Engine, Fairchild Ranger XT-R-2 TP Turboprop Engine

Type: Turboprop, 4 units

Power Rating: 7,345 kW (9,850 ehp)

Compressor: 12-stage axial

Combustor: Six through flow can-type

Turbine: 2-axial stages driving compressor, 2-axial stages driving propeller

Weight: 2,815 kg (6,200 lb)

In 1946, the U.S. Navy cancelled its contract for the 24-cylinder, 1,119 kW (1,500 shp) XH-1850 engine under development by the Ranger Aircraft Engine Division of Fairchild Engine and Airplane Corporation. Remaining funds were assigned to study a turboprop engine, with wide variations in configurations. Included were a simple gas turbine; a gas turbine using a regenerative cycle; use of a reheat cycle; and a compound arrangement with one turbine driving the compressor and the other the propeller. Designs were also to be in the context of aircraft missions appropriate for such turbine engines.

The proposed design utilized four power units arranged around a central drive shaft, with each unit incorporating 12 axial-flow compressor stages and 4 axial-flow turbine stages. This artifact is one unit, used for compressor tests. The project was canceled in 1948 due to a Government decision to restrict engineering and design contract awards and funds to a limited number of major engine manufacturers.