Honeywell International Inc.

Ronald A Peck

Donald Jeffrey Christensen

William Lee Giesler

Todd Langston

Stephen G Abel

George T Woessner

David M Mathis

Mark H Baker

Tony Libera

Ronald Pardini

Marvin K Collins

Cynthia S Byers

Air Turbine Starter (ATS) systems are provided, as gas turbine engines including ATS systems. In one embodiment, a gas turbine engine includes an accessory gearbox (AGB) and an integrated Air Turbine Starter (ATS) system. The AGB includes a gearbox gear train within a gearbox housing. The integrated ATS system is removably installed on the AGB and includes an ATS having an air turbine and an output shaft coupled thereto. An ATS clutch module is coupled to the ATS output shaft. The ATS clutch module is further within the gearbox housing and mechanically couples the ATS output shaft to the gearbox gear train when the integrated ATS system is installed on the AGB.

Air turbine starter systems including gearbox-integrated clutch modules and gas turbine engines employing the same

Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on pulse width modulation of a control valve duty cycle. A control valve that is movable between a closed position and a full-open position is disposed downstream of, and in fluid communication with, a solid propellant gas generator. The solid propellant in the solid propellant gas generator is ignited, to thereby generate propellant gas. The control valve is moved between the closed position and the full-open position at an operating frequency and with a valve duty cycle. The valve duty cycle is the ratio of a time the control valve is in the full-open position to a time it takes the valve to complete one movement cycle at the operating frequency. The valve duty cycle is controlled to attain a desired solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and/or propellant gas flow rate.

Solid propellant burn rate, propellant gas flow rate, and propellant gas pressure pulse generation control system and method

An air turbine starter (ATS) configured to couple to a gearbox, the ATS including an output shaft having an outer peripheral surface, a gearbox section, and an ATS section, the gearbox section configured to be disposed within, and coupled to, the gearbox and the ATS section configured to be disposed within the ATS, and a shield plate extending radially from the outer peripheral surface and coupled to the ATS section of the output shaft.

Air turbine starter enhancement for clearance seal utilization

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Phoenix, AZ, United States of America

Ronald A Peck