公开(公告)号：CA1202099A

公开(公告)日：1986-03-18

申请号：CA427362

申请日：1983-05-04

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZAGRANSKI RAYMOND D ,  HOWLETT JAMES J ,  LAPPOS NICHOLAS D

IPC: F02C9/28 ,  B64C27/00 ,  B64D31/00 ,  B64D31/06 ,  B64D37/00 ,  F02C9/26 ,  F02C9/46 ,  F02C9/42 ,  G05D1/00

Abstract: Super Contingency Aircraft Engine Control A fuel control (23) for an aircraft engine (10) employs super contingency logic (76) in response to low rotor speed of a helicopter (130) engine failure (131) or entry into an avoid region of a flight regime following engine failure (133) to alter (161, 166-169) limits on the gas generator (30) of a free turbine gas engine (10), whereby following engine failure or in periods of extreme power need, risk of stressing an engine to its failure point is undertaken in favor of acquiring enough power to avoid a certain crash.

公开(公告)号：DE3377375D1

公开(公告)日：1988-08-18

申请号：DE3377375

申请日：1983-05-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ZAGRANSKI RAYMOND D ,  HOWLETT JAMES J ,  LAPPOS NICHOLAS D

IPC: F02C9/28 ,  B64C27/00 ,  B64D31/00 ,  B64D31/06 ,  B64D37/00 ,  F02C9/26 ,  F02C9/46

公开(公告)号：CA1198192A

公开(公告)日：1985-12-17

申请号：CA425723

申请日：1983-04-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MORRISON TERRY ,  HOWLETT JAMES J ,  ZAGRANSKI RAYMOND D

IPC: F02C3/10 ,  F02C9/28 ,  G05D1/00 ,  G05D1/08 ,  F02C9/26

Abstract: Helicopter Cruise Fuel Conserving Engine Control A digital fuel control (53) for a helicopter engine (20) controls fuel flow (52) to the engine in response to a turbine reference speed (62) determined in a normal mode (Fig. 5) to be a rated speed, in a fade-in mode (Fig. 6) to be incremented (117, 120) to an estimated optimum minimum speed (114, 115, 125), in an optimizer mode (Fig. 7) to be incremented (138) in a direction (137) leading to least fuel consumption (135), and in a fade-out mode (Fig. 8) to be incremented (151, 153) back to rated speed (154). The invention provides an engine reference speed which results in minimum fuel consumption during cruise flight.

公开(公告)号：DE3376992D1

公开(公告)日：1988-07-14

申请号：DE3376992

申请日：1983-04-15

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MORRISON TERRY ,  ZAGRANSKI RAYMOND D ,  HOWLETT JAMES J

IPC: F02C3/10 ,  F02C9/28 ,  G05D1/00 ,  G05D1/08

Abstract: A digital fuel control (53) for a helicopter engine (20) controls fuel flow (52) to the engine in response to a turbine reference speed (62) determined in a normal mode (Fig. 5) to be a rated speed, in a fade-in mode (Fig. 6) to be incremented (117, 120) to an estimated optimum minimum speed (114, 115, 125), in an optimizer mode (Fig. 7) to be incremented (138) in a direction (137) leading to least fuel consumption (135), and in a fade-out mode (Fig. 8) to be incremented (151, 153) back to rated speed (154). The invention provides an engine reference speed which results in minimum fuel consumption during cruise flight.

公开(公告)号：CA1214149A

公开(公告)日：1986-11-18

申请号：CA425724

申请日：1983-04-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： HOWLETT JAMES J ,  ZAGRANSKI RAYMOND D

IPC: B64C27/14 ,  G05D1/08 ,  B64C27/78

Abstract: Helicopter Engine Torque Compensator The blade angle controlling pitch beam servo (26) of a helicopter tail rotor (22) is responsive to a signal manifestation (76) indicative of free turbine engine (20) gas generator speed (78) to provide torque compensation so that the helicopter airframe will not counter-rotate under the main rotor (10) of a helicopter as a consequence of the torque provided thereto by the airframe-mounted engine (20) or in the absence thereof. A trimming embodiment (Fig. 2) provides only sufficient blade angle command (82a) to compensate for that provided by fixed, collective/tail mixing (110-114). Torque compensation tail rotor blade angle commands may be applied through existing stability and autopilot actuators (30-32) or through an additional torque servo (120, Fig. 3).