Power turbine shaft for decoupled gas generator
AssigneeRtx Corporation
InventorJon Erik Sobanski
Life of this patent
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Abstract
A propulsion system for an aircraft includes a propulsor section that includes a fan with a plurality of fan blades that are rotatable about a fan axis, a core engine that is configured to generate a gas flow, a power turbine where the gas flow from the core engine is expanded to generate shaft power, and a power turbine shaft that is coupled between the power turbine and the propulsor section. The power turbine shaft is of an axial length between a first end portion and a second end portion along the fan axis that is greater than half a distance between a leading edge of the fan blades and a mechanical coupling of the power turbine shaft to the power turbine, and includes an outer diameter that increases in a direction away from each of the first end portion and the second end portion.
Claims18
A propulsion system for an aircraft comprising:
- a propulsor section including a fan with a plurality of fan blades rotatable about a fan axis;
- a core engine configured to generate a gas flow;
- a power turbine mechanically uncoupled from the core engine and rotatable independent of the core engine where the gas flow from the core engine is expanded to generate shaft power;
- and
- a power turbine shaft disposed outside of the core engine and coupled between the power turbine and the propulsor section, wherein the power turbine shaft is of an axial length between a first end portion and a second end portion along the fan axis that is greater than half a distance between a leading edge of the fan blades and a mechanical coupling of the power turbine shaft to the power turbine, and includes an outer diameter that increases in a direction away from each of the first end portion and the second end portion, and wherein the power turbine shaft includes a radial wall with a thickness that varies between the first end portion and the second end portion such that a cross-sectional area of the radial wall transverse to a longitudinal length of the power turbine shaft is uniform between the first end portion and the second end portion.
A propulsion system for an aircraft comprising:
- a fan section including a fan drive gear system driving a fan shaft supporting a plurality of fan blades about a fan axis;
- a core engine defining a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with fuel, and ignited to generate a gas flow that is expanded through a turbine section;
- a power turbine mechanically uncoupled from the core engine and rotatable independent of the core engine where the gas flow from the core engine is expanded to generate shaft power;
- and
- a power turbine shaft disposed outside of any portion of the core engine for transmitting torque from the power turbine to the fan drive gear system, wherein the power turbine shaft is hollow and includes an outer diameter that increases in a direction away from each of a first end portion and a second end portion and is of an axial length between the first end portion and the second end portion along the fan axis that is greater than half a distance between a leading edge of the plurality of fan blades and a mechanical coupling to the power turbine, and wherein the power turbine shaft includes a radial wall thickness that varies between the first end portion and the second end portion such that a cross-sectional area of the radial wall transverse to a longitudinal length of the power turbine shaft is uniform between the first end portion and the second end portion.
A method of operating a gas turbine engine, the method comprising:
- generating a gas flow with a core engine that is disposed about a core engine axis that is inclined relative to a fan axis;
- generating shaft power to drive the fan having a plurality of fan blades with a power turbine receiving the gas flow from the core engine;
- and
- transmitting shaft power to a fan disposed about the fan axis through a power turbine shaft with an axial length along the fan axis that is greater than half a distance between a leading edge of the plurality of fan blades and a mechanical coupling to the power turbine, and that includes a radial wall thickness that varies between a first end portion and a second end portion such that a cross-sectional area of the radial wall transverse to a longitudinal length of the power turbine shaft is uniform between the first end portion and the second end portion.
Dependencies are inferred from the claim text.