A tire characteristic value measurement apparatus (100) includes a support arm (124) which is provided in vertical movement means (111 to 121). The support arm (124) bears a tire (T) on a roller conveyor (101) from below and has electrically insulative properties. The tire characteristic value measurement apparatus (100) further includes electric resistance value detection means (125 to 139) which is provided in the vertical movement means (111 to 121). The electric resistance value detection means (125 to 139) detects an electric resistance value of the tire T borne by the support arm (124).

A tire characteristic value measurement apparatus (100) includes a support arm (124) which is provided in vertical movement means (111 to 121). The support arm (124) bears a tire (T) on a roller conveyor (101) from below and has electrically insulative properties. The tire characteristic value measurement apparatus (100) further includes electric resistance value detection means (125 to 139) which is provided in the vertical movement means (111 to 121). The electric resistance value detection means (125 to 139) detects an electric resistance value of the tire T borne by the support arm (124).

A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

Provided are a device and a measuring method for measuring an unbalanced moment on a bottom surface of a circular valve core. The device includes a diverging shaped tube, a water tank, a transparent tube, spring dynamometers, laser sources, a circular valve core, and a high-speed camera with a camera stand. Inner shackles and the laser sources are evenly distributed on an outer side of the circular valve core of the device, the spring dynamometers are connected with the inner shackles and with the outer shackles evenly distributed on an inner wall of the transparent tube. The method records an unbalanced state of the circular valve core under an impact of water flow from different orientations with the high-speed camera on the camera stand, the location of the laser point on the outer wall and a tension force of the spring dynamometer are read to calculate a torque of the circular valve core.

Provided are a device and a measuring method for measuring an unbalanced moment on a bottom surface of a circular valve core. The device includes a diverging shaped tube, a water tank, a transparent tube, spring dynamometers, laser sources, a circular valve core, and a high-speed camera with a camera stand. Inner shackles and the laser sources are evenly distributed on an outer side of the circular valve core of the device, the spring dynamometers are connected with the inner shackles and with the outer shackles evenly distributed on an inner wall of the transparent tube. The method records an unbalanced state of the circular valve core under an impact of water flow from different orientations with the high-speed camera on the camera stand, the location of the laser point on the outer wall and a tension force of the spring dynamometer are read to calculate a torque of the circular valve core.

A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

A method for balancing a set of blades intended to be arranged on a bare disc of an aircraft engine, the bare disc comprising a defined number of numbered cells (ai) intended to receive the same defined number of blades, which can have a spread of mass, the method comprising the following steps:—sorting the blades by monotonic order of their mass (mi) to form an ordered set of blades,—separating the ordered set of blades in a balanced manner into four lobes constituted by a first large lobe, by a second large lobe, by a first small lobe and by a second small lobe, the blades being classified into each lobe according to a current placement order, and—arranging the four lobes on the bare disc by making the current placement order of the blades correspond to the numbered cells of the bare disc.

A system and method are provided for controlling a wind turbine in response to a blade liberation event. Accordingly, estimated response signatures for the wind turbine are determined. Sensor data indicative of at least two actual response signatures of components of the wind turbine to a rotor loading are collected. The actual response signatures are compared to the estimated response signatures. The two or more actual response signatures meeting or exceeding the estimated response signatures is indicative of a blade liberation event. In response to detecting the blade liberation event, a rapid shutdown control logic is initiated to decelerate the rotor at a rate which exceeds a nominal deceleration rate of the rotor.