| 摘要 |
A gas turbine engine is provided and comprises a housing having an air inlet and an exhaust outlet with a fluid passageway formed through the housing for connecting the inlet to the outlet. A low pressure spool assembly comprises a first shaft rotatably mounted within the housing and has at least one low pressure compressor stage secured to one end of the first shaft and a low pressure turbine stage secured to the other end of the first shaft. The low pressure compressor stage is disposed within the fluid passageway immediately downstream from the housing inlet while, conversely, the low pressure turbine stage is disposed within the fluid passageway and immediately upstream from the outlet. An intermediate pressure spool assembly is also provided and comprises a second shaft rotatably mounted within the housing and coaxial with the first shaft, an intermediate pressure compressor stage secured to one end of the second shaft and an intermediate pressure turbine stage secured to the other end of the second shaft. The intermediate pressure compressor stage is disposed within the fluid passageway immediately downstream from the low pressure compressor stage while the intermediate pressure turbine stage is positioned immediately upstream from the low pressure turbine stage. A high pressure spool assembly is further provided and comprises a third shaft rotatably mounted within the housing and having a high pressure compressor stage secured to one end of the shaft and a high pressure turbine stage secured to the other end of the third shaft. The high pressure compressor stage is disposed within the fluid passageway immediately downstream from the intermediate pressure compressor stage while the high pressure turbine stage is disposed immediately upstream from the intermediate pressure turbine stage. The high pressure stage further includes a fuel combustor and, in addition, the axis of the third or high pressure shaft is offset from and preferably perpendicular to the axes of the first and second shafts.
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