Alstom Technology Limited

David John Henriquez

Peter Stuttaford

Hany Rizkalla

Stephen Wilder Jorgensen

Charles A Ellis

Sherman Craig Creighton

Plazi Ricklin

A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.

Tunable transition duct side seals in a gas turbine engine

A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.

Transition duct assembly

Growing community of inventors

Hobe Sound, FL, United States of America

David John Henriquez