A cooktop appliance or griddle assembly may include a cooking platter, a spring-loaded platform, and a sensor body. The cooking platter may define a top surface and a bottom surface. The spring-loaded platform may be mounted below the cooking platter. The sensor body may be attached to the spring-loaded platform in biased conductive engagement with bottom surface.

The present invention provides, in order to improve detection accuracy, a freezing detection device comprising: a strut having a mounting space formed therein, the strut being installed in a freezing measurement area in which a freezing detection object unit is disposed; a probe made of a magnetostrictive material and disposed to penetrate the strut, the lower end of the probe being inserted into the mounting space, the upper end thereof being exposed to the freezing measurement area, the probe having a drive coil disposed so as to surround the outer periphery of one side of the interior of the mounting space such that a driving magnetic field for magnetostrictive vibration is formed, and the probe having a feedback coil disposed so as to surround the outer periphery of the other side of the interior of the mounting space while being spaced apart from the drive coil by a predetermined interval; a variable adjustment unit circuit-connected to the drive coil and the feedback coil such that errors of a vibration frequency occurring in the probe are adjusted; a magnet unit disposed along outer peripheries of the drive coil and the feedback coil such that the vibration displacement of the probe increases, thereby forming a bias magnetic field; an elastic member disposed in the mounting space and provided to have an elastic modulus preconfigured such that a vibration frequency occurs in the probe, the elastic member generating magnetostrictive vibration and elastically supporting the probe; and so as to apply a voltage corresponding to a vibration frequency, the calculation control unit indirectly assessing the freezing condition of the freezing detection object unit through a change in the vibration frequency of the probe resulting from a freezing load.

A system may include a static air temperature probe attached to an aircraft, an electronic flight instrument system, and a processor. The processor may be configured to measure a static air temperature at the aircraft using the static air temperature probe. The processor may further be configured to calculate a Mach number associated with the aircraft based at least partially on the static air temperature. The processor may also be configured to calculate a true air speed of the aircraft based on the Mach number. The processor may display an indication of the true air speed using the electronic flight instrument system. The processor may also be configured to calculate the speed of sound based at least partially on the static air temperature.

A thermally isolated sensor associated with a gas turbine engine includes a sensor probe configured to measure a temperature of a fluid associated with the gas turbine engine, and a base to be coupled to the gas turbine engine. The thermally isolated sensor includes a leading projection coupled to the base that extends into the fluid. The leading projection is configured to be heated by a heat source associated with the gas turbine engine. The thermally isolated sensor includes a trailing projection coupled to the base that extends into the fluid. The trailing projection is downstream from the leading projection. The trailing projection includes an inlet, and the sensor probe is disposed within the inlet and thermally isolated from the leading projection.

A system includes a device having a first surface configured to be exposed to airflow about an exterior of an aircraft, the device including a first self-compensating heater configured to heat the first surface, a first current monitor configured to sense a first measurement value representing electrical current flow through the first self-compensating heater, one or more processors, and computer-readable memory encoded with instructions that, when executed by the one or more processors, cause the system to receive aircraft flight condition data and produce an icing condition signal based upon the first measurement value and the aircraft flight condition data.

A probe for the measurement of the total pressure or temperature of a two phase wet gas flow is also disclosed. Embodiments provide a stem, a tip on the top of the stem, a cup serving as a shield is formed in the tip, a at least one tube or thermal element positioned within the cup serving as a measuring device for the incoming wet gas flow; at least one hole which passes through at least one wall of the cup; and a pressure changing device configured to accelerate the wet gas flowing around the cup. A method and system for the measurement of the total pressure or temperature of a two phase wet gas flow is also disclosed.

A gas turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. At least one of the combustion section or turbine section can have an exhaust gas passage. The turbine engine can also include an exhaust gas temperature sensor with a housing having an elongated probe portion. The elongated probe portion can have an outer wall bounding an interior. A temperature probe can be provided within the housing.

A thermocouple system, has a metal feedthrough having a cylindrical portion having an axis of symmetry and a terminal end region arranged thereon, which completely closes the cylindrical portion, and which has at least two passageways, the opening cross-section of which is smaller than the cross-sectional surface vertical to the axis of symmetry through the cylindrical portion. Through one passageway, a thermocouple is guided, and in the region of the passageway, the thermocouple is connected to the end region in a fluid-tight manner by way of a seal.

An air temperature sensor arrangement for a vehicle includes a temperature sensor housing having a base portion, an inlet and an outlet. Also included is a main flow path defined by a continuously curvilinear wall, the main flow path extending from the inlet to the outlet for separating particulate matter from an inlet airflow. Further included is a temperature sensor disposed within an internal cavity of the temperature sensor housing.

A total air temperature probe includes a housing having inner surfaces defining an airflow passage, a first section of the airflow passage of the housing having an airflow inlet scoop with a first cross-sectional area and an inertial separation bend downstream of the airflow inlet scoop, wherein the airflow passage is configured to be substantially straight; and a second section of the airflow passage of the housing having a main exit channel and an elongated outlet with a second cross-sectional area, wherein the airflow passage is contoured to direct particle deflections to the elongated outlet, wherein the second section is downstream from the first section, and wherein the first cross-sectional area is greater than the second cross-sectional area