A system includes a vertical molten sulfur pump assembly that includes a top portion adjacent to a first end of the vertical molten sulfur pump assembly and a bottom portion adjacent to a second end of the vertical molten sulfur pump assembly. A pump motor is disposed in the top portion, an impeller is disposed in the bottom portion within an impeller casing, and a shaft is disposed within a central column and connecting the pump motor with the impeller. A pump inlet is disposed at the second end below the impeller casing. The pump inlet and the impeller casing are configured to be immersed in molten sulfur. The vertical molten sulfur pump assembly is configured to pump the molten sulfur into the inlet and upwards through a discharge passageway by rotation of the impeller. A vibration sensor and a temperature sensor are disposed on an external surface of the bottom portion, on or proximate to the impeller casing and the pump inlet. The temperature sensor is configured to measure a temperature of the molten sulfur proximate to the pump inlet. The vibration sensor includes a substrate comprising a polymer and a resonant layer disposed on a surface of the substrate. The resonant layer includes an electrically conductive nanomaterial and is configured to produce a resonant response in response to receiving a radio frequency signal.

A probe adapter includes an adapter body including a probe aperture and a slot. The probe adapter further includes a driver slidably mounted within the slot and slidable between a first position and a second position. The driver includes a first end and a second end opposite the first end. The first end includes a ramped recess extending in a direction from the first end toward the second end. The probe adapter further includes a threaded fastener configured to contact the second end of the driver so as to retain the driver in the first position.

A method for stability analysis of a combustion chamber of a gas turbine engine based on image sequence analysis belongs to the field of fault prediction and health management of aeroengine. Firstly, flow field data inside a combustion chamber of a gas turbine engine is acquired. Secondly, flow field images of the combustion chamber are preprocessed to respectively obtain a discrimination model data set and a prediction model data set. Then, a 3DWaveNet model is constructed as a generation network of a prediction model. A discrimination network of the module is constructed. The generation network and the discrimination network are combined to form the prediction model. Finally, a discrimination model is constructed according to the discrimination model data set; the training set in the discrimination model data set is used for training, and the test set is used for assessment.

Embodiments of the present disclosure include a method for controlling a power generation system, the method including: detecting a heat distribution across a component of a power generation system from a thermal output of the component, during operation of the power generation system; calculating a projected heat distribution across the component based on a library of modeling data for the power generation system; calculating whether a difference between the heat distribution and the projected heat distribution exceeds a thermal threshold; adjusting the power generation system in response to the difference exceeding the predetermined threshold, wherein the adjusting includes modifying an operating setting of the power generation system.

A detection device for a turbine blade of an aircraft engine includes a machine table, a fixing frame, a dip coating mechanism, and a detection mechanism. A sliding cavity is formed in an upper end of the machine table, a support plate is slidably arranged in the sliding cavity, a side end of the support plate is rotatably connected to a chuck, the fixing frame is in an inverted “U” shape and is fixed on the upper end of the machine table, and a mounting barrel is rotatably arranged on the fixing frame. The dip coating mechanism and the detection mechanism are arranged on the machine table, such that wall-hanging sediments in an air film hole and a cooling channel will be exposed to a first photosensitive camera and a second photosensitive camera through fluorescent liquid, thus completing wall hanging and blockage detection of the blade synchronously.

A method of monitoring turbine blade creep in a gas turbine engine is provided. The method includes: receiving an image of a turbine blade of a row of turbine blades, the image having been obtained using a borescope located in the engine adjacent a row of turbine blades; measuring on the image a distance between radially inner and radially outer landmarks on the turbine blade; and comparing the measured distance with a reference distance to determine an amount of creep-induced lengthening of the blade.

A service apparatus for use in maintaining a machine including a stator and a rotor is provided. The service apparatus includes a carriage assembly configured to couple to the rotor. The service apparatus is selectively transitionable between a stowed position in which the service apparatus is rotatable with the rotor and an extended position in which the service apparatus is extended toward the stator. The service apparatus also includes at least one maintenance device coupled to the carriage assembly. The at least one maintenance device is operable to perform a maintenance operation on a surface of the stator with the service apparatus in the extended position.

A system for use in servicing a machine. The system includes a tubular body including a longitudinal axis, a tip end, a dispensing nozzle defined at the tip end, and an interior channel in flow communication with the dispensing nozzle. The tubular body is configured to be flexible. An actuator is configured to selectively modify an orientation of the tubular body, and a reservoir is in flow communication with the interior channel. The reservoir is configured to supply a maintenance fluid to the tubular body for discharge from the dispensing nozzle.

A system for use in servicing a turbomachine, the system including a first tubular body including an interior channel, and a second tubular body. The first and second tubular bodies are bendable between a neutral shape and a biased shape. The bodies are bent when in the neutral shape. The second tubular body includes a tip end, and the second tubular body is translatable within the interior channel. The first tubular body and the second tubular body are rotatable to selectively orient the tip end in multiple degrees of freedom. The system also includes a steering cable extending from the tip end, wherein the steering cable biases the tip end for selective orientation in additional degrees of freedom.

Apparatus and associated methods relate to a system for detecting foreign object debris ingested into an aircraft engine. The system detects such foreign object debris by projecting a beam of light over an inlet of the aircraft engine. When foreign object debris is ingested into the aircraft engine, it intercepts the beam of light and scatters a back-scattered portion of the intercepted beam of light. An optical detector is configured to detect the back-scattered portion of the intercepted beam of light. A processor is configured to determine whether foreign object debris is ingested by the aircraft engine based on a comparison of a threshold value with a signal indicative of the back-scattered portion generated by the optical detector.