| 摘要 |
The subject engine includes two turbocompressor units, the first a relatively low pressure device having a rotor with mechanically connected turbine wheel and compressor impeller elements. The second unit has separated turbine wheel and compressor impeller pieces with power being transmitted from the turbine wheel to the compressor impeller through a differential gear assembly. In operation, the compressor of the first unit supplies compressed air to the second unit which increases the pressure of the air and supplies it to a combustor where fuel is added and burned to generate high temperature high pressure gases. These gases are first applied to the turbine of the second unit then to the turbine of the first unit after which they may be passed through a recuperator to heat the compressed air from the compressor of the second unit before it is introduced into the combustor. The differential gear assembly has an output shaft leading to a torque converter or other power transferring mechanism. Such assembly also has a power takeoff gear train for supplying power to an accessory drive. A starter motor is also selectively connected with the differential to initiate rotation of the compressor and turbine of the second turbocompressor unit in the engine starting operation. A clutch controlled power transfer path is provided to connect the output shaft and predetermined parts of the differential during the starting and braking steps of operation. To enhance the efficiency of the engine one or both compressors may be equipped with rotary inlet guide vanes while each turbine may be provided with variable nozzles.
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