Abstract: A ducted fan gas turbine powerplant is mounted to aircraft structure via a single plane mounting which comprises a single peripheral array of struts which connect the core gas generator, the fan cowl and the aircraft structure. The structure which connects the struts to the core gas generator is extended downstream of the array of struts and terminates in a plain bearing. A downstream portion of the core gas generator includes a cylindrical portion which is in sliding engagement with the plain bearing, so that radial forces generated by the movement arm, the fulcrum of which coincides with the strut connection with the core gas generator are transmitting via the struts to the aircraft structure and relative axial expansion between the extension and the core gas generator is enabled.

Abstract: A surge prevention system for a fan jet engine of an aircraft serves to manifest a signal whenever pressure distortions at the engine's inlet is calculated by judiciously located total pressure probes mounted downstream of the fan on the fan struts in the fan discharge duct. The engine's bleed valve is automatically opened to prevent surge and the fuel control's speed sensor is automatically reset to compensate for any loss of thrust. Safety switches are included to render the system inoperative whenever the aircraft is in the margin of stall and the reset feature is rendered inoperative for normal bleed open operating conditions.