公开(公告)号：AU5465990A

公开(公告)日：1990-11-22

申请号：AU5465990

申请日：1990-05-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SWEET DAVID H ,  GREENBERG CHARLES E ,  LAPPOS NICHOLAS D ,  WALSH DAVID M ,  MEISNER RICHARD P

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  B64D35/00 ,  B64C27/06

Abstract: The speed 54,56 of the free turbine 40 of a helicopter engine 22 is compared 134,138 with the speed 142,140 of the helicopter rotor 10 to indicate 106,108 a specific magnitude of autorotation and the deceleration 150 of the rotor above either one of two threshold magnitudes 220,222 (dependent on the magnitude of autorotation) is utilized 81,68,69 to increase fuel flow 72 to the engine according to a specific schedule 160,162, determined by the type of autorotation, in anticipation of rotor speed droop which would otherwise occur during recovery from the autorotation maneuver.

公开(公告)号：CA2015588A1

公开(公告)日：1990-11-19

申请号：CA2015588

申请日：1990-04-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALSH DAVID M ,  GREENBERG CHARLES E ,  LAPPOS NICHOLAS D ,  SWEET DAVID H

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  G05D1/00

Abstract: -22- A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor larding (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down. (120, 103-105).

公开(公告)号：ES2018773A4

公开(公告)日：1991-05-16

申请号：ES90630108

申请日：1990-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALSH DAVID M ,  LAPPOS NICHOLAS D ,  GREENBERG CHARLES E ,  SWEET DAVID H

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08

公开(公告)号：ES2019059T3

公开(公告)日：1995-12-16

申请号：ES90630107

申请日：1990-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SWEET DAVID H ,  LAPPOS NICHOLAS D ,  MEISNER RICHARD P ,  GREENBERG CHARLES E ,  WALSH DAVID M

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  G05D1/00

Abstract: The speed 54,56 of the free turbine 40 of a helicopter engine 22 is compared 134,138 with the speed 142,140 of the helicopter rotor 10 to indicate 106,108 a specific magnitude of autorotation and the deceleration 150 of the rotor above either one of two threshold magnitudes 220,222 (dependent on the magnitude of autorotation) is utilized 81,68,69 to increase fuel flow 72 to the engine according to a specific schedule 160,162, determined by the type of autorotation, in anticipation of rotor speed droop which would otherwise occur during recovery from the autorotation maneuver.

公开(公告)号：ES2019059A4

公开(公告)日：1991-06-01

申请号：ES90630107

申请日：1990-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SWEET DAVID H ,  LAPPOS NICHOLAS D ,  MEISNER RICHARD P ,  GREENBERG CHARLES E ,  WALSH DAVID M

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08

公开(公告)号：AU5466090A

公开(公告)日：1990-11-22

申请号：AU5466090

申请日：1990-05-03

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALSH DAVID M ,  GREENBERG CHARLES E ,  LAPPOS NICHOLAS D ,  SWEET DAVID H

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  B64D31/06

Abstract: A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down (120, 103-105).

公开(公告)号：DE69027714D1

公开(公告)日：1996-08-14

申请号：DE69027714

申请日：1990-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALSH DAVID M ,  LAPPOS NICHOLAS D ,  GREENBERG CHARLES E ,  SWEET DAVID H

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  G05D1/00

Abstract: A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down (120, 103-105).

公开(公告)号：DE69022880D1

公开(公告)日：1995-11-16

申请号：DE69022880

申请日：1990-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SWEET DAVID H ,  LAPPOS NICHOLAS D ,  MEISNER RICHARD P ,  GREENBERG CHARLES E ,  WALSH DAVID M

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  G05D1/00

Abstract: The speed 54,56 of the free turbine 40 of a helicopter engine 22 is compared 134,138 with the speed 142,140 of the helicopter rotor 10 to indicate 106,108 a specific magnitude of autorotation and the deceleration 150 of the rotor above either one of two threshold magnitudes 220,222 (dependent on the magnitude of autorotation) is utilized 81,68,69 to increase fuel flow 72 to the engine according to a specific schedule 160,162, determined by the type of autorotation, in anticipation of rotor speed droop which would otherwise occur during recovery from the autorotation maneuver.

公开(公告)号：DE69027714T2

公开(公告)日：1996-11-07

申请号：DE69027714

申请日：1990-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALSH DAVID M ,  LAPPOS NICHOLAS D ,  GREENBERG CHARLES E ,  SWEET DAVID H

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  G05D1/00

Abstract: A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down (120, 103-105).

公开(公告)号：ES2018773T3

公开(公告)日：1996-10-01

申请号：ES90630108

申请日：1990-05-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALSH DAVID M ,  LAPPOS NICHOLAS D ,  GREENBERG CHARLES E ,  SWEET DAVID H

IPC: B64D31/00 ,  F02C9/28 ,  G05D1/08 ,  G05D1/00

Abstract: A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down (120, 103-105).