Abstract: A smart indicator for an engine, and applications thereof. In an embodiment, the indicator includes a processing module and a display. The processing module receives a plurality of input parameter signals from various engine sensors. The input parameter signals are transformed by the processing module into values that can be displayed on the display. The display depicts at least the most relevant transformed value for controlling the engine and how this transformed value relates to an associated limit value for the engine such as, for example, a temperature limit value, a rotational speed limit value, or a torque limit value. In one embodiment, the input parameter signals are transformed by converting the input parameter signals to a plurality of digital values, subtracting an appropriate limit value for the engine from each digital value, dividing each resulting difference value by the appropriate limit value for the engine, and multiplying the resulting quotient value by a scaling value.

Abstract: Smart instrumentation and monitoring provide primary engine instrumentation for an aircraft. The instrumentation generates real time engine power available data for the entire power regime and flight envelope of the aircraft while engine monitoring functions track, record and output performance usage data, trend data, and flight profile data. Generated data is provided to an aircraft flight manual and mission management module that automatically calculates and generates aircraft operational and performance data needed to safely operate the aircraft. The generated data is selectively displayed on flat-panel cockpit displays and/or electronic kneeboard displays in a graphical format that enhances aircrew situational awareness and permits aircrew members to operate the aircraft with its intended margin of safety.

Abstract: An aircraft engine diagnostic apparatus is described. The diagnostic apparatus senses engine performance related parameters refers the data to a standard atmosphere condition and plots values relating to the functions of each engine performance related parameter with respect to other engine performance related parameters. The apparatus compares these actual engine operating parameter values with standard baselines for normal engines and calculates the deviation between the actual curve and the standard curve as referred engine diagnostic data (REDD), an indicator of engine performance condition. The apparatus also senses the direction of deviation of the changing engine parameters from the standard baseline as an additional diagnostic indicator of the probable cause of engine deterioration. The deviation values are then instantaneously provided for immediate diagnosis of engine condition. A method of using the apparatus to diagnose engine problems is also described.

Abstract: An aircraft brake tester includes pressure transducers to detect pressure levels in each of a plurality of hydraulic lines connected to each of a plurality of aircraft disc brake cylinders, respectively. Each aircraft disc brake includes a set of cylinders, each connected to one of a set of hydraulic lines. Each respective hydraulic line exerts a hydraulic pressure to a respective cylinder engaged with the hydraulic line potentially resulting in different cylinders on the same aircraft brake receiving different hydraulic pressures. The pressure transducers convert the detected pressure levels into analog signals and output the analog signals to a processor. The processor digitizes, references and calibrates the analog signals into actual pressure values and simultaneously displays the actual pressure values.

Abstract: A turbine fan speed monitor for use with an aircraft engine which monitors actual fan speeds for each of a plurality of aircraft engines. The apparatus also input instantaneous values of total air temperature, pressure altitude, altitude rate, and the position of the wheels. The fan speed monitor calculates an overspeed limit value for the turbine fan as a function of each of the total air temperature, pressure altitude, altitude rate, and position of the wheels data and indicates when the actual fan speed exceeds the overspeed limit value for each monitored engine. The monitor warns the pilot of calculated overspeed conditions that he can control by throttle manipulation. Engine life is related to the calculated speeds at take-off, climb and cruise. The monitor keeps a record of the time and duration of these instances when the actual fan speed exceeds the overspeed limit for any engine.

Abstract: An indicator monitor which performs a plurality of functions. Both engine exhaust gas temperature and engine rpm are monitored. Based on the engine rpm, it is determined whether the engine is in starting or operating condition. Different parameters and different values are used based on this indication. A plurality of different functions including parameters indicative of temperature in rpm can be monitored by this one meter with a single display and which has electronics that can be housed in an area smaller than the display face.

Abstract: An electrical input signal representative of the existing operating state of a rotating bladed disk or other rotating member is classified into one of a plurality of predetermined operating states and a sequence detector is employed for detecting the occurrence of one of a plurality of possible predetermined sequences of such operating states. Predetermined fixed damage coefficients are then correlated with respectively corresponding detected predetermined sequences of operating states and accumulated with other similarly selected damage coefficients so as to provide a cumulative indication of low cycle fatigue damage done to the rotating member over its past history of experienced operating state sequences.

Abstract: A method and apparatus for sensing the velocity of a fluid flow, especially within the boundary layer of a fluid flow path through a compressor. A reference flow under constant pressure is established through an orifice dividing two plenum chambers, and directed through a flow sensing opening in a probe positioned in the flow to be sensed. The flow sensing opening is slightly larger than the orifice. A relative pressure indicator connected to the two plenum chambers indicates the velocity of the sensed fluid flow. The flow sensing opening is arranged so that the normal reference flow of fluid therethrough is in the same direction as the normally expected flow direction of the flow to be sensed.