Multi-spool geared turbofan arrangement with integrated starter/generator
A geared turbofan engine with at least one compression stage and at least one turbine stage on a high speed shaft, the high speed shaft coupled through a speed reduction gear box to a low speed shaft with a fan and a starter/generator. The low speed shaft is collinear with the high speed shaft but does not rotate within the high speed shaft. The speed reduction gear box is positioned between and mechanically couples the high speed shaft and the low speed shaft, which allows the fan and the integrated starter/generator on the low speed shaft to operate at a lower speed than the high speed shaft.
1. A gas turbine engine comprising:
a high speed shaft, the high speed shaft including a compressor and a turbine;
a combustor between the compressor and the turbine;
a low speed shaft, the low speed shaft including a fan and an integrated starter/generator; and
a speed reduction gear box connecting the low speed shaft to the high speed shaft, wherein air flows into the fan and exits as a bypass air flow and a core flow, the core flow entering the compressor, then flows to the combustor to burn with a fuel, and then flows through the turbine, the turbine driving the low speed shaft through the speed reduction gear box,
the high speed shaft being supported by a first bearing located between the speed reduction gear box and the compressor and a second bearing located aft of the turbine, and
the low speed shaft being supported by a third bearing located between the fan and the integrated starter/generator and a fourth bearing located between the integrated starter/generator and the speed reduction gear box.
2. The gas turbine engine of claim 1 , wherein the low speed shaft is collinear with the high speed shaft but does not rotate within the high speed shaft.
3. The gas turbine engine of claim 1 , wherein the speed reduction gear box is located between the integrated starter/generator and the compressor.
4. A multiple spool geared turbofan gas turbine engine comprising:
a high speed shaft, the high speed shaft including a first compressor, a second compressor downstream of the first compressor, a first turbine, and a second turbine located downstream of the first turbine;
a combustor located between the second compressor and the first turbine;
a low speed shaft, the low speed shaft including a fan and an integrated starter/generator located downstream of the fan; and
a speed reduction gear box mechanically coupling the high speed shaft and the low speed shaft, the first turbine and the second turbine driving the high speed shaft and driving the low speed shaft through the speed reduction gear box,
the low speed shaft being supported by a first bearing located between the fan and the integrated starter/generator and a second bearing located between the integrated starter/generator and the speed reduction gearbox, and
the low speed shaft being collinear with the high speed shaft but not rotating within the high speed shaft.
5. The multiple spool geared turbofan gas turbine engine of claim 4 , wherein the speed reduction gear box is located between the integrated starter/generator and the first compressor.
6. The multiple spool geared turbofan gas turbine engine of claim 4 , wherein:
the first compressor is a low pressure compressor; and
the second compressor is a high pressure compressor.
7. The multiple spool geared turbofan gas turbine engine of claim 4 , wherein:
the first turbine is a high pressure turbine; and
the second turbine is a low pressure turbine.
8. The multiple spool geared turbofan gas turbine engine of claim 4 , wherein the high speed shaft is supported by a third bearing located between the speed reduction gear box and the first compressor and a fourth bearing located aft of the second turbine.