Abstract: A system for determining rotor-dynamic orbit information including an engine case supporting at least one engine stage, each at least one engine stage including a rotor having blades; at least one blade tip sensor operatively coupled to the engine case and in operative communication with the blades; at least one compensation sensor in operative communication with the at least one blade tip sensor; and an orbit controller in operative communication with the at least one blade tip sensor and the at least one compensation sensor.

Abstract: An inspection method is provided during which an inspection scope is arranged with a component. The inspection scope includes a transducer and a vibration isolator. The arranging of the inspection scope includes preloading the transducer against the component through the vibration isolator where the transducer contacts a surface of the component. Vibrations in the component are induced using the transducer. A vibratory response in the component excited by the vibrations is measured using the transducer to provide sensor data.

Abstract: An inspection method is provided during which an inspection device is arranged with a specimen component. The inspection device includes a piezoelectric actuator, an isolator and a piezoelectric sensor. The piezoelectric actuator engages and is preloaded against a surface of the specimen component sequentially through the isolator and the piezoelectric sensor. The isolator electrically isolates the piezoelectric actuator from the piezoelectric sensor. Vibrations are induced in the specimen component using the piezoelectric actuator. A vibratory response in the specimen component excited by the vibrations is measured using the piezoelectric sensor. Response data indicative of the vibratory response measured is provided using the piezoelectric sensor.

Abstract: An inspection method is provided during which a head of an inspection scope is inserted into an interior of a powerplant. The head of the inspection scope includes an actuator and a sensor. The powerplant includes a component within the interior of the powerplant. The head of the inspection scope is abutted against a surface of the component. Vibrations in the component are induced using the actuator. A vibratory response excited by the vibrations is measured using the sensor to provide measurement data. The measurement data is filtered to provide filtered data, and the filtering includes detrending the measurement data.

Abstract: A resonance inspection system includes a processing system. The processing system is configured to process resonance data including a vibratory response signature of a component to generate a plurality of different resonance spectra waveforms. The plurality of different resonance spectra waveforms includes a first resonance spectra waveform and a second resonance spectra waveform. The processing system is further configured to identify a presence or an absence of a structural mode of the component using the first resonance spectra waveform and the second resonance spectra waveform. The presence of the structural mode is identified by determining the first resonance spectra waveform includes a peak at a first frequency of the portion of the frequency range and the second resonance spectra waveform includes a maximum or a minimum slope point at a second frequency of the portion of the frequency range. The first frequency and the second frequency are within a predetermined frequency range threshold.

Abstract: A resonance inspection system includes a probe and a control assembly. The probe includes a sense piezoelectric transducer and a drive piezoelectric transducer. The control assembly includes a measurement channel, a signal generator, and a grounding subassembly. The measurement channel is electrically connected to the sense piezoelectric transducer by a sense circuit. The signal generator is electrically connected to the drive piezoelectric transducer by a drive circuit. The grounding subassembly includes a first ground and a second ground. The first ground is disposed on the sense circuit. The second ground is disposed on the drive circuit. The first ground is galvanically isolated from the second ground.

Abstract: A fluid system is provided that includes a first actuator, a second actuator and a valve system. The valve system includes a first control valve, a second control valve and a transfer valve. During a first mode of operation, the transfer valve is configured to fluidly couple the first control valve to the first actuator and fluidly couple the second control valve to the second actuator, and the transfer valve is also configured to fluidly decouple the first control valve from the second actuator and fluidly decouple the second control valve from the first actuator. During a second mode of operation, the transfer valve is configured to fluidly couple the first control valve to the first actuator and the second actuator, and the transfer valve is also configured to fluidly decouple the second control valve from the first actuator and the second actuator.

Abstract: A fluid system is provided that includes a first actuator, a second actuator and a valve system. The valve system includes a first control valve, a second control valve and a transfer valve. During a first mode of operation, the transfer valve is configured to fluidly couple the first control valve to the first actuator and fluidly couple the second control valve to the second actuator, and the transfer valve is also configured to fluidly decouple the first control valve from the second actuator and fluidly decouple the second control valve from the first actuator. During a second mode of operation, the transfer valve is configured to fluidly couple the first control valve to the first actuator and the second actuator, and the transfer valve is also configured to fluidly decouple the second control valve from the first actuator and the second actuator.

Abstract: A system for determining rotor-dynamic orbit information including an engine case supporting at least one engine stage, each at least one engine stage including a rotor having blades; at least one blade tip sensor operatively coupled to the engine case and in operative communication with the blades; at least one compensation sensor in operative communication with the at least one blade tip sensor; and an orbit controller in operative communication with the at least one blade tip sensor and the at least one compensation sensor.