| 摘要 |
A jet aircraft engine having an improved turbine section with curved intake manifolds (102) to direct combustion gasses from the engine's combustion chamber (80) into the turbine housing (104) on a chordal flow path through the turbine generally perpendicular to the turbine rotor's axis of rotation. The turbine rotor has a number of radially extending turbine blades (116) for transmitting energy from the combustion gasses to shaft work to drive the engine's fan and compressor. Exhaust manifolds (126) can also be provided, directing the flow of exhaust gasses from the turbine to the engine's intake, and having noise and emissions control capability. |
