Turbine driveshaft for ram air turbine

A driveshaft for an aircraft ram air turbine, the driveshaft comprising:

• a tubular body that defines an axis of rotation and that includes a forward portion and a frusto-conical portion located rearward of the forward portion;
• and
• a flange adjoining the forward portion of the tubular body opposite the frusto-conical portion, the flange having a forward face and an opposite rear face,
• wherein the frusto-conical portion is arranged at approximately 14° with respect to the axis, and
• wherein the rear face of the flange is arranged at approximately 9° with respect to the axis.

A ram air turbine assembly for an aircraft, the assembly comprising:

• a turbine subassembly having a rotatable hub;
• a gearbox positioned adjacent to the hub;
• a strut positioned adjacent to the gearbox, wherein the strut supports the gearbox;
• a power conversion device;
• and
• a drivetrain operably connected between the turbine subassembly and the power conversion device, the drivetrain having a turbine driveshaft attached to the hub and located at least partially within the gearbox, the turbine driveshaft including:
• a tubular body that defines an axis of rotation and that includes a forward portion and a frusto-conical portion located rearward of the forward portion;
• and
• a flange adjoining the forward portion of the tubular body opposite the frusto-conical portion, the flange having a forward face and an opposite rear face,
• wherein a ratio of an outer diameter of the forward portion of the tubular body to an inner diameter of the forward portion of the tubular body is in a range of approximately 1.423 to 1.425.

A method of installing a driveshaft in an aircraft ram air turbine, the method comprising:

• providing a driveshaft having a tubular body that includes a forward portion and a frusto-conical portion located rearward of the forward portion, and a flange adjoining the forward portion of the tubular body opposite the frusto-conical portion, the flange having a forward face and an opposite rear face, wherein a ratio of an outer diameter of the forward portion of the tubular body to an inner diameter of the forward portion of the tubular body is in a range of approximately 1.423 to 1.425;
• positioning the driveshaft at least partially within a gearbox;
• and
• operatively engaging the driveshaft in a drivetrain that extends between a turbine and a power conversion device.