Abstract: An engine over speed detection circuit for determining an engine over speed condition is described. The circuit includes a detection unit configured to send a pulsed signal indicative of engine speed; a reactive impedance configured to discharge upon receipt of a pulse of the pulsed signal at a rate defined by the pulsed signal; a comparator unit to compare a voltage or current value of the reactive impedance with a threshold value and to output the result of the comparison at the rate of the pulsed signal.

Abstract: An optical measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one light source for emitting light that impinges on a blade surface of each blade in a row of blade assemblies. The system also includes a video device for imaging the blades as the blades rotate about the center axis. Further, the system includes a controller for controlling operation of the light source and video device. The controller detects a pixel intensity associated with each blade and a spacing between each pixel intensity wherein a change in spacing between consecutive pixel intensities indicates that a distance between consecutive blades has changed relative to the first distance thereby indicating at least one locked blade assembly.

Abstract: An apparatus which includes an aspirated smoke detector, and a pre-filter coupled to an inflow port of the detector wherein the pre-filter carries a removable filter element. The filter element is configured such that when it is removed, fluid flow through the filter is blocked. When the filter element is present in the pre-filter, fluid flow through the filter is permitted.

Abstract: A method is provided for detecting fuel discharge from a lubricant in a housing of an internal combustion engine. A first lambda deviation is measured by a lambda sensor for a first mass air flow supplied in an intake tract of the engine. A second lambda deviation is measured by the lambda sensor for a second mass air flow that differs from the first mass air flow, and is supplied in an intake tract of the engine. An actual comparative value is calculated from the measured first and second lambda deviations. A desired comparative value indicative of the fuel discharge is calculated from a first desired lambda deviation for the first mass air flow, and a second desired lambda deviation is calculated for the second mass air flow. The fuel discharge is detected based on a comparison of the actual comparative value and the desired comparative value.

Abstract: A fill level gauge is described with a rinsing device for rinsing a fill level sensor, comprising a sensor for detecting a measuring signal as well as a measurement device connected to the sensor for determining a measurement from the detected measuring signal, with the measurement device being connected to a comparator for comparing the measurement determined with a first reference value at a predetermined condition of comparison, which comprises a control signal output for issuing a control signal, with the rinsing device being coupled to the control signal output or being connected to the control signal output such that, when the condition of comparison is fulfilled, the control signal output transmits a control signal to the rinsing device for activating said rinsing device so that the rinsing device is activated.

Abstract: A system for inspecting a turbomachine includes a traverse actuator system having a carriage configured to move a probe into and out of the turbomachine. The traverse actuator system has a track with a plurality of linearly arranged teeth. The track is configured for operation with the carriage. A motor is operably connected with the carriage and track, and the motor is configured to engage the plurality of linearly arranged teeth so that operation of the motor forces the carriage to move along the track.

Abstract: A gas detector includes a detecting element, a circuit board, a housing case having a gas introduction hole, and a metal member which covers the gas introduction hole. The detecting element is disposed under the metal member. The gas detector further includes a detecting element wiring fusing prevention member which is electrically conductive and is electrically connected to a grounding line of the circuit board. The detecting element wiring fusing prevention member is disposed at a position such that the shortest distance between the metal member and the detecting element wiring fusing prevention member is smaller than that between the metal member and the detecting element.

Abstract: A hydrocarbon leak detection sensor having a hydrocarbon indicator paint applied to a surface exposed to a flow in which the presence of a hydrocarbon is detected. The sensor is located at a low point in a static drain line that is connected to a main fuel line of a liquid propellant rocket engine between a main fuel valve and a fuel injector of a combustion chamber. The sensor includes a housing with a flow inlet port and a flow outlet port with an optical device opposed to a removable plug that secures a target disk with a hydrocarbon indicator paint applied to an exposed surface. A light source is used to illuminate the hydrocarbon indicator that changes color from white to red in the presence of a hydrocarbon.

Abstract: A method for inspecting a turbomachine is provided. The method includes the steps of, attaching a gimbal mount to the turbomachine, inserting a probe into the turbomachine through the gimbal mount, and adjusting a position of the probe via the gimbal mount. A removing step removes the probe from the turbomachine. An attaching step attaches a traverse actuator system to the gimbal mount. The traverse actuator system is connected to the gimbal mount through a pressure isolation system. A reinserting step is used to reinsert the probe back into the turbomachine. An inspecting step is used to inspect or test the turbomachine.

Abstract: A system for inspecting a turbomachine is provided. The system includes a pressure isolation system configured to maintain a pressure resistant seal around a probe. The pressure isolation system has a probe bearing located adjacent to a pressure seal. The probe bearing is configured to facilitate back and forth movement of the probe by reducing friction. A gimbal mount is connected to the pressure isolation system. The pressure isolation system has a valve seal located between the gimbal mount and the pressure seal. The valve seal is configured to isolate the pressure seal from the gimbal mount when the probe is not in the valve seal. The system is configured to move the probe into and out of the turbomachine.

Abstract: Exemplary methods and apparatus for testing an electrically fired item, e.g., a primer-only cartridge or all-up round (AUR) cartridge, in a variety of modes are provided. For example, a test system may provide a method of testing a primer-only cartridge and an apparatus to execute such method. Various parameters associated with operation of the electrically fired item, such as a primer or initiator, may be varied and measured using an embodiment including programmable selection of a pulse duration for firing control signals, a voltage of the firing control signals, and a number of pulses associated with the firing control signals. An inline resistance of the path of the control signals may also be adjusted. Test data including temperature, pressure, voltage, and/or current associated with operation of the electrically fired item may be measured during tests and displayed on a display device.