| Model 250 / T63 | |
|---|---|
_250_C20B.jpg) MTU-built Allison 250-C20B | |
| Type | Turboshaft/Turboprop |
| National origin | United States |
| Manufacturer | |
| Major applications | |
| Number built | >30,000 |
| Developed into | Rolls-Royce RR500 |
| Variants | Rolls-Royce RR300 |
TheAllison Model 250 (now known as theRolls-Royce M250 and designatedT63/T703 in US military service) is a highly successfulturboshaft engine family, originally developed by theAllison Engine Company in the early 1960s. The Model 250 has been produced by Rolls-Royce since it acquired Allison in 1995.
In 1958, theDetroit Diesel Allison division of General Motors was chosen by the US Army to develop a new light turbine engine to power a "Light Observation Aircraft" (LOA), to replace theCessna O-1A Bird Dog. At this stage, the US Army was unsure whether to have a fixed- or rotary-wing aircraft, so Allison was instructed to consider both applications. Design studies undertaken considered a wide range of possible mechanical configurations for the turboprop/turboshaft. These studies culminated in the testing of the first prototype engine, designated YT63-A-3, in April 1959.[1] In 1960, the US Army settled for a rotary wing platform. The YT63-A-3 first flew in a variant of theBell 47 helicopter in 1961. A modified version of the engine (YT63-A-5) with the exhaust pointing upwards (to avoid grass fires) soon followed. This version, rated at 250 hp, passed the Model Qualification Test in September 1962. TheHughes OH-6 design, powered by the T63, was selected for the US ArmyLOH in May 1965.
The Model 250 powers a large number of helicopters, small aircraft and even a motorcycle (MTT Turbine Superbike).[2] As a result, nearly 30,000 Model 250 engines have been produced, of which approximately 16,000 remain in service, making the Model 250 one of the highest-selling engines made by Rolls-Royce.
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Allison adopted a reverse-airflow engine configuration for the Model 250: although air enters the intake/compression system in the conventional fashion, the compressed air leaving the centrifugal compressor diffuser is ported rearwards via two transfer pipes, which go around the outside of the turbine system, before the air is turned through 180 degrees at entry to the combustor. The combustion products expand axially forward through the two-stage (single-stage on early engines) high-pressure turbine section, which is connected to the compressor via the HP shaft. The combustion products continue to expand through the two-stage power turbine, which generates shaft horsepower for the aircraft. A coaxial stub shaft connects the power turbine to a compact reduction gearbox, located inboard, between the centrifugal compressor and the exhaust/power turbine system. The exhaust stream then turns through 90 degrees to exit the engine in a radial direction through twin exhaust ducts, which form a V-shape seen in the front elevation.
An important design feature of the Model 250 engine is its modular construction, which greatly simplifies maintenance and repair activity. Also, the unique reverse-flow design provides for ease of hot section maintenance. There are four modules:
Earlier versions have seven axial compressor stages mounted on the HP shaft to supercharge a relatively low-pressure-ratio centrifugal compressor. The -C20B is typical, with an overall pressure ratio of 7.2:1, at an airflow of 3.45 lb/s (1.8 kg/s), with a power output, at the shaft, of 420 hp (310 kW).
One of the latest versions of the Model 250 is the -C40, which has only a centrifugal compressor producing a pressure ratio of 9.2:1, at an airflow of 6.1 lb/s (2.8 kg/s), and develops, at the shaft, 715 hp (533 kW).
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Data fromThe Instrumentation Design And Control of a T63-A-700 Gas Turbine Engine[7]
Related development
