The TG-100A benefited from the Anglo/American technology exchange with one of its designers, Glenn Warren, stating that one of the most important British contributions was the concept of multiple combustion cans.

[2] General Electric adopted a single shaft engine configuration, like the Rolls-Royce Dart , where the turbine drove both the compressor and the propeller reduction gearbox.

Combustion products exiting the chambers discharged through the single stage turbine before entering a rapidly converging annular exhaust terminated by a circular tail pipe.

Although the 14 stage all-axial compressor produced a decent pressure ratio (approximately 6.15:1 at design speed; 5.3:1 at Maximum Power, SLS,ISA), it was not particularly efficient.

A derivative of the T31, the General Electric TG-110A, given the military designation T41, was ordered but subsequently cancelled.