Power Systems Mfg., LLC

Ansaldo Energia IP UK Limited

H2 IP UK Limited

Ramesh Keshava-Bhattu

Hany Rizkalla

Stephen Wilder Jorgensen

Gregory Edwin Vogel

Joshua R McNally

Gene Chong

Matthew Yaquinto

Jeremy Metternich

Fred Hernandez

Bryan Kalb

David Giel

James Brackett

Bernard Tam Yen Sam

David E Paredes

Stephen W Jorgensen

An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. Each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes includes a substantially quadrilateral cross-sectional profile, and each of the air/fuel mixing tubes of the radially inner subset of air/fuel mixing tubes includes a substantially circular cross-sectional profile.

Multitube pilot injector having a split airflow for a gas turbine engine

The present invention discloses a novel apparatus and way for sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is utilized having a first annular portion, a second annular portion, and a transition portion, the compressible seal regulates airflow passing through the compressible seal via a plurality of openings and/or axially extending slots.

Sealing device for a gas turbine combustor

Growing community of inventors

Jupiter, FL, United States of America

Ramesh Keshava-Bhattu