The Boeing Company

Peter J Louden

Alexander P Borelan

James T Giffin

Malcolm L Olthouse

Kurt Randall Kraft

Thomas M Baker

Gary L Vieth

Jeffrey E Duven

Michael T Dunn

Jim W Hackler

Clifford M Schjoneman

A fire seal (52) for an aircraft propulsion system including at least one mating plate pair (54) formed between a nozzle body (44) and an outer structure (24) and a support pylon (26). The mating plate pairs (54) each include an upper plate row (58) and a lower plate row (60), both rows extending in an arc (66) about an upper region (56) of the propulsion system, with a vertical overlap (88) existing between the upper and lower plate rows. A gap (90) exists between the upper plate row (58) and lower plate row (60) of each mating plate pair (54), preferably at all times. A seal region (62) exists between the forward-most mating pair and the aft-most mating pair. A pressure equalization mechanism controls pressure between the area forward of the seal region (62) and the area aft of the seal region (62). A number of endplates (110) are positioned at various longitudinal locations near the lateral ends of the mating plate pairs. A method of fire-sealing an aircraft propulsion system fire zone area including providing at least one mating plate pair (54) positioned between opposed surfaces in order to create a labyrinth path through which flame has difficulty passing. The method further includes controlling pressure between the area forward of the mating plate pairs and the area aft of the mating plate pairs.

Aircraft labyrinth fire seal

Flight deck information warning system for notifying the flight crew of abnormal engine operating conditions in the sub-idle region. The warning system is responsive to signals representative of engine exhaust temperature, engine core rotor speed, total air temperature, engine fuel flow and, airframe calibrated airspeed.

Abnormal start advisory system (ASAS) for aircraft engines

A logic controlled APR system including arming logic, engine failure detection circuits, and test circuit means for testing system operating condition without engine operation. The logic controlled APR system detects an engine failure in a multi-engine aircraft and provides solenoid controlled increased fuel flow to the remaining normally operating engines, and includes a disarm mode in the event of an RTO (rejected take-off).

Automatic performance reserve (APR) system having means indicative of

A logic controlled APR system including arming logic, engine failure detection circuits, and system fault detector circuit means for monitoring system integrity. The logic controlled APR system detects an engine failure in a multi-engine aircraft and provides increased fuel flow to the remaining normally operating engines, and includes a disarm mode in the event of an RTO (rejected take-off).

Automatic performance reserve (APR) system

Growing community of inventors

Mercer Island, WA, United States of America

Peter J Louden