THIS discussion of the problems encountered in designing the installation for the TG-180 in the P-84 Thunderjet is presented in the hope that other engineers designing installations for other turbojets may benefit from Republic's experiences.
Problems discussed include provision for quick engine replacement; reduction of losses in the long inlet duct; development of a strong, tight joint for the tail pipe and engine; choice of thermal protection for the fuselage; provision for adjusting tail pipe area; and design of the fuel system. Several suggestions are made for improving the design of the engine from the installation standpoint.
