Honeywell International Inc.

Honeywell G.m.b.h.

Mike S Koerner

Richard Bryce Fox

Stephen Frederic Yates

Russell W Johnson

Peter M Michalakos

Bijan F Hagh

Evgeni Ganev

Deanna Pinar Chase

Paul Kurlak

Cristian E Anghel

Nick A Nolcheff

Dacong Weng

Kyusung Kim

Steven Robert Eccles

Eric Blumer

Raj Mohan Bharadwaj

Allen Kent MacKnight

Mark Kaiser

Filip Reinis

Dennis Mikio Morita

John Meier

Russ Johnson

Henry Au

Myron Quan

James Laffan

Daniel R Robles

Siamak Nikbin

Alan D Hemmingson

John Linert

Zia Iqbal Mirza

Thach Nguyen

Chung Y Liu

Tom Iies

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

An environmental control system (ECS) having contaminants in supply air that flows into an environment includes an outside air contaminant component that senses contaminants in outside air, wherein the outside air contaminant component is upstream of the environment, A recirculated air contaminant component is provided and that senses contaminants in recirculated air supplied by the environment, wherein the recirculated air contaminant component is downstream of the environment. A voltage supply provides a non-linear variable voltage to at least one of the components. A controller is in communication with the components and the voltage supply; wherein, upon a measured resistance, from at least one of the components, that exceeds a threshold, the controller varies at least one of an outside air flow and a recirculated air flow in the ECS.

Adjustable sensor or sensor network to selectively enhance identification of select chemical species

A cooling system in which an ACS (air cycle system) turbine may be driven by high pressure air from a turbo-fan engine and a VCS (vapor cycle system) having an evaporator and a VCS refrigerant compressor may be driven by the ACS turbine. Fluid of the chilled fluid reservoir, which may be chilled fuel, may be circulated through and cooled in the evaporator. In some embodiments, the ACS turbine may be coupled to the VCS refrigerant compressor by a magnetic coupling.

Integrated air and vapor cycle cooling system

An Environmental Control System includes sensors, an air purification subsystem, and a controller in communication with the sensors and air purification subsystem. The sensors detect contaminants in outside air supplied through engine and APU bleeds or other air sources including ground supplies and electric compressors, contaminants in recirculated air, particulates in outside air, carbon dioxide in recirculated air, temperature in an environment, and pressure in an environment. These sensed parameters are compared against thresholds. Based on the comparisons, changes to the outside air and/or recirculated air are made.

Aircraft environmental control system that optimizes the proportion of outside air from engines, APU's, ground air sources and the recirculated cabin air to maintain occupant comfort and maximize fuel economy

An Environmental Control System includes a sensor, an air purification subsystem, and a controller in communication with the sensor and air purification subsystem. The sensor detects a contaminant in the air and generates a contaminant signal. The controller compares the contaminant signal to a predicted sensory response threshold. When the contaminant signal reaches the predicted sensory response threshold, the controller commands the air purification subsystem to alter a condition in the air.

Human factors approach to control contaminant concentrations in aircraft supply air from engine and APU bleed air and ground air sources, and in recirculated air being delivered to aircraft cabins for the optimization of user experience and energy consumption

An environmental control system (ECS) includes a controller; and a mode selector in communication with the controller and configured to select at least one of a plurality of modes. The mode is based on one of: number of occupants in an environment; activity of the occupants in the environment; destination of the environment; and performance of an engine that moves the environment. The controller is configured to change an ECS load on the system based upon the selected mode.

ECO mode ECS logic

A system and method for preventing condensation in a crown area of an aircraft may include routing dry gas into a crown area of the aircraft between the cabin interior panels and the aircraft skin.

System for preventing water condensation inside aircraft

An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages.

Emergency power engine restart system

A power source is provided for a resistive heating element that heats a catalyst bed of a reactor that receives a monopropellant fuel and reacts the fuel in the presence of the catalyst bed to provide hot gas driving a turbine. The power source is a capacitor that discharges its charge across the resistive heating element so that its temperature is elevated to a point where the reaction of the monopropellant fuel occurs. The power source may be used in airborne applications, such as emergency power systems for aircraft, where it is desirable to minimize the weight of the unit and to allow the unit to use safer monopropellant fuels.

Thermal catalytic ignition system for airborne applications

A power generation system including a housing defining a cavity and having an inlet for receiving a fluid that is used to cool and pressurize the cavity and an outlet for removing the fluid from the cavity. The system also may include a rotor having a first end positioned within the cavity of the housing and a second end, a plurality of bearings, positioned to contact the rotor, for providing radial support to the rotor, and a turbine connected to the second end of the rotor. Further, the system may include a heat sink positioned within the cavity and between the housing and the rotor, and an electronic component attached to the heat sink.

Electrical power generation system and method for mitigating corona discharge

One embodiment of the invention provides a turbine control system that adjusts the control thresholds of two-position valves, which provide propellant to the turbine, based on turbine load so as to compensate for increased turbine speed overshoot at low load and the increased turbine speed undershoot at high load. These two-position on-off modulated valves are used in a bang-bang (fully open or fully closed) regulation scheme to eliminate or minimize speed droop by using variable speed bounds implemented as a function of load.

Turbine speed control system and method

A method to desorb water from a desiccant of an air recharge system comprises the steps of a) filling a purge reservoir using an air compressor and a desiccant dryer to produce discharge air, b) stopping the air compressor; c) back purging the desiccant, and d) vent resetting the system, wherein the filling a purge reservoir step does not result in an addition of discharge air to an air storage tank in fluid communication with the purge reservoir and wherein the air storage tank is filled with an amount of the discharge air such that the air storage tank is at a full storage tank pressure prior to filling the purge reservoir. A method of filling an air storage tank of an air recharge system is also disclosed.

Air recharge system dryer and methods therefor

A power generation system including a housing defining a cavity and having an inlet for receiving a fluid that is used to cool and pressurize the cavity and an outlet for removing the fluid from the cavity. The system also may include a rotor having a first end positioned within the cavity of the housing and a second end, a plurality of bearings, positioned to contact the rotor, for providing radial support to the rotor, and a turbine connected to the second end of the rotor. Further, the system may include a heat sink positioned within the cavity and between the housing and the rotor, an electronic component attached to the heat sink, and a reaction chamber for receiving the fluid from the outlet and for producing a substance that is directed to the turbine causing it to rotate.

Growing community of inventors

Rancho Palos Verde, CA, United States of America

Mike S Koerner