Aircraft propeller assembly with blade pitch reset for ground idle
AssigneeHartzell Propeller Inc.
InventorsLoy D. Pace, Donald C. Stackhouse, Earl W. Jones, Dennis S. Zimpfer
Life of this patent
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Abstract
An aircraft propeller has adjustable pitch blades which are reset from a low pitch in-flight idle position to a lower pitch ground idle position by a beta feedback and reset mechanism. The reset mechanism includes a set of cam elements supported for movement in response to rotation of the blades and positioned to engage a follower plate adjustably mounted on the beta feedback control rods.
Claims18
An aircraft propeller assembly comprising a propeller hub adapted to be driven by a turbine engine on an aircraft, said hub supporting a plurality of angularly disposed and radially projecting adjustable pitch propeller blades, pitch changing means including a hydraulic fluid cylinder and piston for changing the pitch of said blades between a feather position and a reverse pitch position through a low pitch in-flight idle position and a lower pitch on-ground idle position in response to actuation of said piston by hydraulic fluid, feedback control means including a valve for controlling the flow of the fluid to said piston, a plurality of feedback control rods extending parallel to the propeller axis of rotation and having rearward end portions connected to actuate said valve, first positive actuated means for moving said control rods and closing said valve in response to axial movement of said piston and rotation of said blades to said in-flight idle position, second positive actuated means for moving said control rods and closing said valve in response to further axial movement of said piston and rotation of said blades to said on-ground idle position, and means for precisely adjusting said first and second positive actuated means for precisely selecting the pitch of said blades at said in-flight idle position and said on-ground idle position.
An aircraft propeller assembly comprising a propeller hub adapted to be driven by a turbine engine on an aircraft, said hub supporting a plurality of angularly disposed and radially projecting adjustable pitch propeller blades, pitch changing means including a hydraulic fluid cylinder and piston for changing the pitch of said blades between a feather position and a reverse pitch position through a low pitch in-flight idle position and a lower pitch on-ground idle position in response to actuation of said piston y hydraulic fluid, feedback control means including a valve for controlling the flow of the fluid to said piston, a plurality of axially extending feedback control rods connected to actuate said valve, means for moving said rods axially in response to axial movement of said piston to said on-ground idle position, reset means including cam members supported for rotation in response to predetermined rotation of corresponding said blades, and cam follower means mounted on said control rods and disposed for engagement by said cam members for moving said rods and closing said valve in response to rotation of said blades to said in-flight idle position to provide for precisely resetting the pitch of said blades to said on-ground idle position by said piston after landing of the aircraft.
An aircraft propeller assembly comprising a propeller hub adapted to be driven by a turbine engine on an aircraft, said hub supporting a plurality of angularly disposed and radially projecting adjustable pitch propeller blades, pitch changing means including a hydraulic fluid cylinder and piston for changing the pitch of said blades between a feather position and a reverse pitch position through a low pitch in-flight idle position and a lower pitch on-ground idle position in response to actuation of said piston by hydraulic fluid, each said blade including an outwardly projecting counterweight element, feedback control means including a valve for controlling the flow of the fluid to said piston, a plurality of axially extending feedback control rods connected to actuate said valve, means for moving said rods axially in response to axial movement of said piston to said on-ground idle position, reset means including cam members mounted on said blades for corresponding rotation with said blades, and an annular cam follower mounted on said control rods and surrounding said piston for engagement by said cam members for moving said rods and closing said valve in response to rotation of said blades to said in-flight idle position to provide for precisely resetting the pitch of said blades to said on-ground idle position by said piston after landing of the aircraft.
Dependencies are inferred from the claim text.