Abstract: Cooling for an electronic package mounted on an aircraft engine housed in a nacelle is achieved by connecting the package to the inlet of the engine and overboard of the nacelle so that substantially continuous air flow over the electronic package will ensue from either direction depending on the varying pressure gradients adjacent the points where connections are made and the conditions exists during the flight envelope. This negates the necessity of providing positive pumping devices for effectuating the flow of the cooling air.

Abstract: For improved thrust responsiveness and smooth transition of the various zones of an augmentor of an augmented jet engine powered aircraft, the time to prefill the fuel manifolds of the zones are calculated from preselected parameters so as to be on line upon light-off. The throttle lever signal is rate limited so that the preascertained manifold volume of each zone divided by the zone filling fuel flow produces a signal indicative of the time to open the normal fuel fill valve to prefill the manifold at the proper time and in the right sequence using a rate limited throttle lever signal.

Abstract: Turbine inlet temperature of a gas turbine engine is calculated from compressor discharge temperature, total and static pressures and total fuel metered to the engine by combining a sensed engine temperature with a derived fuel/air ratio and from the empirical burner can temperature rise equation solving for the turbine inlet temperature value.