Honeywell International Inc.

Honeywell G.m.b.h.

Timothy D Mahoney

David D Jones

Brendan Hall

Darrell Horner

Larry A Portolese

Larry James Yount

Richard Ling

Steven Alan Lewis

Devesh Bhatt

James Neil Quitmeyer

Richard F Hess

Christopher Douglas Eick

Jeff D Miller

Miroslav Krupa

Mitchell Laidlaw

Jay R Sims

William Lorenz

Joseph M Horvath

Anthony C Libera

Pavel Urbanek

Kenneth S Weir

Philip E Rose

Lori Murphy

Scot E Griffiths

William M McMahon

John Teager

Christopher D Eick

A computer-implemented method for real-time streaming of flight data includes receiving flight data from one or more aircraft data sensors, evaluating the received flight data according to data evaluation rules, and upon determining that the received flight data matches one or more conditions specified in the data evaluation rules, starting or stopping a transmission of the received flight data to a ground station.

Systems and methods for real-time streaming of flight data

A system and method for controlling the fuel flow rate in a direct metering fuel control system to compensate for actuator flow. The system includes a fuel metering pump that supplies fuel to a fluid-operated actuator and to a gas turbine engine combustor and determines, using a generated model of the fuel metering pump and/or the fluid-operated actuator, fuel flow rate needed by the gas turbine engine and/or the actuator fuel flow rate needed by the fluid-operated actuator. The fuel flow rate of the fuel metering pump is controlled based on the determined actuator fuel flow rate and the determined engine fuel flow rate.

Actuator flow compensated direct metering fuel control system and method

A fuel supply system includes a fuel metering pump and a servo-flow pump that are used to supply fuel to one or more fuel manifolds and one or more fluid-operated actuators, respectively. The fuel metering pump and the servo-flow pump are driven by the same electric motor(s).

Direct metering fuel control with integral electrical metering pump and actuator servo pump

A distributed engine control system is provided. The engine control system includes first and second engine data concentrators. Each of the first and second engine data concentrators include a processor module, a signal conditioning module coupled to the processor module, a data transfer module coupled to the processor module, and a data bus coupled between the first and second engine data concentrators and a hydro-mechanical unit (HMU).

Distributed engine control system

A method and system for controlling fuel flow in a fuel metering system that includes a metering valve and a proportional bypass valve that produces a differential pressure error across the metering valve includes supplying a first fraction of fuel through the metering valve. A second fraction of the fuel is directed through the proportional bypass valve. The differential pressure error produced by the bypass valve is determined, and fuel flow through the supply line is controlled by adjusting the metering valve based at least in part on the determined differential pressure error, and by adjusting the proportional bypass valve to maintain a substantially constant metering valve differential pressure across the metering valve.

Fuel metering system proportional bypass valve error compensation system and method

A fuel system () for a gas turbine engine () having a shaft () and requiring fuel to be supplied at a first rate for engine start up, the fuel system () including: a main fuel pump () for providing fuel to the gas turbine engine (), the main fuel pump () having an output varying with shaft speed, the output being at a windmilling rate when the engine () is windmilling, the windmilling rate being less than the first rate; and an auxiliary fuel pump () for providing fuel to the gas turbine engine () and having an auxiliary output rate greater than or equal to the difference between the first rate and the windmilling rate. A method of operating such a fuel system () is also disclosed.

Reduced-weight fuel system for gas turbine engine, gas turbine engine having a reduced-weight fuel system, and method of providing fuel to a gas turbine engine using a reduced-weight fuel system

A bleed air power assist system is coupled to a gas turbine engine that includes a high pressure turbine, a low pressure turbine, and an electrical generator driven by the high pressure turbine. The bleed air power assist system selectively bleeds air discharged from the high pressure turbine and supplies it to an air turbine that is also coupled to the generator. Thus, the system selectively reduces the power extracted from the high pressure turbine. This, coupled with the bleed air that is diverted from the low pressure turbine, allows the low pressure spool to run at lower speeds when high engine thrust is not needed or desired, but when the generator is still needed to supply high electrical loads.

Gas turbine engine bleed air power assist system and method

An electromechanical inlet guide vane actuation system includes one or more electric motor driven actuators that are used to appropriately position the inlet guide vanes in a gas turbine engine. The actuation system includes a control circuit that supplies guide vane actuation control signals in response to guide vane position command signals it receives. The guide vane actuation control signals are supplied to one or more electric motors, which position actuators, and thus the inlet guide vanes, to the commanded position.

Gas turbine engine electromechanical variable inlet guide vane actuation system

A common design framework for input and output signal validation, arbitration, and fault reporting for real-time controllers includes a method of validating redundant input and output signals and arbitrating between the redundant input and output signals by determining a fault severity level for each of the redundant input and output signals, and determining a signal to transmit for further processing based at least in part on the determined fault severity levels.

Signal validation and arbitration system and method

A highly reliable, multi-channel control, monitoring, and protection system includes at least three processors in each of the redundant channels, a main processor, and first and second monitor processors. The main processor performs the main control functions, and the monitor processors mirror one or more of the functions performed by the main processor. The processing performed in the main processor and the monitor processors is continuously compared to determine whether control needs to be shifted to one of the other redundant channels.

Jet engine control and protection system and method

A system for controlling the flow of fuel to a gas turbine engine is operable in at least two modes. In a first mode, the flow rate of fuel supplied from a fuel source to the combustors of the turbine engine is controlled by modulating the position of a metering valve. A controller determines the controllability of the metering valve and, if it is determined to be non-controllable, then the system is operated in the second mode. In the second mode, the flow rate of fuel supplied to the combustors is controlled by modulating the position of a bypass valve.

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Chandler, AZ, United States of America

Timothy D Mahoney