Honeywell International Inc.

Alan D Hemmingson

Cristian E Anghel

Nick A Nolcheff

Richard Ling

Mike S Koerner

John Meier

Oswald George Harris

James Laffan

A propulsion and electric power generation system includes a gas turbine propulsion engine, an electrical generator, an aircraft power distribution system, a plurality of auxiliary fans, and a controller. The gas turbine propulsion engine includes at least a low-pressure turbine coupled to a fan via a low-pressure spool, and the low-pressure turbine is configured to generate mechanical power. The electrical generator is directly connected to the low-pressure spool and generates a total amount of electrical power (Pe). The aircraft power distribution system receives a first fraction (Pa) of the total amount of electrical power. The auxiliary fans receive a second fraction (Pf) of the total amount of electrical power. The controller is configured to control a ratio of Pf to Pa (Pf/Pa) such that the ratio spans a range from less than 0.6 to at least 0.9.

Distributed propulsion and electric power generation system

A system and method of phase compensating transient performance data are provided. Transient performance data are collected for a plurality of parameters, and two of the parameters are selected. A transfer function is applied to the transient performance data for at least one of the selected parameters to thereby generate phase compensated performance data that is representative of a steady state relationship between the selected parameters.

Transient performance data phase compensation system and method

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Tempe, AZ, United States of America

Alan D Hemmingson