Abstract: 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.

Abstract: A fluid probe includes a heat spreader structure that defines therein a fluid chamber that is in fluid communication with an external environment of the probe, and a thermal energy source in thermal communication with the heat spreader structure. The heat spreader structure may be made from heat pipes, which function as both temperature-control elements and structural elements. The thermal coupling of the heat spreader structure and the thermal energy source may be used to transfer heat between the two, heating, cooling, and/or maintaining temperature of the heat spreader structure. The fluid probe may have any of a variety of uses, for example being a pitot tube for an aircraft, a fluid sampling device, a medical device, or a device for injecting a fluid.

Abstract: A fuel injector for a turbomachine includes an inner heat shield having an air cavity wall defining an air cavity for allowing air to flow therethrough. The inner heat shield includes an integral air swirler forming a downstream end thereof. The integral air swirler extends in an axially downstream direction at least as far as a fuel distribution channel defined on or in a fuel distributor of the injector to direct airflow at an outlet of the fuel distributor.

Abstract: An air data probe is provided. The air data probe includes a pitot probe having a mounting base or flange, support strut, and tube with a forward facing inlet that is configured to capture a total pressure of the surrounding air, at least three dams placed within the tube of the pitot probe for blocking the ballistic trajectory of water droplets or ice crystals from passing directly through the tube to a downstream pressure sensing element, and a heater element integrated into the tube of the pitot probe on the outside of the dams. The at least three dams are oriented within the tube of the pitot probe in such a way that the dam locations are configured for two or more installations of the air data probe.

Abstract: A pitot tube having an inclined surface according to one embodiment may comprise: a housing which forms the outer appearance of the pitot tube; an opening which is arranged on the front side of the housing to allow a fluid to be injected thereinto; a first flow path which is connected to the opening; a slit which is arranged on the side of the housing to allow the fluid to be introduced thereinto; a second flow path which is connected to the slit; and a heater for heating frozen ice introduced into the opening and the slit to liquefy the ice, wherein the first flow path may be located above the center of the opening. Further, an inclined surface may be provided between the first flow path and the opening such that the liquefied fluid collides with the inclined surface after passing through the opening.

Abstract: An improved instrument for measuring low indicated air speed greatly reduces variation with one or more of time, temperature, and ambient pressure change. This is accomplished by periodically re-zeroing the transducer using only a single electronically controlled valve. Re-zeroing may be initiated in response to a change in the internal temperature of the transducer.

Abstract: A multi-part air data probe sensor assembly facilitating rapid replacement is provided. One example air data probe sensor assembly comprises a mount plate interface including at least one mount plate electrical connector configured to mate with electrical lines of an aircraft and at least one mount plate pneumatic connector configured to mate with pneumatic tubes of an aircraft; and a detachable sensor body having at least one sensor electrical connector that is coupled with the at least one mount plate electrical connector and at least one sensor pneumatic connector that is coupled with the at least one mount plate pneumatic connector; and a mechanical seal provided between the mount plate interface and the detachable sensor body, wherein the mechanical seal is composed of a moisture blocking material.

Abstract: An air data probe comprises an elongated body structure having a proximal end and a distal end, with the elongated body structure including an outer surface and an opposing inner surface that defines an interior channel. A probe tip is located at the distal end of the elongated body structure, with the probe tip including an outer surface and an inner surface that are contiguous with the outer an inner surfaces of the elongated body structure. The probe tip has an opening in communication with the interior channel that allows outside air to pass from the probe tip into the interior channel. An electrical heater cable is coupled to the elongated body structure and the probe tip. The electrical heater cable comprises a compact double layer helix portion coupled to the elongated body structure or the probe tip, or coupled to both the elongated body structure and the probe tip.

Abstract: A pitot tube includes a substantially cylindrical body portion and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening and a radially tapering outer surface extending from the body portion toward the inlet opening. Another pitot tube includes a substantially cylindrical body portion and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening. One or more electrical coils including one or more coil wraps are located at an interior of the pitot tube. One or more bulkheads are located between a forwardmost coil wrap and a drainage feature to limit travel of particles ingested into the interior.

Abstract: Methods for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

Abstract: A pitot tube is provided having a tube wall and a heating arrangement for generating heat for heating thereby at least a portion of the tube wall to prevent the tube from becoming clogged with ice. The heating arrangement includes a radiation absorbing surface configured for absorbing electromagnetic radiation (EMR) and generating the heat. At least one radiation conveying portion is provided for receiving EMR from an EMR source and conveying it to the radiation absorbing surface.

Abstract: A pitot tube includes a substantially cylindrical body portion and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening and a radially tapering outer surface extending from the body portion toward the inlet opening. Another pitot tube includes a substantially cylindrical body portion and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening. One or more electrical coils including one or more coil wraps are located at an interior of the pitot tube. One or more bulkeads are located between a forwardmost coil wrap and a drainage feature to limit travel of particles ingested into the interior.

Abstract: A probe for measuring the total pressure of a flow and a method for implementing the probe is provided. The probe is intended to be fitted in an aircraft. The probe comprises a Pitot tube and means for reheating the probe assembly. The probe also comprises means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe. If the temperature delivered by the means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow is less than the first reference temperature, then an additional reheating of regions of the Pitot tube likely to accumulate particles conveyed by the flow is triggered.

Abstract: A differential-pressure flowmeter that can reduce (eliminate) a difference between the ambient temperature of one pressure sensor and the ambient temperature of another pressure sensor so as to allow for accurate and stable pressure measurement is provided, and a flow-rate controller equipped with such a differential-pressure flowmeter is provided. Provided are a body having a main fluid channel through which a fluid, whose pressure is to be measured, flows, and two pressure sensors held by the body and arranged in series relative to the main fluid channel, and a temperature balancer composed of a material with high thermal conductivity is accommodated in a recess that is formed in the body located below the two pressure sensors.

Abstract: An airflow sensor apparatus for measuring flow rate includes a pitot tube with a bypass channel wherein the pitot tube extends halfway into a flow channel in order to reduce a pressure drop. One or more upstream taps can be spaced along the pitot tube facing into a direction of a flow stream which directs the fiow to the bypass channel. At least one or more downstream taps can be located to face perpendicular to the direction of flow, such that the fluid after passing over a flow sensor passes through the downstream tap(s). The upstream tap senses stagnation pressure and the down stream tap senses static pressure which is exerted in all directions in the flow channel in order to determine a velocity pressure based on a difference between pressures.

Abstract: A method of generating, for an aircraft, a total air temperature compensated for recovery or deicing heater error includes measuring a total air temperature with a total air temperature probe. A local angle of attack for the total air temperature probe is determined. Then, a corrected total air temperature, compensated for recovery or deicing heater error, is generated as a function of the measured total air temperature and the determined local angle of attack for the total air temperature probe.

Abstract: A smart probe system for an aircraft receives an input from a heated total air temperature sensor. When on the ground, the heater for the total air temperature probe is cycled so that when a preselected temperature is indicated by the temperature sensing element in the total air temperature probe, the heater power is turned off, and as the total air temperature probe cools, changes. Changes in indicated temperature from the temperature sensing element are measured and the changes analyzed and used for determining outside air temperature. The outside air temperature can be calculated by determining the rate of change in the temperature while the probe cools. A complimentary method is to determine when the indicated temperature stabilizes, after the heater is turned off, and deriving outside air temperature from the stabilized temperature signal from the sensing element.