Abstract: A method for calibrating a position sensor of a variable vane assembly for a gas turbine engine includes positioning an actuator member in at least one predetermined position, determining a first measured position of the actuator member in the at least one predetermined position with a first channel of a position sensor, determining a second measured position of the actuator member in the at least one predetermined position with a second channel of a position sensor, determining a measured position difference between the first measured position and the second measured position, and calibrating the second channel of the position sensor by adjusting the second measured position by the measured position difference to determine a second calibrated position.

Abstract: The present invention provides a turbine sub-runner that is positioned to be within the vortex zone of a turbine main runner. The sub-runner includes at least two sub-runner blades, configured to monitor the relative flow of the vortex created by the main runner. A sub-runner hub will be positioned downstream of the main runner blades. A sub-runner shaft, having a threaded section, will also be a part of the sub-runner, and will be connected to the sub-runner hub housing adjustable sub-runner blades and the mechanism enabling to regulate angular position of sub-runner blades. A main runner blades control mechanism will be connected to the sub-runner shaft via threaded interface, and is capable of transferring the rotational energy of the sub-runner into angular movement of the main runner blades.

Abstract: Embodiments of systems and methods permit use of variable diffuser vanes in multi-stage compressor devices. These embodiments deploy a flow sensor to identify the direction of flow for a working fluid that transits the stages of the compressor device. In one embodiment, the flow sensor generates a signal, which a controller processes to align a variable diffuser vane with the direction of flow of the working fluid. This configuration pre-empts the operational difficulties of previous designs by providing independent control over the diffuser vanes in the individual stages of the multi-stage compressor device.

Abstract: Embodiments of a system and method can modify the position of diffuser vanes to improve performance of a compressor device, e.g., a centrifugal compressor. These embodiments form a feedback loop to manage the position of the diffuser vanes relative to one or more operating parameters on the compressor device. In one embodiment, the system and method measure input power with the diffuser vanes at a first position and a second position. Changes in the input power will identify other positions for the diffuser vanes that optimize performance of the compressor device, e.g., to reduce power consumption and to achieve and maintain peak compressor efficiency within the entire operating envelope of the compressor device.

Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.

Abstract: A system for monitoring a turbomachine is provided. The system includes a turbomachine component having a variable geometry, a first sensor disposed to sense a condition of the turbomachine component, a second sensor disposed to sense an operational condition of the turbomachine, the operational condition being associated with an operation of the turbomachine component and a controller operably coupled to the first and second sensors, the controller being configured to execute a turbomachine process in accordance with a result of sensing by the second sensor with respect to the operational condition regardless of whether the first sensor detects the condition.

Abstract: A method for the variation of at least one blade row of a fluid-flow machine, in which, in dependence of the actual operating point, in addition to an aerodynamic speed, at least one further quantity pertinent to the position of the operating point in the family of characteristics of the fluid-flow machine is employed for control.

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for controlling turbine guide vane positions. According to an example embodiment of the invention, a method is provided for controlling at least one turbine guide vane. The method includes receiving a reference signal associated with the at least one turbine guide vane, measuring an actuator position and an angular position associated with the at least one turbine guide vane, generating a deadband signal based at least in part on the angular position, and manipulating the at least one turbine guide vane based at least in part on the deadband signal and the reference signal.

Abstract: A turbomachine having variable-angle diffuser vanes operates by regulating the angle of the diffuser vanes on the basis of the sensors disposed on the pump body or pipes of a surge detection device. The onset of surge can be forecast by measuring the fluctuations in the operating parameter(s) over a measuring interval of time computed on the basis of the operating characteristics of the impeller of the turbomachine. The onset of surge is prevented by adjusting the angle of the diffuser vanes in accordance with the sampling duration for parameter fluctuations over the measuring interval of time, and by adjusting the diffuser vanes to maintain the operating parameter fluctuations of the fluid machinery below a threshold value of the turbomachine derived from the design flow rate of the turbomachine. Application of the surge detection device in combination with fluid flow guide vanes and blades of the turbomachine enables full utilization of the potential capability of the turbomachine.

Abstract: A compressor has inlet guide vanes, rotor blades and stator blades. To prevent rotating stall, baffle vanes 5 capable of having their angles varied are installed upstream of the inlet guide vanes, actuators to vary the angles of baffle vanes are coupled to the baffle vanes, sensors installed upstream of the baffle vanes detect a rotating stall condition inside the flow passage of the compressor, and a control unit is responsive to signals from the sensors to output control signals to the actuators to vary the angles of the baffle vanes so as to prevent the rotating stall condition. Instead of the baffle vanes, fluid jets may be provided upstream of the inlet guide vanes for the same purposes.

Abstract: According to the invention there now is provided a method of producing a sintered titanium based carbonitride alloy with 325 weight-% binder phase with extremely good properties at extremely fine machining with high cutting speeds and low feeds. The method relates to the use of a raw material comprising a complex cubic carbonitride containing the main part of the metals from groups IV and V of the periodic system and carbon and nitrogen to be found in the finished alloy whereby said alloy has the composition0.87.ltoreq.X.sub.IV .ltoreq.0.990.66.ltoreq.X.sub.C .ltoreq.0.76where X.sub.IV is the molar ratio of the group IV elements of the alloy and X.sub.C is the molar ratio of carbon.