Turbine driveshaft for ram air turbine

Abstract

A driveshaft for an aircraft ram air turbine includes a tubular body and a flange. The tubular body defines an axis of rotation and includes a forward portion and a frusto-conical portion located rearward of the forward portion. The flange adjoins the forward portion of the tubular body opposite the frusto-conical portion, and has a forward face and an opposite rear face. 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.

1 . 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 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.   
     
     
         2 . The driveshaft of  claim 1  and further comprising:
 a hub pilot located adjacent to the forward face of the flange, wherein a ratio of the outer diameter of the forward portion of the tubular body to the hub pilot diameter is in the range of approximately 1.359 to 1.380. 
 
     
     
         3 . The driveshaft of  claim 1 , wherein a length of the tubular body, measured in an axial direction, is approximately 22.715 cm (8.943 inches). 
     
     
         4 . The driveshaft of  claim 1 , wherein the frusto-conical portion is arranged at approximately 14° with respect to the axis. 
     
     
         5 . The driveshaft of  claim 1 , wherein the forward face of the flange is arranged at approximately 2° with respect to the axis, and wherein the rear face of the flange is arranged at approximately 9° with respect to the axis. 
     
     
         6 . The driveshaft of  claim 1  and further comprising:
 a hub pilot located adjacent to the forward face of the flange, wherein the hub pilot has a diameter of approximately 18.001 cm (7.090 inches), wherein a length of the tubular body, measured in an axial direction, is approximately 22.715 cm (8.943 inches), wherein the frusto-conical portion is arranged at approximately 14° with respect to the axis, wherein the forward face of the flange is arranged at approximately 2° with respect to the axis, and wherein the rear face of the flange is arranged at approximately 9° with respect to the axis. 
 
     
     
         7 . 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.   
     
     
         8 . The driveshaft of  claim 7 , wherein the forward face of the flange is arranged at approximately 2° with respect to the axis. 
     
     
         9 . The driveshaft of  claim 7 , wherein an outer diameter of the forward portion of the tubular body is approximately 7.117 cm (2.802 inches) and an inner diameter of the forward portion of the tubular body is approximately 4.994 cm (1.966 inches). 
     
     
         10 . The driveshaft of  claim 7  and further comprising:
 a hub pilot located adjacent to the forward face of the flange, wherein the hub pilot has a diameter of approximately 18.001 cm (7.090 inches). 
 
     
     
         11 . The driveshaft of  claim 7 , wherein a length of the tubular body, measured in an axial direction, is approximately 22.715 cm (8.943 inches). 
     
     
         12 . The driveshaft of  claim 7 , wherein the frusto-conical portion is arranged at approximately 14° with respect to the axis. 
     
     
         13 . The driveshaft of  claim 7  and further comprising:
 a hub pilot located adjacent to the forward face of the flange, wherein the hub pilot has a diameter of approximately 18.001 cm (7.090 inches), wherein a length of the tubular body, measured in an axial direction, is approximately 22.715 cm (8.943 inches), wherein the frusto-conical portion is arranged at approximately 14° with respect to the axis, wherein the forward face of the flange is arranged at approximately 2° with respect to the axis, wherein an outer diameter of the forward portion of the tubular body is approximately 7.117 cm (2.802 inches), and wherein an inner diameter of the forward portion of the tubular body is approximately 4.994 cm (1.966 inches). 
 
     
     
         14 . 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. 
   
     
     
         15 . 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.