A method (400) of measuring rotor blade tip deflections of turbomachine rotor blades (R.sub.1, R.sub.2) during operation using Blade Tip Timing (BTT) includes measuring (402), by a proximity sensor (202), a proximity signal caused by a moving rotor blade (R.sub.1, R.sub.2) and determining (412), by a control module (212), a Time-of-Arrival (ToA). The method (400) includes measuring a time that the shaft starts to rotate a measurable angular distance and a time the shaft has completed its rotation of the measurable distance and storing (406) timing data indicative of a plurality of ToA measurements of the rotor blade (R.sub.1, R.sub.2) and the zero crossing times. The method (400) includes determining the shaft Instantaneous Angular Position (IAP) between at least two zero crossing times, which determination comprises expressing the shaft IAP between at least two zero crossing times as a continuous, non-constant IAP mathematical function of time, with unknown function coefficients and calculating the unknown function coefficients of the IAP mathematical function.

A method for detecting damage to one or more mobile blades of an impeller of an aircraft engine, includes measuring the speed of the engine, and for each blade acquiring, by a plurality of sensors, measurements of blade-tip passage times; calculating for each sensor, a deflection of the blade tip; extracting a dynamic component of deflection for each of the calculated deflections; detecting the number of functioning sensors; selecting the dynamic components to be processed based on the detecting step; determining, for at least one blade, a variation of the dynamic behavior of the blade for each functioning sensor; and, for each blade for which a variation of the dynamic behavior has been determined, identification of potential damage to the blade.

A rotating machine control device is provided with: an operating terminal for changing a parameter of the rotating machine; a clearance measuring device which measures the amount of clearance between a rotor and a casing; and a control device body. The control device body, in accordance with the amount of clearance measured by means of the clearance measuring device, determines an operating amount for the operating terminal so as to vary the rate of change in the parameter, and outputs the operating amount to the operating terminal.

Magnetic levitation bearing structure includes a cylinder body, a rotating shaft, a motor stator, a motor rotor, an axial bearing, a radial bearing and a displacement sensing device; the displacement sensing device, the axial bearing stator, and the radial bearing stator are directly fixed on an inner wall of the cylinder body.

A method for calibrating a position sensor of a variable vane assembly for a gas turbine engine includes positioning an actuator member in at least one predetermined position, determining a first measured position of the actuator member in the at least one predetermined position with a first channel of a position sensor, determining a second measured position of the actuator member in the at least one predetermined position with a second channel of a position sensor, determining a measured position difference between the first measured position and the second measured position, and calibrating the second channel of the position sensor by adjusting the second measured position by the measured position difference to determine a second calibrated position.

A primary lock system for a translating cowl thrust reverser system includes a primary lock having a housing, a lock, and a manual mechanism. The lock is disposed at least partially within, and is movable relative to, the housing and is movable between a lock position and an unlock position. The manual mechanism is coupled to the lock and is configured, in response to a manual input force supplied to the manual mechanism, to: selectively move from a first position to a second position, whereby the lock is selectively moved from the lock position to the unlock position, respectively, and selectively prevent movement of the lock out of the lock position.

A turbine engine including a stationary component having a probe opening, a plurality of rotor blades rotatable relative to the stationary component, and a sensor assembly disposed within the probe opening. The sensor assembly includes a sensor and a shutter mechanism having a shutter frame with a sensing window and at least one leaf member coupled to the shutter frame. The sensor assembly includes an actuator including a rotatable member having a receiving slot and a stator having a stopper member within the receiving slot. The rotatable member rotates relative to the stator over a range of motion defined relative to the stopper member, and the rotatable member is coupled to the at least one leaf member such that rotating the rotatable member in a first direction uncovers the sensing window, and such that counter-rotating the rotatable member in a second direction covers the sensing window with the at least one leaf member. Selectively covering the sensor when not in use protects the sensor from exposure to harsh conditions, extending its operative life.

Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes an annular substrate extending along an axial direction, the annular substrate defining a cavity at a radially inward surface of the annular substrate, and a smart structure coupled to the annular substrate, the smart structure including a support structure; an actuator structure to at least one of expand or contract in response to a change in temperature of the actuator structure, and a variable surface coupled to the support structure, the support structure to move the variable surface in a radial direction.

A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface, are circumferentially spaced around the circular disk, and extending along the longitudinal axis from a first end portion to a second end portion. At least part of the first end portion and/or of the second end portion comprises a material having higher magnetic permeability than that of a remainder of the position markers.

Apparatus and associated methods relate to health-monitoring of a magnetic speed probe. An inductive coil of the magnetic speed probe is used for two purposes: i) to sense a changing magnetic field caused by rotation of a rotating member; and ii) to radiatively transmit radio-frequency signals for determining the health of the magnetic speed probe. A signal generator coupled to the inductive coil of the magnetic speed probe generates the radio-frequency signals that, when conducted by the inductive coil, causes an inductive coil to act as a radio transmitter by radiatively transmitting the radio-frequency signals. The radio-frequency signals transmitted by the inductive coil are detected by a radio receiver. The radio-frequency signals received are indicative of health of the magnetic speed probe.