Honeywell International Inc.

Honeywell G.m.b.h.

Roger D Peckham

Marko Bacic

Glenn A Knight

Jim R Rumbo

James Kenneth Haberstock

Gregory C Carlucci

Dennis David Loots

Michael R Kelley

Jimmy Ray Rumbo

A system and method are provided for controlling turbine blade tip-to-static structure clearance in a gas turbine engine installed on an aircraft. Mode control data are processed to determine that a fuel-saving mode is enabled, and aircraft data are processed to determine that the aircraft gas turbine engine is generating a substantially constant thrust. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is minimized upon determining that both the aircraft gas turbine engine is generating a substantially constant thrust and the fuel-saving mode is enabled. The turbine blade tip-to-static structure clearance in the aircraft gas turbine engine is then selectively increased to a predetermined clearance, and a change in aircraft gas turbine engine thrust is prevented until the predetermined clearance is achieved.

System and method for turbine blade clearance control

An aircraft flight management system having a flight management computer that stores a pre-planned lateral route of flight of the aircraft comprising a plurality of successive waypoints to be overflown, the next proximate waypoint being an active waypoint, a method providing a return-to-path maneuver in the event that the aircraft deviates from the pre-planned route, including selecting a new active waypoint, calculating a return-to-path route to overfly the new active waypoint, and selectably accepting the calculated return-to-path route.

Flight management computer lateral route recapture

A path capture forcing function generator utilizes integrations from an initial altitude rate error signal and an initial altitude error signal to provide an altitude rate signal and an altitude signal which are compared to the altitude rate error and altitude error signals to provide path rate error and path error signals to the autopilot. In the process of providing the altitude rate and altitude error signals an altitude acceleration signal is established which is used as a feed forward predictor for expected normal acceleration of the aircraft.

Path capture forcing function generator for aircraft vertical axis

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Glendale, AZ, United States of America

Roger D Peckham