A communication adapter of a gas turbine engine of an aircraft includes a housing configured to be coupled to the gas turbine engine, a plurality of antennas integrated in the housing, a memory system and processing circuitry. The processing circuitry is configured to establish communication with an engine control mounted on the gas turbine engine, establish wireless communication between the communication adapter and an offboard system external to the aircraft through at least one of the antennas integrated in the housing of the communication adapter, and authenticate communication requests at the communication adapter for data sent between the offboard system and the engine control.

A damage evaluation device evaluates damage of equipment, including an operation data obtaining unit which detects a state of the equipment to obtain the state as operation data; an operating state quantity evaluation unit which calculates an operating state quantity including at least one of temperature and generated stress at a predetermined evaluation-target site of the equipment, based on the operation data; a material deterioration evaluation unit which evaluates a material deterioration quantity of a material forming the equipment, based on the operating state quantity; a risk evaluation unit which evaluates at least one of a cumulative damage quantity of the material forming the equipment and failure risk, based on the operating state quantity and the material deterioration quantity; and a recommended maintenance time presentation unit which presents a recommended maintenance time of the equipment based on a result of the evaluation of the risk evaluation unit.

There is provided a system and a method for operating a multi-engine rotorcraft. When the rotorcraft is cruising in an asymmetric operating regime (AOR) at least one engine is an active engine and is operated in an active mode to provide motive power to the rotorcraft and at least one second engine is a standby engine and is operated in a standby mode to provide substantially no motive power to the rotorcraft, at least one of a power level of the at least one second engine is increased and at least one variable geometry mechanism of the at least one second engine is moved to shed any ice accumulation on the at least one second engine.

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.

The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.

Devices, systems and methods for leak detection are provided herein. Also provided are devices, systems and methods for monitoring and/or measuring fluid usage. In some aspects, a system comprising a sensor, a processing system, and a platform are provided. In some aspects, the sensor may be coupled to a spinning device. The sensor can be configured to detect fluid data, which can comprise, for example, displacement data of liquid and/or movement data associated with the liquid in a container and/or flow data associated with a flow of fluid in a conduit. The processing system can be coupled with the sensor and configured to communicate the fluid data. The platform can comprise an application communicatively coupled to one or more databases storing evaluation data (e.g., known pattern data) and configured to receive the fluid data and determine if there is a leak.

A mounting member for a sensor for a turbomachine having an axis is disclosed. The mounting member includes a body configured to mount to a portion of a circumferential interior surface of a casing of the turbomachine. An opening extends through a radially inner surface of the body, and is configured to position the sensor facing radially inward relative to the axis. A passage in the body extends longitudinally through the body to route a communications lead of the sensor circumferentially relative to the circumferential interior surface of the casing.

A contamination sensor for a gas turbine engine is disclosed herein. The contamination sensor is made of a selected composition of material and includes a base alloy, an alloy for improving oxide formation, and at least one element from the transition metal group. The composition of the contamination sensor can be adjusted to react with specific contaminants at specific temperature ranges.

A phonic wheel having a body and a tooth is disclosed. An embodiment of the phonic wheel includes a body that is configured to rotate about a rotation axis. The tooth is attached to the body. The tooth has a first axial end relative to the rotation axis, a second axial end opposite the first axial end, and a mid portion extending between the first and second axial ends. The mid portion has a substantially axially uniform height from the body. The first axial end has a greater height from the body than the height of the mid portion.

The method can include sensing operating conditions of the gas turbine engine; generating a base value signal of a control parameter of the bleed valve based on the sensed operating conditions and on control data; determining whether a contaminant management condition is met; generating a control value signal of the control parameter including the base value signal and, when the contaminant management conditions is met, the control value signal further including a contaminant management signal of the control parameter value of the valve superposed to the base value signal, the contaminant management signal including at least three successive back and forth fluctuations of the control parameter value relative the base value signal over a period of 10 seconds or less; and controlling an actuator of the bleed valve based on the control value signal.