Abstract: The present disclosure relates to a method for operating a wind turbine with the steps: detection of the values of predetermined operating parameters by means of suitable sensors, detection of at least one predetermined initial condition, comparison of the detected values to stored values of the operating parameters. The disclosure further relates to a wind turbine for implementing the method. Therefore, the object of the present disclosure is, to be able to adapt the operation of a wind turbine to changes using a method of the type named above, such that when the detected parameter values deviate from the stored parameter values, as a function of the initial condition, either the stored parameter values are adapted to the detected parameter values or the operation of the wind turbine is influenced as a function of the detected parameter values.

Abstract: A method for forming a pressure measurement hole in a component includes the step of forming a hole in a body of the component, the hole extending from a body surface of the component. An insert having a longitudinal passage is fitted into the hole such that the insert protrudes from the body surface. The protruding end of the insert is machined to define an insert surface profile matched to the body surface profile and displaced from the body surface by a distance substantially equal to a thickness of a covering layer that is to be bonded onto the body surface. A blocking pin is inserted into the insert passage. The covering layer is then bonded to the body surface in the region of the hole and insert after which the blocking pin is removed from the insert to open the pressure measurement hole.

Abstract: A turbine engine includes a target structure, for example, a rotating turbine blade. A probe is arranged near the target structure for communicating a detection frequency relative to the target structure for gathering information such as tip clearance. A housing is arranged adjacent to the target structure. In one example, the housing is a blade outer air seal. The housing includes a structural material that supports a window material. The window material is arranged between the probe and the target structure. The window material is transparent to the detection frequency permitting the detection frequency to pass through the window to the target structure for measurement of its position relative to the housing. The window material prevents probe contamination and provides a seal between the cooling path and turbine gas flow path.

Abstract: A plug assembly is disclosed herein for a borescope inspection path defined through apertures in spaced walls. The plug assembly includes a first plug operable to at least partially close a first aperture in an inner wall. The plug assembly also includes a second plug operable to at least partially close a second aperture in an outer wall. The plug assembly also includes a member extending along an axis and connecting the first and second plugs together in spaced relation to one another along the axis. The member is operable to elastically buckle.

Abstract: A impingement cooling system for heavy duty turbines that includes a manifold affixed to a casing of the heavy-duty turbine, wherein the manifold includes a plurality of impingement holes in the surface of the manifold and a blower that provides air flow across the plurality of impingement holes of the manifold to cool the casing of the heavy-duty turbine to control the clearance between a tip of a turbine blade and a shroud of the heavy-duty turbine.

Abstract: A gearbox life estimation system includes a single sensor or multiple sensors configured for obtaining field operational data related to loading of a gearbox from a single gearbox component or different gearbox components. The system further includes a processor configured for receiving signals representative of the field operational data from the sensors, for providing calculated operational load data for the gearbox components based on the field operational data, and for providing an estimate of remaining life of gearbox using the calculated operational load data.

Abstract: A system and method is provided for detecting and controlling rotating stall in the diffuser region of a compressor. A pressure transducer is placed in the gas flow path downstream of the impeller, preferably in the compressor discharge passage or the diffuser, to measure the sound or acoustic pressure phenomenon. Next, the signal from the pressure transducer is processed either using analog or digital techniques to determine the presence of rotating stall. Rotating stall is detected by comparing the detected energy amount, which detected energy amount is based on the measured acoustic pressure, with a predetermined threshold amount corresponding to the presence of rotating stall. Finally, an appropriate corrective action is taken to change the operation of the compressor in response to the detection of rotating stall.

Abstract: The invention relates to a method and a system for detecting the ingestion of an object by an aircraft turbine engine during a mission. The method includes the steps of acquiring during the mission digital images of the operating fan of the turbine engine, these images being acquired at an acquisition frequency proportional to the speed of rotation of the fan and to the number of blades of the fan (E10), identifying the different phases of the mission of the aircraft (E40), for each phase of the mission, comparing the images of the fan with at least one reference image corresponding to sound operation of the fan (E60), and, if necessary, identifying each abnormal image of the fan which differs from the corresponding reference image, the identification of an abnormal image of the fan corresponding to the crossing of an alert level for detecting the ingestion of an object by the turbine engine (E90).

Abstract: A multi sensor clearance probe with at least longitudinally and transversely spaced apart first and second sensors operable to measure first and second distances respectively between the sensors and a longitudinally spaced apart rotating rotor. The sensors being operable to measure blade tip clearances between radially outer turbine blade tips and an annular stator shroud circumscribing the blade tips. The blade tips may be squealer tips and the sensors operable to measure the distances between the sensors and tops of squealer tip walls and outwardly facing walls within cavities of the squealer tips. The probe may be operably connected to a controller for sending signals to the controller indicating the first and second distances for controlling an air valve used for active clearance control. Two or more of the probe may be used to determine rotor centerline offset.

Abstract: In certain embodiments, a system includes a physical computing device having a tangible machine-readable medium including code. The code is adapted to determine an efficiency of a section of a steam turbine based on a relationship between enthalpy difference values and leakage flow rate values between adjacent sections of the steam turbine. The relationship includes a point of equalizing an enthalpy of the leakage and an enthalpy at a destination of the leakage.

Abstract: A system and method capable of performing online corrosion monitoring of a component installed in a gas turbine. A sensing device is located so that electrodes thereof are exposed to an operating environment within the gas turbine section containing the component. The electrodes are formed of a material so that the component and electrodes similarly respond to corrosive agents within the gas turbine section. The electrodes are electrically insulated from each other and each electrode is operable as an anodic electrode or a cathodic electrode, depending on the extent of corrosion thereat, so that each electrode has an electrical potential value, voltages exist across the electrodes, electric currents flow between the electrodes, and the electrical potential/current values correspond to corrosion behaviors at the anodic electrodes.

Abstract: Apparatus and method of operating a centrifugal compressor and active control system includes a centrifugal compressor with compressor blades mounted on an impeller, an annular cavity bounded in part by a shroud adjacent to the blades, and an active control system for controlling a clearance between the shroud and the blades by controlling a cavity pressure in the cavity. An electronic controller for controlling a control pressure valve for pressurizing using a source of compressor discharge pressure air and depressurizing the cavity respectively may open and close the valves using pulse width modulation. Pressure and clearance sensors positioned for measuring the cavity pressure the blade tip clearance respectively in signal supply communication with the electronic controller may be used. The shroud may be supported by radially spaced apart annular radially outer and inner supports connected to a casing by a bolted joint bounding the cavity.

Abstract: A fluid dynamic polymer-based contact sensor measures ambient pressure based on the resistivity changes across the sensor under different ambient pressures. The pressure sensor may applied to airfoil structures such as wind turbine blades without impacting the blade structure and fluid dynamic characteristics. The sensor may also be applied to fluid measurements. The pressure measurements are used to measure blade performance with high fidelity. The pressure measurements are transmitted to processing to determine blade characteristics and environment including flow separation, stagnation point, angle of attack, lift and drag and wind speed. Further processing of the pressure distribution may identify wind shear, up-flow and yaw error.

Abstract: Systems and methods for isolating a performance anomaly within one or more line replaceable units (LRUs) on a gas turbine engine by monitoring the start up transient are presented. The system comprises a set of sensors, an anomaly detector and a fault isolation reasoner. Each sensor of the set monitors at least one operating parameter of at least one engine component. The anomaly detector is configured to detect an anomaly in a component by comparing a particular value of an operating parameter to a base line value of that parameter. The specific cause of the startup anomaly is isolated utilizing a set of component reasoners that is based on the nature of the detected anomaly. The key events during the engine startup are identified by the combination of monitoring physically relevant phases of a startup and monitoring the engine control schedule.

Abstract: A method for predicting surge in a compressor is provided, which is applicable to a cooling apparatus equipped with a centrifugal compressor. A set of highest outlet pressure values is obtained by a performance test performed on the centrifugal compressor. A coolant flow rate value and an opening percentage value of inlet guide vanes of the centrifugal compressor are measured. An outlet pressure value of the centrifugal compressor is calculated with an equation using the measured coolant flow rate value and the measured opening percentage value. The outlet pressure value is compared with one of the highest outlet pressure values corresponding to the measured opening percentage value, and if the outlet pressure value is larger than or equal to the highest corresponding outlet pressure value, it confirms imminent surge in the centrifugal compressor, so as to provide a basis of preparation for surge elimination.

Abstract: A method is provided for determining the remaining service life of a rotor of a thermally loaded turboengine. In the method, a temperature on the rotor is determined, the thermal stress on the rotor is derived from the determined temperature, and the remaining service life of the rotor is deduced from the derived thermal stress. A simple, exact and flexible determination of the remaining service life is achieved in that the temperature is measured directly at a predetermined point of the rotor, and in that the thermal stress on the rotor is derived from the measured temperature.

Abstract: A wind turbine comprising a system for monitoring at least one wind turbine component including a closed fluid circulating system with a fluid reservoir. The monitoring system comprises establishing a level value of the fluid systems reservoir, and establishing at least one environmental value of the fluid systems reservoir or the surroundings of the system. The level value and the at least one environmental value contributing to defining the fluid systems functionality, and the monitoring system further comprises establishing a monitoring value on the basis of the level value and the at least one environmental value.

Abstract: A system for detecting onset of a stall in a rotor is disclosed, the system comprising a sensor located on a static component spaced radially outwardly and apart from tips of a row of blades arranged circumferentially on the rotor wherein the sensor is capable of generating an input signal corresponding to a flow parameter at a location near the tip of a blade, a control system capable of generating a rotor speed signal, and a correlation processor capable of receiving the input signal and the rotor speed signal wherein the correlation processor generates a stability correlation signal.

Abstract: A method and control for predicting the remaining useful life of an airfoil for a gas turbine engine includes the steps of monitoring conditions of the blade such as flutter, leaning, etc. A measured amount of deflection of the airfoil is compared to tabulated data to predict an expected crack length which is likely causing the deflection, etc. Once a predicted crack length has been identified, the amount of accumulated damage to the airfoil at the crack is monitored and stored. The amount of useful life for the blade can be predicted by compiling the accumulated damage over time. The useful life remaining can be displayed such that flight plans or maintenance schedules for the aircraft can be modified as appropriate.

Abstract: There is provided an axial bearing load distribution system for a gas turbine engine of the type having a low pressure rotor supported by axial bearings. The system comprises a line having an inlet end positioned in a high-pressure compressor gas path downstream of any compressor stage provided with a variable geometry. The line is adapted to sense static pressure in the high-pressure compressor gas path. The line has an outlet end producing the static pressure. An air-tight pressure actuator is operatively connected to the outlet end and to one of the axial bearings to exert a force on the axial bearing proportionally to a pressure of the outlet end.

Abstract: A method and system for recreating a two-dimensional distribution of temperatures in an exhaust plane of a gas turbine engine. Light transmission and detection pairs may be arranged in the annulus of the exhaust of the turbine engine in such a way that the individual rays form a two-dimensional mesh of beams across a sector of the exhaust. Based on the absorption of the rays, the temperature of the sector of the exhaust thru which the ray passes may be determined. Based on these determinations, an image that corresponds to the operation of the turbine engine may be generated.

Abstract: A clearance control apparatus for controlling the clearance between a rotary assembly (17) and a casing (24) surrounding the rotary assembly (17) is disclosed. The clearance control apparatus comprises a temperature measuring device (34) to measure the temperature of a radially outer portion of the rotary assembly and a cooling arrangement (28) to cool the casing (24). A control system (36) is associated with the temperature measuring device (34) and the cooling arrangement (28) to control the extent of cooling of the casing (24). The extent of cooling is dependent upon the temperature of the aforesaid portion.

Abstract: A system for controlling the operating lines of a gas turbine engine comprising a compression system which compresses an incoming flow of a gas, a bleed system which extracts gas from a bleed location in the compression system prior to the gas entering a throttling orifice, a recirculation system which reintroduces at least a portion of the gas extracted by the bleed system into a feed location in the compression system or upstream from it, a control system which controls the recirculated gas such that the operating lines of the compression system are changed such that the stall margin of the compression system is increased.

Abstract: An instrumented component (18, 19) for use in various operating environments such as within a combustion turbine engine (10). The component (18, 19) may have a substrate, a sensor (50, 94, 134) connected with the substrate for sensing a condition of the component (18, 19) during operation of the combustion turbine (10) and a connector (52, 92, 140) attached to the substrate and in communication with the sensor (50, 94, 134) for routing a data signal from the sensor (50, 94, 134) to a termination location (53). The component (18, 19) may include a wireless telemetry device (54, 76, 96) in communication with the connector (52, 92, 140) for wirelessly transmitting the data signal. Recesses (114, 116) may be formed with a root portion (112, 132) of components (18, 19) within which wireless telemetry device (54, 76, 96) may be affixed.

Abstract: An instrumented component (18, 19) for use in various operating environments such as the hot gas path section of a combustion turbine engine (10). The component (18, 19) may have a substrate, a sensor (50, 204, 210) connected with the substrate for sensing a condition of the component (18, 19) within the casing during operation of the combustion turbine (10) and a connector (52, 202) attached to the substrate and in communication with the sensor (50, 204, 210) for routing a data signal from the sensor (50, 204, 210) to a termination location (53). The component (18, 19) may include a wireless telemetry device (54, 202) in communication with the connector (52, 202) for wirelessly transmitting the data signal outside the casing. A transceiver (56) may be located outside the casing for receiving the data signal and transmitting it to a processing module (30) for developing information with respect to a condition of the component (18, 19) or a coating (26) deposited on the component (18, 19).

Abstract: A coolable borescope boss includes cooling passages extending through the boss and oriented for spraying cooling air into a hole extending through the boss. Centerlines of the cooling passages may intersect the a hole axis of the hole. The cooling passages may be cylindrical or open slots disposed through the boss. The boss may be on an arcuate gas turbine engine shroud segment circumscribed about an axial centerline axis. The segment may be part of an annular segmented turbine shroud having cylindrical shroud first and second sections and a conical shroud midsection therebetween and the segment having cylindrical segment first and second sections and a conical segment midsection therebetween. A hole exit of the hole being flush with the conical segment midsection. A borescope plug tip having a spherical tip chamfer may be used to seal against a conical boss chamfer of the boss.

Abstract: An impeller device may include a magnetic detecting element and a magnetic body, which is paired with the magnetic detecting element, for detecting a rotational position of a rotary impeller. The rotary impeller is formed with a bottomed recessed part having an opening into which one of the magnetic detecting element or the magnetic body is inserted, and the opening of the recessed part is sealed with resin injected by insert molding so that the one of the magnetic detecting element and the magnetic body is buried in the rotary impeller. The magnetic detecting element and the magnetic body are capable of facing to each other through a bottom face of the bottomed recessed part.

Abstract: An emergency shutdown detection device for a gas turbine includes a longish, mechanically severable sensor element (5), in which at least one electric line (1 to 4) is provided, with at least one resistor (R1 to R3) being electrically connected to the electric line such that upon severance of the sensor element (5), the electrically connected resistor is electrically disconnected from the electrical line to alter a resistance value for the electrical line.

Abstract: An arrangement is provided for detecting a shaft break on a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine machine, especially an aircraft engine. A second turbine (11), especially a low pressure turbine, is positioned downstream from the first turbine. An actuating element (18) is positioned lying radially inwardly relative to a flow channel, between the rotor of the first turbine and a stator of the second turbine. A transmission element (22) is guided in the stator of the second turbine (11), in order to transmit a shaft break detected by the radially inwardly positioned actuating element (18) to a switching element (23) positioned radially outwardly relative to the flow channel on a housing (14) of the gas turbine.

Abstract: A board card having a control circuit includes a first substrate and an electrical fan. The first substrate has a heat source and the electrical fan is disposed on the first substrate. The electrical fan includes a revolving spindle, a plurality of blades and a LED module. The revolving spindle is disposed on the first substrate and rotates about an axis. The blades are joined with the revolving spindle. The LED module is electrically connected to the control circuit, wherein when the revolving spindle drives the blades rotate, the light-emitting direction of the LED module is along a radial direction of the revolving spindle.

Abstract: A processing system for clearance estimation in a rotating machine includes one or more sensors and one or more digital signal processors for calculating the estimated clearance. The processing system may include techniques for obtaining real-time clearance estimates and techniques for obtaining averaged clearance estimates. Aspects of the processing system may also include a method of switching between real-time clearance estimates and averaged clearance estimates depending on the operating conditions of the rotating machine. Other aspects of the processing system include the use of two digital signal processors: a first digital signal processor configured to receive signals from a clearance sensor and perform a first set of high speed processing tasks, and a second digital signal processor configured to receive signals from the first digital signal processor and perform a second set of lower speed processing tasks.

Abstract: A gas turbine machine includes a second turbine (11), e.g. a low pressure turbine, positioned downstream from a first turbine (10), e.g. a medium pressure turbine. An arrangement for detecting a shaft break of a rotor shaft includes an operator element (16) positioned between the rotor of the first turbine (10) and a stator of the second turbine (11) radially inwardly relative to a flow channel, and a sensor element (21) guided in the stator of the second turbine (11), to convert a shaft break, detected by the radially inwardly positioned operator element (16), into an electrical signal and to transmit this electrical signal to a switching element which is positioned radially outwardly relative to the flow channel on a housing of the gas turbine machine.

Abstract: An eddy current sensor for use as a dynamic proximity sensor, particularly for monitoring of blade tip timing and clearance in turbomachinery, has a common coil for use in both generating a magnetic field in a proximate region and detecting the effect of eddy currents generated by said field in electrically conductive objects passing through that region. The coil is wound on a rectangular or other elongate former so that the coil is itself elongate in section. This can improve the resolution of the device when used for sensing the passage of objects of elongate section (such as a turbine blade tip when the sensor coil is oriented with its shorter cross-sectional dimension aligned with the shorter cross-sectional dimension of the respective object. Also described is a method of processing a signal wave form from such devices to derive ‘trigger’ points for blade tip timing.

Abstract: Apparatus comprising a signal tube extending from an engine component on a hot side of a firewall in a gas turbine engine to an engine control mechanism disposed on a cool side of the firewall. The apparatus includes a fuse in the portion of the signal tube extending through the hot side. An exemplary fuse includes a temperature-sensitive inner member that is deformable upon exposure to temperatures greater than a predetermined temperature. The fuse is operative responsive to a breach in the signal tube to change from a first condition to a second condition to prevent an over-temperature situation on the cool side of the firewall. An outer member substantially enclosing the inner member provides information about the condition of the fuse. A system utilizing the fuse includes a gas turbine engine having a firewall separating a hot side from a cool side, an engine control mechanism disposed on the cool side, and a signal tube extending from a component on the hot side to the engine control mechanism.

Abstract: A plug for an inspection hole of a gas turbine engine is disclosed. The plug may have a stem including a first shaft, wherein a first seal is located circumferentially about the first shaft. The plug may have a swivel seal including a second seal spaced from a ball by a second shaft, and the swivel seal may be rotatably connected to the stem by the ball. The ball and the second seal may be fixed to the second shaft.

Abstract: Apparatus and a method of detecting combustor rumble in a gas turbine engine having combustion equipment that is susceptible to combustor rumble. The method has steps of: locating a dynamic pressure transducer remotely from the combustion equipment; connecting a conduit between the transducer and a location in the engine remote from the combustion equipment and subject to pressure fluctuations due to the combustor rumble; and measuring the pressure fluctuations using the transducer to detect combustor rumble.

Abstract: An arrangement for determining a rotational-speed of a blade rotating around an axis is provided. A transmit-unit is located at the rotating blade, while a receive-unit is located at the rotating hub of the blade. The transmit-unit and the receive-unit are connected by a transmission-system, which is used to transmit a signal from the transmit-unit to the receive-unit. A detection-unit is located at the blade, which is used to detect a force acting on the blade due to the rotation of the blade. The detection-unit is built to interrupt the transmission of the signal when the detected force exceeds a predetermined value. The receive-unit comprises a control-unit, which detects a high rotational-speed of the blade by evaluating the interrupted transmission of the signal. The transmission-system is built as an optical-transmission system, which transmits an optical-signal from the transmit-unit to the receive-unit for evaluation.

Abstract: The turbocharger having a device for detecting a malfunction of the turbocharger, particularly a malfunction of at least one bearing of the turbocharger has the following features: The device for detecting a malfunction of the turbocharger has a memory device, in which the target operating states of an intact turbocharger are stored. The device for detecting a malfunction of the turbocharger further has a comparing device, in which the determined actual operating state of the turbocharger is compared to a corresponding target operating state of an intact turbocharger. The turbocharger further has a measuring device for determining an actual operating state of the turbocharger, wherein the device for detecting a malfunction of the turbocharger emits an error message if the comparing device detects that the actual operating stage deviates from the target operating state by a predefined measure.

Abstract: A gas turbine engine has a signal transmission system comprising a waveguide 40 which enables the transmission of microwave radio signals between a rotor 24 and stationary receiving electronics 32 of the engine. The waveguide 40 is centred on the engine axis 9.

Abstract: A method of securing a releasable component in an assembled engine by inserting a conduit through an aperture in a casing of the engine, the conduit being carried by a borescope and directing the borescope to the releasable component, and supplying an adhesive onto the releasable component through the conduit.

Abstract: A system for measuring clearance between a first object and a second object is provided. The system includes a sensor configuration to generate a first signal representative of a first sensed parameter and a second signal representative of a second sensed parameter. The system also includes a clearance measurement unit configured to process the first and second signals based upon a ratiometric technique to calculate clearance between the first and second objects.

Abstract: Turbine comprising a tubular body that receives an upstream stator, a rotor including a propeller and a downstream stator. The trailing edge of the blades of the upstream stator is inclined through a negative angle relative to a normal relative to the axis, and the leading edge of the blades of the propeller is inclined and rounded in an incline directed downstream. The rotational mounting of the propeller in the turbine involves a fixed shaft installed in the upstream and downstream stators, and which carries an upstream bearing bush and a downstream bearing bush, close to the end of the location of the propeller, and a stop formed by a crown of support pins in an upstream and downstream direction. The propeller comprises a tubular hub through which the fixed shaft extends and which has a bearing bush at each end in order to co-operate at the same time with the corresponding bearing bush of the fixed shaft and with the corresponding peripheral stop.

Abstract: A gas turbine engine simulator comprising a simulator rotor disc which has substantially the same maximum external dimensions as a rotor disc and is manufactured from a material which has a density of less than 220 kg/m3. The simulator rotor disc is manufactured from a foamed plastic material with a closed cell structure. The simulator rotor disc is provided with a cavity in flow communication with a source of simulator coolant fluid, at least one flow outlet, at least one heater unit and at least one thermocouple mounted within said cavity for the measurement of simulator coolant fluid temperature within said cavity.

Abstract: Methods, apparatus and systems for machinery testing and inspection using a manipulator are provided. The apparatus includes a tubular shaft, an operator end coupled to the tubular shaft and including a first spool rotatably coupled to the operator end, an effector including an attachment end that includes a second spool rotatably coupled to the attachment end, and a control cable channeled through the shaft from the first spool to the second spool. The control cable is wound at least partially around the first spool and is wound at least partially around the second spool such that rotation of the first spool rotates the second spool using the control cable.

Abstract: The method consists in depositing, by alumina spraying, an electrically insulating sublayer on the substrate, then in placing the sensor on the electrically insulating sublayer and finally in depositing, by alumina spraying, a cover layer on the sensor and the electrically insulating sublayer. It further includes, before the cover layer is deposited, a step in which an impermeable and thermally insulating cement is applied locally on wires of the sensor.

Abstract: A torque monitoring apparatus is disclosed herein. The torque monitoring apparatus includes a hub extending along an axis of rotation between first and second opposite ends. The torque monitoring apparatus also includes a plurality of spokes positioned on the hub and extending radially outward from the hub to respective distal ends. The torque monitoring apparatus also includes a plurality of projections spaced from the plurality of spokes along the axis of rotation. Each of the plurality of projections extends radially outward from the hub to respective distal ends. The plurality of projections are thinner along the axis than the plurality of spokes.

Abstract: A method and apparatus for monitoring blade vibrations in a turbine engine having blade tip target portions associated with blades. An illumination conduit including a plurality of optical fibers conveys light from a light source to a transmission end of the optical fibers where the light is focused to define an axially elongated projected image. The blade tip target portions pass through the projected image and reflect light to a receptor array defined by receptor ends of a plurality of optical fibers forming an imaging conduit for conveying the reflected light to a sensor array. An imaging end of the imaging conduit radiates an image onto the sensor array that is identical to the reflected light image received at the receptor array to track tangential and axial movement of a predetermined point on the target portion.

Abstract: A turbo machine airfoil, such as a blade or a vane in a compressor, in which the airfoil root portion includes screw threads having a dove tail cross sectional shape, and the rotor disk includes holes having similar screw threads such that a blade or vane can be easily replaced by unscrewing the old blade or vane and screwing in a new blade or vane. A locking pin biased by a spring is located in the root of the airfoil to lock the airfoil in the threaded hole to prevent the airfoil from loosening due to vibrations and to lock the airfoil in place at a desired angle of attack for maximum efficiency of the turbo machine. The removable cover plate is located on the casing and over the rotor disk such that the blade can be removed through the opening without the need to disassemble the turbo machine.

Abstract: A wind turbine blade instrumentation structure and method is provided for fluid dynamic polymer-based contact sensors measuring ambient pressure based on the resistivity changes across the sensor. The pressure sensors may applied in predetermined patterns to airfoil structures, such as wind turbine blades, without impacting the blade structure and fluid dynamic characteristics. The pressure sensors measure blade performance with high fidelity. The pressure measurements are transmitted to processing to determine blade characteristics and environment including flow separation, stagnation point, angle of attack, lift and drag and wind speed. Further processing of the pressure distribution may identify wind shear, up-flow and yaw error.

Abstract: A radial fan (1) with a housing (2) and a fan impeller (3) disposed therein, an air inlet (4) and an air outlet (5) is provided, a pressure space (6) being formed between the latter, and in front of the air inlet (4) a laminar element (7) being disposed which, in a bypass (8) formed therein, has a sensor (9) for recording at least one parameter of the medium flowing through the air inlet (4).