Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Michael C Monzella

Kenneth M Pesyna

Bryan H Lerg

Victor Oechsle

Michael Moser

Renée M Wiley

Michael Grzelecki

Zachary A Rauch

Renée Wiley

A gas turbine engine includes a bypass duct and a rotating detonation augmentor. The bypass duct is configured to conduct air through a flow path arranged around an engine core of the gas turbine engine to provide thrust for propelling the gas turbine engine. The rotating detonation augmentor is located in the bypass duct and configured to be selectively operated to detonate fuel and a portion of the air to increase the thrust for propelling the gas turbine engine.

Rotating detonation augmentors with adjustable throats for gas turbine engines

Various embodiments of the present disclosure provide a turbine engine cooling system configured to provide cooling air to a particular region of the engine to cool that region of the engine. The cooling system is configured to modulate the flow of cooling air to reduce the amount of cooling air flowing to that region of the engine during periods in which less cooling is needed. The cooling system includes a flow limiter configured to choke the mass flow rate of the cooling air provided to the region during modulation to avoid providing more cooling air than is needed to adequately cool that region of the engine.

Flow control in modulated air systems

Growing community of inventors

Indianapolis, IN, United States of America

Michael C Monzella