure such that the rotor is disposed radially inward of the stator. The rotor exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.

Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine.

Abstract: A dispatch advisor to assist in selecting operating conditions of a power plant that maximizes operational revenue is described. The dispatch advisor obtains a base load map for operating the power plant to meet base load power demands. The base load map includes a primary base load operating space for attaining target plant power output and efficiency, and an expanded base load portion for attaining higher plant power output and less than optimal efficiency. Both the primary base load operating space and the expanded base load portion associate power output and efficiency values of the power plant that result from a subset of operational parameter values for operating the power plant during base load. The dispatch advisor can transform the flexible base load map into one or more visualizations describing the revenue possibilities associated with operating the power plant based on operating values and attained power output and efficiency.

Abstract: A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.

Abstract: A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. Further, the rotary machine includes a seal assembly at the rotor-stator interface. The seal assembly includes at least one seal and a groove formed into the rotor at the rotor-stator interface. In addition, the seal assembly includes a removable insert positioned within the groove of the seal assembly and defining at least a portion of the rotor face. As such, during operation of the rotary machine, if the rotor and the stator make undesirable contact at the rotor-stator interface, the removable insert becomes damaged to prevent damage from occurring to the rotor and the stator.

Abstract: A control system for active stability management of a compressor element of a turbine engine is provided. In one example aspect, the control system includes one or more computing devices configured to receive data indicative of an operating characteristic associated with the compressor element. For instance, the data can be received from a high frequency sensor operable to sense pressure at the compressor element. The computing devices are also configured to determine, by a machine-learned model, a stall margin remaining of the compressor element based at least in part on the received data. The machine-learned model is trained to recognize certain characteristics of the received data and associate the characteristics with a stall margin remaining of the compressor element. The computing devices are also configured to cause adjustment of one or more engine systems based at least in part on the determined stall margin remaining.

Abstract: A rotating field machine (200) including a stator (140) and a rotor (150) are provided. In particular, a dual-winding rotating field machine (200) in which the stator (140) includes two separate windings can be provided. In one example implementation, the stator (140) can include an excitation winding (220) configured to control an excitation current and a power winding (230) configured to control power flow to an electrical system. The dual-winding rotating field machine (200) can further include a starting mode and a generating mode. During the starting mode, both the excitation winding (220) and the power winding (230) can be coupled to one or more switching power converters (170). During the generating mode, the power winding (230) can be coupled to a variable frequency bus and the power converter (170) can be used to manage excitation power only.

Abstract: A bearing support assembly to support one or more bearings on a shaft. The bearing support assembly includes a bearing support frame configured to be coupled to a static frame, a plurality of ribs connected to the bearing support frame, and a bearing support connected to the plurality of ribs and configured to support a bearing of the one or more bearings. The bearing support assembly has a non-axisymmetric stiffness around a circumference of the bearing support assembly.

Abstract: A system and method are provided for damping power system oscillations in a power system network having one or more local inverter-based generators within a plant, the plant connected to a grid at a point of intersection (POI). The system and method include a plant-level controller or local controller that receives one or more grid signals having a characteristic indicative of a power system oscillation. The plant-level controller or local controller generates an auxiliary signal from the grid signals that is used by the local controller of the inverter-based generators. At the local controller, the auxiliary signal is used to modulate reactive power output from the inverter-based generator to change a voltage at the POI, the voltage change damping the power system oscillations.

Abstract: Methods and apparatus for computer-aided prostate condition diagnosis are disclosed. An example computer-aided prostate condition diagnosis apparatus includes memory to store instructions and a processor. The example processor can detect a lesion from an image of a prostate gland and generate a mapping of the lesion from the image to a sector map, the generating the mapping of the lesion comprising identifying a depth region of the lesion, wherein the depth region indicates a location of the lesion along a depth axis. The processor can also provide the sector map comprising a representation of the lesion within the prostate gland mapped from the image to the sector map.

Abstract: Methods and systems for generating a recovery scheduling solution in response to a scheduling disruption are disclosed.

Abstract: A wireless power transmitting and charging system is disclosed. A method for operating a power transmitter of the wireless power transmitting and charging system comprises the steps of: maintaining a ping value table where ping signal conditions are mapped according to the height of a power receiver; recognizing the power receiver by varying a ping signal according to the ping signal conditions recorded in the ping value table; and controlling a charging mode according to a message received from the power receiver.

Abstract: A turbomachine equipped with an embedded electric machine having a segmented and movable stator is provided. In one aspect, a turbomachine defines a radial direction and includes a rotating component, actuators, and an electric machine. The electric machine includes a rotor assembly rotatable with and operatively coupled with the rotating component. The electric machine also includes a stator assembly having a stator split into stator segments. Each one of the stator segments is movable by one of the actuators between a first position and a second position along the radial direction, the stator segments each being closer to the rotor assembly along the radial direction when in the first position than when in the second position.

Abstract: Methods and systems are provided for automatically characterizing lesions in ultrasound images. In one example, a method includes automatically determining an A/B ratio of a region of interest (ROI) via an A/B ratio model that is trained to output the A/B ratio using a B-mode image of the ROI and an elastography image of the ROI as inputs, and displaying the A/B ratio on a display device.

Abstract: A heat exchanger is provided that can include furcating unit cells coupled with each other. Each of the unit cells can be elongated along an axis and include a sidewall that defines annular ring openings on opposite ends of the unit cell along the axis. The sidewall also can define undulating annular rings between the annular ring openings and axially separated from each other along the axis. The sidewall can further define angled openings into the unit cell both above and below each of the undulating annular rings. At least a first opening of the annular ring openings and the angled openings can be configured to be an inlet to receive a first fluid into the unit cell and at least a second opening of the annular ring openings and the angled openings configured to be an outlet through which the first fluid exits the unit cell.

Abstract: A system includes a gas turbine having a turbine stage disposed in a combustion gas path, wherein the turbine stage includes turbine vanes disposed upstream from turbine blades. The system includes an isothermal expansion system coupled to the turbine stage. The isothermal expansion system includes multi-fluid injectors configured to vary axial positions of combustion within a turbine stage expansion of the turbine stage to reduce temperature variations over the turbine stage expansion, wherein at least one of the multi-fluid injectors is coupled to each of the turbine vanes. Each of the multi-fluid injectors includes a fuel port configured to inject a fuel, an oxidant port configured to inject an oxidant, and a barrier fluid port configured to inject a barrier fluid between the fuel and the oxidant, wherein the barrier fluid is configured to delay mixing between the fuel and the oxidant.

Abstract: Various methods and systems are provided for identifying connected regions in ultrasound images. An exemplary method includes acquiring ultrasound video data of an anatomical region while a force is being applied to induce movement within the anatomical region, the ultrasound video data including a plurality of ultrasound images. The method includes identifying two or more connected regions in one of the plurality of ultrasound images, generating a modified ultrasound image by graphically distinguishing the first connected region from the second connected region, and causing a display device to display the modified image.

Abstract: A pump system for pressurizing a fluid within a closed loop thermal transport bus is disclosed herein. The example of the pump system disclosed herein includes an electric motor including a rotor shaft and a stator, wherein the rotor shaft is to generate a first torque; a pump including an impeller coupled to an impeller shaft, wherein the impeller is to increase a kinetic energy of the fluid; a driver wheel attached to the rotor shaft, wherein the driver wheel is radially connected to a follower wheel; and a co-axial magnetic coupling to connect at least one of the follower wheel to the impeller shaft or the driver wheel to the rotor shaft, wherein the co-axial magnetic coupling includes an outer hub, an inner hub, and a barrier can, the barrier can to hermetically seal a portion of the pump system from the fluid.

Abstract: Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.

Abstract: There is provided a current control circuit (20) for connection between a first electrical network (42) and a converter, the current control circuit (20) comprising: first and second input terminals (24,26) for connection to the first electrical network (42); first and second output terminals (28,30) for respective connection to converter terminals (46,48) of the converter; first and second switching limbs, the first switching limb interconnecting the first input and output terminals (24,28), the second switching limb interconnecting the second input and output terminals (26,30), each switching limb including a respective switching element (32,34,36,38); a director limb (76) extending between the first and second output terminals (28,30), the director limb (76) including at least one current director element (84) and at least one first resistive element (86), the director limb (76) including an intermediate terminal (82); a second resistive element (88), a first end of the second resistive element (88) ope

Abstract: An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

Abstract: A vehicle repair control system includes a sensor generating data signals relating to a vehicle, a communication system, and one or more processors that determine a repair to be performed on the vehicle based on the sensor data signals received over the communication system. The processors examine historic repair data indicative of outlays for previous repairs of other vehicles, and examine the historic repair data to determine fluctuations in the outlays for the previous repairs to determine a projected outlay for the repair to be performed on the vehicle based on the fluctuations. The processors determine a quantity-based reduction in the projected outlay based on a number of repairs performed at a repair facility and communicate a control signal to the repair facility to autonomously direct the repair to be performed on the vehicle responsive to determining the quantity-based reduction to change a state of the vehicle.

Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.

Abstract: An apparatus to refuel a vessel with cryo-compressed hydrogen is disclosed herein. The apparatus includes a refueler controller configured to defuel the vessel prior to a refuel process based on a pressure of the vessel; fill a mixing tank with at least the cryo-compressed hydrogen based on the pressure of the vessel and a pressure of the mixing tank, wherein the mixing tank is connected upstream of the vessel and is structured to include the cryo-compressed hydrogen; initiate the refuel process of the vessel; adjust a temperature of the mixing tank in response to a temperature of the vessel not satisfying a target temperature of the vessel during the refuel process, wherein the temperature of the mixing tank is to be adjusted based on an increase or a decrease of flow of supercritical hydrogen; and end the refuel process in response to the pressure of the vessel satisfying a target pressure of the vessel.

Abstract: The subject matter of the present disclosure generally relates to techniques for following a treatment protocol having one or more treatment parameters to cause a targeted physiological outcome at a distal site, assessing an expression level of a gene in a region of interest after completing the treatment protocol, and modifying the one or more treatment parameters based on the expression level of the gene. The treatment protocol may include one or more ultrasound energy treatments to the region of interest.

Abstract: A power system and method for powering an imaging system. The power system and method include a power distribution unit (PDU) coupled to an imaging system gantry. An input of the PDU is electrically coupled to an alternating current (AC) power source from a utility power supply. An output of the PDU is electrically coupled to the imaging system gantry. The power system and method further include an energy storage system providing peak power to an X-ray generator of the imaging system during X-ray generation.

Abstract: A system and method for inspecting fan blade clearances in a fan stator module are presented. The method includes rotating a fan rotor assembly that includes an attached bracket situated between adjacent fan blades connected to the fan rotor assembly. The bracket includes a laser module and an inclinometer configured to measure a circumferential position of the laser module. The method further includes projecting a laser beam from the laser module to the fan case to determine a distance measurement between the laser module and the fan case at multiple circumferential points around the fan case. The distance measurement and circumferential position data is processed by a computing device to determine a clearance distance between a fan blade and the fan case.

Abstract: A turbine nozzle assembly includes at least one airfoil and an outer endwall coupled to a radial outer end of the at least one airfoil. A mounting rail is coupled to the outer endwall and extends at least partially radially outward from the outer endwall and at least partially circumferentially along the outer endwall. A stress relief structure is defined in the mounting rail. The stress relief structure includes an end opening defined in a radial outer surface of the mounting rail, a slot defined through the rail thickness of the mounting rail and coupled to the end opening, and an oblong opening defined through the rail thickness of the mounting rail and coupled to a radial inner end of the slot. The oblong opening is arranged asymmetrically in a circumferential direction relative to the slot to relieve stress where prevalent in the mounting rail.

Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.

Abstract: The conductor bar for a squirrel-cage rotor comprises at least one end which is partially slit such that a section of the end forms two symmetrical branches relative to the slit. The centre of gravity of each branch is arranged such that the branches flare towards the outside of the bar under the effect of centrifugal force when the rotor is rotated.

Abstract: A component includes a magnetic core having a body formed of a first material, defining a first opening and a second opening thereon. A duct formed of a second material extends at least partially through the body between the first opening and the second opening. The first opening and the second opening are in fluid communication by way of the duct.

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: Various methods and systems are provided for ultrasound imaging. In one embodiment, a method comprises acquiring, via an ultrasound probe, Doppler measurements over a plurality of cardiac cycles, evaluating a flow profile comprising the Doppler measurements to detect an abnormality in the flow profile, and displaying, via a display device, the flow profile with a reference flow profile overlaid thereon. In this way, the attention of a physician evaluating results from an ultrasound imaging examination may be directed to abnormal flow that is potentially indicative of pathologies, thereby enabling earlier and more accurate diagnosis of pathologies.

Abstract: The present disclosure pertains to electric machines such as electric propulsion systems for aircraft that integrated cooling systems, and methods of cooling such an electric machine. Exemplary electric machines include an electric motor that has a stator, a rotor, and a drive shaft operably coupled to the rotor. Exemplary electric machines further include a motor cooling conduit that defines a pathway for conveying a cooling fluid through or around at least a portion of the electric motor, a casing assembly that circumferentially surrounds at least a portion of the electric motor, a casing assembly conduit integrally formed within at least a portion of the casing assembly which defines a pathway for conveying the cooling fluid through the at least a portion of the casing assembly, and a pump or compressor operably coupled to the drive shaft and configured to circulate the cooling fluid through the motor cooling conduit and the casing assembly conduit.

Abstract: An apparatus comprises a power electronic energy conversion system comprising a first energy storage device configured to store DC energy and a first voltage converter configured to convert a second voltage from a remote power supply into a first charging voltage configured to charge the first energy storage device. The apparatus also includes a first controller configured to control the first voltage converter to convert the second voltage into the first charging voltage and to provide the first charging voltage to the first energy storage device during a charging mode of operation and communicate with a second controller located remotely from the power electronic energy conversion system to cause a second charging voltage to be provided to the first energy storage device during the charging mode of operation to rapidly charge the first energy storage device.

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 method for making ultrasound transducers and ultrasound probes includes providing a piezoelectric layer having a first surface and a second surface, where the second surface is on an opposite side of the piezoelectric layer from the first surface. The method includes fabricating a plurality of conductive through vias extending from the first surface to the second surface of the piezoelectric layer, where fabricating the plurality of conductive through vias comprises cutting a plurality of trenches through the piezoelectric layer and filling each of the plurality of trenches with a conductive material. The method includes cutting the piezoelectric layer into a plurality of transducer units after fabricating the plurality of conductive through vias and cutting each of the transducer units into a plurality of transducer elements.

Abstract: An airfoil for a turbine engine includes an outer wall bounding an interior and defining a pressure side and a suction side, the outer wall extending axially between a leading edge and a trailing edge to define a chord-wise direction, and also extending radially between a root and a tip to define a span-wise direction. At least one cooling conduit can be formed in the interior of the airfoil, and a tip rail can project from the tip in the span-wise direction.

Abstract: Methods for forming a unitary ceramic component are provided. The method may include: positioning a braze reactant layer in a contact area between a first densified ceramic component and a second densified ceramic component; positioning a pack material around at least a portion of the first densified ceramic component or the second densified ceramic component; positioning at least one infiltrate source in fluid communication with the braze reactant layer; and thereafter, heating the at least one infiltrate source, the pack material, the first densified ceramic component, and the second densified ceramic component to a braze temperature that is at or above a melting point of at least one phase of the infiltrate composition such that at least one phase of infiltrate composition melts and flows into the braze reactant layer and reacts with a ceramic precursor compound therein to form a ceramic material.

Abstract: A gas turbine engine includes a fan assembly having a plurality of fan blades; and a turbomachine. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbomachine further including a first input power source; a second input power source configured to counter-rotate relative to the first input power source; a power output component operably connected to the fan assembly; and a gear assembly located forward of the combustion section of the turbomachine, the gear assembly configured to receive power from the first input power source and the second input power source and provide power to the power output component, the gear assembly comprising a helical gear.

Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.

Abstract: A method of imaging a turbine engine component with a first surface and a second surface that is spaced from the first surface. The turbine engine component includes a plurality of holes with inlets formed in the second surface or interior that are fluidly coupled to outlets formed in the first surface or exterior. The method includes determining at least one fluid frequency, determining at least one sampling frequency, and pulsing fluid through at least a portion of the interior of turbine engine component while imaging the turbine engine component.

Abstract: The invention provides compounds suitable for use as contrast agents in magnetic resonance imaging (MRI). The compounds of the present invention are manganese (II) complexes having advantageous properties as compared with similar known compounds.