초록

A gas turbine aircraft engine with power variability is provided. The gas turbine aircraft engine comprises a compressor and a turbine mounted on a common shaft, and, a continuously variable transmission coupled to the shaft for transmitting power to a propulsion load.

대표청구항 ▼

1. A gas turbine aircraft engine with power variability comprising: an engine case;a single spool comprising a compressor and a turbine mounted on a common shaft inside the engine case;a propulsion load selected from a group comprising of: a fan and a propeller; anda continuously variable transmissi

1. A gas turbine aircraft engine with power variability comprising: an engine case;a single spool comprising a compressor and a turbine mounted on a common shaft inside the engine case;a propulsion load selected from a group comprising of: a fan and a propeller; anda continuously variable transmission provided between the single spool and the propulsion load, the continuously variable transmission being coupled to the shaft within the engine case for transmitting power to the propulsion load, the continuously variable transmission being operable to vary the speed of the propulsion load relative to the speed of the single spool, the continuously variable transmission having a housing structurally mounted to the engine case, the housing having a mounting interface for a bearing support supporting the propulsion load. 2. The gas turbine aircraft engine as defined in claim 1, wherein the continuously variable transmission is of toroidal type. 3. The gas turbine aircraft engine as defined in claim 1, further comprising a gear box coupled to the shaft for transmitting power from the shaft to the propulsion load. 4. The gas turbine aircraft engine as defined in claim 3, wherein the continuously variable transmission is disposed adjacent to an input of the gearbox. 5. The gas turbine aircraft engine as defined in claim 3, wherein the continuously variable transmission is disposed adjacent to an output of the gearbox. 6. The gas turbine aircraft engine defined in claim 1, wherein the engine is a turbofan or a turbopropeller. 7. A single spool gas turbine aircraft engine comprising: a single spool including means for pressurizing air for combustion, and means for extracting energy from combustion gases, the means for pressurizing air and the means for extracting energy being coupled for synchronous rotation;a fan or a propeller driven by said means for extracting energy; andcontinuously variable transmission means coupling the single spool to the fan or the propeller, said continuously variable transmission means being synchronize to a throttle of the engine via an engine electronic control system. 8. The gas turbine aircraft engine as defined in claim 7, wherein the continuously variable transmission means is of toroidal type. 9. The gas turbine aircraft engine as defined in claim 7, further comprising a speed reduction means between the means for extracting energy and the fan or the propeller. 10. The gas turbine aircraft engine as defined in claim 7, further comprising a means for coupling the fan or the propeller to the means for extracting energy. 11. A method for varying the rotational speed of a fan or propeller on a single spool gas turbine aircraft engine comprising the steps of: a) providing the engine with a single spool comprising a compressor and a turbine mounted on a common shaft and rotating therewith at a common rotational speed;b) transmitting rotational movement from the turbine to the fan or the propeller; andc) continuously varying a rotational speed of the fan or the propeller in relation to the common rotational speed of the turbine and compressor and as a function of the engine throttle. 12. The method as defined in claim 11, further comprises stepping down the rotational speed of the fan or the propeller in relation to the common rotation speed of the turbine and compressor.