| 摘要 |
A mixed flow, high bypass, gas turbofan engine that is small and compact, and that develops a thrust in the range of approximately 200-300 pounds. The engine has an axial length of approximately 18 inches, an air inlet of approximately 10 inches in diameter, and an exhaust nozzle of approximately 6 inches in diameter. To reduce engine length high pressure compressor diameter, a high pressure compressor is positioned in a location that is displaced from and is preferably parallel to the engine axis (i.e., centerline), a burner (i.e., combustion chamber) is similarly positioned on the other side of the engine axis, only one turbine is used, and a unique flow path also is used. In addition, a heat exchanger of the regenerative type which includes a plurality of pipe diffusers is used, and it is positioned in the hot exhaust flow of the single turbine to pre-heat the compressor air prior to entry into the burner. Further, a gear shift may be used with the compressor to give better part-power performance. The small size, the thrust capability, and the good fuel consumption during part-power operation, make this engine ideal for use in air-launched cruise missiles.
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