A pressure and temperature probe of a gas turbine engine includes a base portion and an airfoil portion extending from the base portion to an end portion located at a distal end of the probe. The airfoil portion includes a leading edge located at an upstream end of the probe relative to a direction of airflow across the probe. A temperature sensor is located in a temperature sensor chamber located in the airfoil portion, and a temperature airflow hole in the end portion is configured to admit an airflow into the temperature sensor chamber around the temperature sensor. The temperature airflow hole is configured and positioned such that the airflow admitted via the temperature airflow hole has a turning angle of less than 90 degrees into the temperature sensor chamber.

A measurement system for an aircraft gas turbine engine includes a probe and a heated-gas source in fluid communication with the pressure probe. The probe includes a probe body defining an internal cavity of the probe. The probe further includes a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow. The probe further includes a plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.

A measurement system for an aircraft gas turbine engine includes a probe and a heated-gas source in fluid communication with the pressure probe. The probe includes a probe body defining an internal cavity of the probe. The probe further includes a plurality of sensor inlet ports extending through the probe body and configured to receive a sensed fluid flow. The probe further includes a plurality of probe conduits. Each probe conduit of the plurality of probe conduits is coupled to a respective sensor inlet port of the plurality of sensor inlet ports and extending from the respective sensor inlet port to an exterior of the probe body. The heated-gas source is configured to supply a heated gas flow to one or both of: the plurality of sensor inlet ports via the plurality of probe conduits and an interior of the probe body outside of the plurality of probe conduits.

The invention relates to a temperature sensor comprising a thermocouple (7) defining a hot point (13), said temperature sensor comprising a mineral insulated cable (14) with an outer diameter greater than 2 mm and less than 5 mm and a reinforcement tube (60) from which projects the mineral insulated cable at the hot point end, so as to form a swaging.

Method for the manufacture of a temperature sensor with a thermocouple comprising the following successive steps: a) introduction, in a support tube made of a ceramic material, of two thermocouple wires until they extend beyond said support tube; b) welding the ends of said thermocouple wires extending beyond said support tube so as to form a thermocouple hot point; c) introduction, at least partially, of the support tube into a reinforcement tube made of a stainless steel; d) fixing a cap onto said reinforcement tube so as to protect said hot point.

Systems and methods for operating a rotorcraft engine are described herein. Measurements indicative of at least one of current temperature and current pressure at an inlet of the engine are obtained from at least one sensor while the rotorcraft is in flight. At least one current inlet loss is determined from the measurements. Current available engine power of the rotorcraft engine is determined based on the at least one current inlet losses. A visual indication of the current available engine power is produced via a flight display.

A temperature sensor integrated type semiconductor pressure sensor apparatus includes a temperature detection device, a lead wire covered with a lead wire protection material, and a terminal, which are integrated together by a thermoplastic resin. This can prevent the lead wire from being deformed in the assembly process, thereby simplifying the assembly process. Furthermore, the temperature detection device is exposed from the opening at the tip of the protrusion, which can secure enough temperature response. Furthermore, the temperature detection device, the lead wire and the lead wire protection material are covered with the thermoplastic resin, so they are protected from combustion gas component, oil contaminant and corrosion product included in intake air.

A physical quantity detector includes a housing, a circuit board, a cover, a resin member, a conductor, and a conductive member. The circuit board includes a board surface. The cover faces the board surface and defines, together with the hosing, a passage through which the target fluid flows. The conductor includes a passage side portion and a connecting portion. The conductive member electrically connects the connecting portion to the circuit board. The conductive member includes a first end in the thickness direction facing a contact target that is either one of the connecting portion or the board surface. The first end includes a contact portion in contact with the contact target and a contactless portion away from the contact target in the thickness direction.

An intake air temperature estimation system includes: an adiabatically compressed intake air temperature computing unit that computes an adiabatically compressed intake air temperature based on an intake air temperature before compression, an intake air pressure before compression and an intake air pressure after compression; and an estimated intake air temperature computing unit that computes an estimated intake air temperature. The estimated intake air temperature computing unit variably sets a coefficient of the function in response to an amount of change per unit time in the intake air pressure after compression such that a followability of the estimated intake air temperature to the adiabatically compressed intake air temperature at the time when the amount of change is large is higher than a followability of the estimated intake air temperature to the adiabatically compressed intake air temperature at the time when the amount of change is small.

A temperature sensor includes a pair of thermocouple wires, a temperature measuring junction formed by joining tip ends of the pair of thermocouple wires together, an outer tube having a tip end in which the temperature measuring junction is held, an insulator insulating the pair of thermocouple wires from the outer tube, and a glass seal filled in a base end of the outer tube. The pair of thermocouple wires disposed in the outer tube have surfaces where passive films are respectively formed due to the oxidization of the metallic materials on the surfaces of the pair of thermocouple wires.