Multi-shaft gas turbine engine
A gas turbine engine is disclosed with a first spool having a first turbine connected to a first compressor through a first rotatable shaft; a second spool having a second turbine connected to a second compressor through a second rotatable shaft; and a gearbox having a power input port coupled to each of the first and second shafts and a power output port connected to a third shaft, wherein the rotational speed of the third shaft is lower than the rotational speed of each of the first and second shafts.
1. A gas turbine engine comprising:
a power device that includes a pusher propeller;
a first gearbox configured to provide power to the power device, the first gearbox having a first input and a first output;
a first spool including a first rotatable shaft, a compressor, and a high-pressure turbine coupled to the compressor through the first rotatable shaft and coupled to the first gearbox through the first rotatable shaft to provide power to the first gearbox;
a second spool including a second rotatable shaft and a low-pressure turbine coupled to the second rotatable shaft and configured to provide power to the power device;
a third rotatable shaft;
a second gearbox having a second input, a third input, and a second output, the first rotatable shaft coupled to the first input, the second rotatable shaft coupled to the second input, and the third rotatable shaft coupled to the first output and to the third input to transmit power from the first gearbox to the second gearbox; and
an output shaft coupled directly to the second output and to the power device to transmit power directly from the second gearbox to the power device,
wherein the first spool and the second spool are arranged circumferentially around a core-flow of the gas turbine engine, the core-flow is directed from upstream to downstream in a sequential order along an axial direction through an inlet, the compressor, a combustor, the high-pressure turbine, the low-pressure turbine, and the pusher propeller,
wherein the power device and the second gearbox are located downstream of the low-pressure turbine in the axial direction, the first gearbox is located downstream of the combustor and upstream of the second gearbox in the axial direction, and
wherein the first rotatable shaft, the second rotatable shaft, the third rotatable shaft, and the output shaft are configured to rotate at different speeds.
2. The gas turbine engine of claim 1 , wherein the first gearbox and the second gearbox include one of hydraulic means, electric means, one or more clutches, and/or transmission means to control variable gear ratios.