Integrated control system for a gas turbine engine

US4242864A · kind A · utility

Assignee

• The United States of America as represented by the Administrator of the National Aeronautics and Space Administration · US

Inventors

• Jack E. Cornett · Cincinnati, US
• Andrew A. Saunders, Jr. · Cincinnati, US
• Ira E. Marvin · Columbia, US
• Richard S. Beitler · Cincinnati, US

Key dates

• Filing date: May 25, 1978
• Grant date: Jan 6, 1981
• Expiry date: May 25, 1998

Classification

• Technology area (CPC F): Mechanical Engineering; Lighting; Heating
• CPC primary: F02K1/17
• WIPO field: Engines, pumps, turbines
• WIPO sector: Mechanical engineering

Abstract

An integrated control system for a gas turbine engine of the turbofan type receives signals from a plurality of engine sensors and from the engine operator and generates control signals therefrom. A first control signal regulates the fan exhaust nozzle area in order to control inlet throat Mach number to maintain a low level of engine noise. Additional control signals regulate fuel flow to control engine thrust and fan pitch to control fan speed. A plurality of schedules are utilized to maintain a predetermined relationship between the controlled parameters and a number of fixed and calculated limits can override the control signals to prevent unsatisfactory engine performance.