公开(公告)号：US10807701B2

公开(公告)日：2020-10-20

申请号：US16271276

申请日：2019-02-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Paul W. Futa, Jr. ,  Hannah Amor ,  Gary A. Valencourt ,  Christopher Douglas Eick ,  Donald Striker ,  Kevin Baker ,  Jonathan Seeley

IPC: B64C11/38 ,  B64C11/44 ,  F01D7/00 ,  B64C27/64 ,  B64C11/40 ,  B64C11/30 ,  B64C11/42

Abstract: A propeller pitch control system for a turboprop engine of an aircraft includes a negative torque sensor, a full feather control valve assembly, and a feather valve assembly. The feather valve assembly is responsive to fluid pressures from the negative torque sensor and the control valve assembly to move between a plurality of positions. An engine control unit or a manual user interface can also be used to control the position of the feather.

公开(公告)号：US20200255123A1

公开(公告)日：2020-08-13

申请号：US16271276

申请日：2019-02-08

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Paul W. Futa, Jr. ,  Hannah Amor ,  Gary A. Valencourt ,  Christopher Douglas Eick ,  Donald Striker ,  Kevin Baker ,  Jonathan Seeley

IPC: B64C11/38 ,  F01D7/00 ,  B64C11/44

Abstract: A propeller pitch control system for a turboprop engine of an aircraft includes a negative torque sensor, a full feather control valve assembly, and a feather valve assembly. The feather valve assembly is responsive to fluid pressures from the negative torque sensor and the control valve assembly to move between a plurality of positions. An engine control unit or a manual user interface can also be used to control the position of the feather.

公开(公告)号：US11066150B2

公开(公告)日：2021-07-20

申请号：US16227175

申请日：2018-12-20

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Paul W. Futa, Jr. ,  Sammuel Tillich ,  Steven Alan Lewis ,  Christopher Douglas Eick ,  Donald Striker ,  Michael Albert McPherson

IPC: B64C11/38 ,  B64C11/44 ,  F02D29/02 ,  B64C11/40 ,  F02B61/04

Abstract: A propeller oil control system for a turboprop engine of an aircraft includes an engine control unit and a propeller oil controller. The engine control unit is operable to determine a flight phase of the aircraft and is configured to supply control commands. The propeller oil controller is coupled to receive a supply of oil and to discharge the oil at a discharge oil pressure. The propeller oil controller includes an electrohydraulic servo valve that receives the control commands moves to a plurality of positions between a first position and a mid-position, and a plurality of positions between the mid-position and a second position. The engine control unit only commands the electrohydraulic servo valve to move out of the first position when the engine control unit determines the aircraft is conducting a take-off roll or the aircraft is in flight.

公开(公告)号：US10850831B2

公开(公告)日：2020-12-01

申请号：US16230201

申请日：2018-12-21

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Paul W. Futa, Jr. ,  Sammuel Tillich ,  Steven Alan Lewis ,  Christopher Douglas Eick ,  Donald Striker ,  Michael Albert McPherson

IPC: B64C11/40 ,  B64C11/30 ,  B64C11/38

Abstract: A propeller pitch control system for a turboprop engine of an aircraft includes an engine control unit and a pitch control unit. The engine control unit is operable to determine a phase of flight of the aircraft and is configured to supply control commands. The pitch control unit is coupled to receive the control commands from the engine control unit and includes a housing, a beta piston, a position sensor, a beta tube, and an electrohydraulic valve. The engine control unit only commands the electrohydraulic valve to move the beta piston from the fully retracted position when the engine control unit determines the aircraft is conducting pre-takeoff roll taxiing operations or is conducting post landing touchdown operations.