An environmental condition may be measured with a sensor (10) including a wire (20) having an ultrasonic signal transmission characteristic that varies in response to the environmental condition by sensing ultrasonic energy propagated through the wire using multiple types of propagation, and separating an effect of temperature on the wire from an effect of strain on the wire using the sensed ultrasonic energy propagated through the wire using the multiple types of propagation. A positive feedback loop may be used to excite the wire such that strain in the wire is based upon a sensed resonant frequency, while a square wave with a controlled duty cycle may be used to excite the wire at multiple excitation frequencies. A phase matched cone (200, 210) may be used to couple ultrasonic energy between a waveguide wire (202, 212) and a transducer (204, 214).

An air temperature sensor with a housing having a skin with a first and second portion, a temperature sensor having at least a portion extending through the housing, a set of fluid passageways defined within an interior of the housing, and a tube to receive bleed air from an aircraft engine located within the interior and to allow hot bleed air into the set of fluid passageways.

A method of measuring a gas turbine engine component of a gas turbine engine according to an example of the present disclosure includes, among other things, providing at least one gas turbine engine component including a coating on a substrate, detecting infrared radiation emitted from at least one localized region of the coating at a first wavelength in a first electromagnetic radiation frequency range, detecting infrared radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength in a second electromagnetic radiation frequency range that differs from the first electromagnetic radiation frequency range, and determining a heat flux relating to the at least one localized region based upon a comparison of the first wavelength and the second wavelength.

Provided herein is a differential temperature sensor which utilizes multiple temperature sensors to quickly and accurately calculate ambient fluid temperature with a reduced response time. The provided systems and methods utilize a first fluid temperature sensor and a second probe temperature sensor to account for the thermal impact of the device on the ambient fluid temperature and the effect of heat within the device, or temperature difference between the probe and fluid temperature, on the first fluid temperature sensor measurement.

A valve device includes: a valve box in which an inlet flow passage into which steam flows and an outlet flow passage through which the steam flows are formed, and in which a valve chamber that connects the inlet flow passage and the outlet flow passage is formed; and a plurality of valve bodies configured to regulate a flow rate of the steam flowing through the outlet flow passage by relative movement to the outlet flow passage. The valve box includes a valve box main body in which the inlet flow passage, the outlet flow passage, and an opening portion are formed, a lid portion that is attachable to and detachable from the valve box main body and closes the opening portion, and a cleaning nozzle that is disposed to penetrate through the lid portion and is configured to supply a cleaning liquid into the valve chamber from the outside.

Methods and apparatus for real-time clearance assessment using a pressure measurement are disclosed. An example method includes determining a first and a second static pressure measurement at a first measurement location and a second measurement location, respectively, relative to the blade tip clearance, determining a normalized pressure measurement using the first and second static pressure measurements, generating a conversion curve to correlate the normalized pressure measurement with a clearance measurement, wherein the conversion curve is developed for the turbine engine during testing at a plurality of operating conditions, and adjusting active clearance control of the blade tip clearance based on the conversion curve.

Methods and systems for operating a gas turbine engine are provided. A health parameter for the gas turbine engine is monitored at a health evaluation device via a first instrument, the health evaluation device being communicatively coupled to a communication link established between a controller, associated with the gas turbine engine, and a second instrument which provides the controller with an operation parameter indicative of an operating condition of the gas turbine engine. The health parameter is compared to a predetermined threshold. When the health parameter is beyond the predetermined threshold, a signal is injected into the communication link to produce a predetermined value for the operation parameter to elicit a health response from the controller associated with the predetermined value.

A heating system for heating a component in a liquid distribution system of an aircraft engine. The liquid distribution system feeds a liquid to the component. The heating system includes an acoustic generator disposed in communication with the component via a liquid passage of the liquid distribution system. The liquid passage defines a length between the acoustic generator and the component. The acoustic generator generates a resonant frequency selected as a function of the length of the liquid passage to generate a standing wave in the liquid within the liquid passage. The standing wave transmitting energy to the component to heat the component.

An aircraft engine comprises an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine, to an outlet within the aircraft engine. At least one strut has a leading edge and a trailing edge and extends across at least part of the air inlet duct. The at least one strut has a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage.

An aircraft engine includes an air inlet duct and at least one strut having a leading edge and a trailing edge. The at least one strut extends across at least part of the air inlet duct and has a strut passage. The trailing edge has one or more edge contours, each defining a contour edge wall recessed from a baseline surface of the trailing edge. The one or more edge contours have a recessed tap in fluid communication with the strut passage.