Provided is a casing deformation amount measuring apparatus for a steam turbine including a casing, a plurality of nuts fixed to an outer surface of the casing, a plurality of bolts individually screwed, at each one side end portion thereof, in the nuts and projecting to an outer side in a diametrical direction of the casing from the outer surface of the casing, and a lagging material held by the plurality of bolts and covering the casing. The casing deformation amount measuring apparatus includes a target mounted on another side end portion of one of the bolts and exposed to the outer side in a diametrical direction of the casing with respect to the lagging material, and a distance meter that is disposed in an opposing relation to the target on the outer side in a diametrical direction of the casing and measures a distance to the target.

A blade damage evaluation apparatus includes: a registration unit for design information of a turbine and maintenance information; an acquisition processor for detection data of sensors; a first discrimination processor for first facility states of the turbine at a plurality of past time points; a classification processor for classes C.sub.n of a plurality of first facility states; a first determination processor for first operating state values of the turbine; another registration unit for first damage rates at past time points; a setting processor of a characteristic function for each of the classes C.sub.n; a second discrimination processor for a second facility state of the turbine at the current time point; a second determination processor for a second operating state value of the turbine at the current time point; and an analyzer for a second damage rate at the current time point.

A system can include a gas turbine and a processing system. The gas turbine can include a compressor coupled to a turbine through a shaft. The processing system can be configured to: automatically transition an operating condition of the system through a plurality of operating states; determine an efficiency of the system at each of a plurality of the operating states; for each of the plurality of operating states: select a future operating state of the system based on the determined efficiency of the current operating state.

A nondestructive method for a volumetric examination of a blade root of a turbine blade while the turbine blade is installed in a turbine shaft of a steam turbine includes attaching a bracket to the turbine blade, the bracket conforming to the geometry of the turbine blade, positioning an ultrasonic phased array probe within a slot formed in the bracket to enable the probe to translate along the geometry of the turbine blade to a desired position for generation of a scan of a portion of the blade root, generating a scan of the desired position by directing ultrasonic waves via the ultrasonic phased array probe, and capturing reflected ultrasonic waves by a receiver to generate the scan and comparing the scan to a reference scan of the blade root to determine defects within the blade root.

Test rig for a back-to-back test of a turbine, including an axle supported in at least one bearing fixed to a carrier, a gear coupled to the axle and a motor coupled to the gear, whereby a gear bearing arrangement comprising two radially extending arms to be coupled to the gear and extending in opposite directions, which arms are pivotally connected to a pair of torque arms extending in a basically parallel direction, with the ends of the torque arms being pivotally coupled to a frame including lateral extensions extending in opposite directions with connection segments, to which segments respective second torque arms arranged in a basically vertical direction in respect to the pair of torque arms are pivotally connected, which second torque arms are pivotally connected to a respective connection element arranged at the carrier.

A stator vane arrangement for a turbomachine comprises a radially inner annular structure, a radially outer annular structure and a plurality of circumferentially spaced vanes extending radially between the inner annular structure and the outer annular structure. At least one of the vanes has a passage extending from the inner annular structure to the outer annular structure. The inner annular structure has at least one radially inwardly extending boss and each boss has a passage extending there-through. The passage in each boss is aligned with a corresponding passage in a vane. Each boss comprises a first portion having a first cross-sectional area and a second portion having a second cross-sectional area which is greater than the first cross-sectional area. The first portion of each boss is positioned between and interconnecting the second portion of the boss and the inner annular structure.

A rotor assembly (30) comprising a rotor (32) having an annular array of rotor blades (34), the rotor mounted to a shaft (38). A phonic wheel (40) coupled to the shaft. A speed sensor (44) axially aligned with the phonic wheel and configured to measure voltage (V), amplitude of the voltage being proportional to clearance (46) between the sensor and phonic wheel. A processor (48) configured to: receive the voltage measurement; derive shaft speed (ω) from the voltage measurement; identify modulation of the voltage amplitude at a frequency which is an integer multiple of the shaft speed; compare voltage amplitude to a threshold; and output a rotor damage signal based on the comparison.

A turbine arrangement for a gas turbine engine comprising a turbine shaft. An axial array of turbine rotors, having a first axial end and a second axial end. A drive arm coupled between the turbine shaft and the first axial end. A measurement system arranged to measure a parameter of the turbine arrangement, the measurement system positioned at the second axial end. The parameter may be rotational speed.

According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine. The bowed rotor sensor system also includes a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data.

One example aspect of the present disclosure is directed to a method for measuring engine performance. The method includes receiving a plurality of parameters related to engine performance. The method includes receiving an indication of an engine wash event. The method includes determining an effectiveness of the engine wash event based on the plurality of parameters. The method includes performing a comparison of the effectiveness of the engine wash event with an expected effectiveness of the engine wash event. The method includes performing a control action based on the comparison.