Abstract: A measurement system for an aircraft gas turbine engine includes an instrumentation hub including at least one probe, and a shield hub positioned axially adjacent the instrumentation hub. The instrumentation hub is rotatable about a rotational axis. The shield hub includes at least one shield which is radially aligned with the at least one probe of the instrumentation hub. The shield hub is rotatable about the rotational axis independent of the instrumentation hub.

Abstract: A measurement system for an aircraft gas turbine engine includes an instrumentation hub including at least one probe, and a shield hub positioned axially adjacent the instrumentation hub. The instrumentation hub is rotatable about a rotational axis. The shield hub includes at least one shield which is radially aligned with the at least one probe of the instrumentation hub. The shield hub is rotatable about the rotational axis independent of the instrumentation hub.

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 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: The present invention relates to a vibration dampening mechanism for use in recreational vehicle applications, preferably for connecting the steering stem to handle bars or other similar steering device. The vibration and noise dampening connection mechanism in accordance with the present invention includes a rubber element entrapped and bonded between two plates, linking the handlebar and the steering post of recreational vehicles. [NOTE: As used herein, the term “rubber” relates to any elastic and primarily non-metallic materials such as rubber, elastomers, or combinations thereof].

Abstract: The present invention relates to a floor board which can be attached to various types of rigid frame used in vehicles, structures or equipment. To minimize the formation and accumulation of debris, the floor board of the present invention includes a fixedly positioned supporting plate which is also connected to a flexible body having protuberances which extend away from the supporting plate in such a way as to deform under a loading force.