The Garrett Corporation

Alliedsignal Inc.

Honeywell International Inc.

Robert B Sumegi

Harvey B Jansen

Frederic E Bolliger

Robert A Hatch

Thomas Nesdill

Daniel J Kuhn

Kenneth W Evenson

Cristopher Frost

Ian L Critchley

Geoffrey D Woodhouse

George B Mattson

David G Walhood

Milton R Adams

Barry J Kingery

Klaus K Huber

John A Salisbury, Deceased

A gas turbine engine integrates the functions of an auxiliary power unit (APU) with one or more functions of an ECS, and that is capable of operating in both an unfired mode and a fired mode. The gas turbine engine includes a combustor system that is configured to allow the gas turbine to quickly transition from the unfired mode to the fired mode, by bypassing a portion of the air flowing to the combustor system around the combustor.

Dual mode power unit having a combustor bypass system

An on/off surge prevention control and method for a gas turbine engine having a variable geometry diffuser is provided. This control receives exhaust gas temperature and compressor discharge pressure signals from the engine, and a signal from the aircraft indicative of a need for bleed air. When the aircraft signal is received, the control opens the diffuser to its maximum open setting, and when said aircraft signal is absent closes said diffuser to its minimum open setting. In the event that a faulty aircraft signal is received, the control senses changes in EGT, P3 and dP3/dt and compares these parameters to preselected values indicative of the compressor nearing surge. When the measured values reach the preselected values, the control closes the diffuser to it minimum open setting. By using a temperature signal in determining when to close the diffuser, unwanted closings due to operating transients in compressor discharge pressure are provided. The control prevents the diffuser from being opened, until a second preselected EGT is reached. This second EGT is selected so that it cannot be reached by the engine so long as said aircraft signal is false.

On/off surge prevention control for a variable geometry diffuser

A modulating surge prevention control and method for a gas turbine engine having a variable geometry diffuser is provided. The control calculates a maximum permissible compressor discharge pressure from a predetermined algorithim that is representative of the compressor discharge pressure when the compressor is operating at its minimum permissible surge margin with the diffuser in its maximum open position. The control also receives a signal from a sensor measuring the actual compressor discharge pressure. A error signal is formed by taking the difference between the measured pressure signal and the calculated signal. The control then continously adjusts the area of the diffuser so as to maintain the actual compressor discharge pressure at or below the calculated pressure. The calculated pressure is also corrected for variations in ambient temperature and altitude.

Modulating surge prevention control for a variable geometry diffuser

A recuperated gas turbine engine fuel governor which controls fuel flow in response to both mechanical and electronic input signals.

Gas turbine engine fuel governor

A recuperated gas turbine engine fuel control valve and method which controls fuel flow during engine acceleration as a preselected empirical function of combustor gauge pressure and combustor inlet temperature, and which can also control fuel flow during deceleration without interruption of the combustion process.

Turbine engine fuel schedule valve and method

A control system for a gas turbine engine includes provisions for adjusting fuel flow in relation to gas generator speed, and for adjusting guide vane position in relation to power turbine speed.

Gas turbine engine fuel control

Growing community of inventors

Phoenix, AZ, United States of America

Robert B Sumegi