Siemens Energy, Inc.

Blake R Cotten

Charalambos Polyzopoulos

Richard L Thackway

Stephen A Ramier

Kevin J Spence

Daniel W Garan

Vinayak V Barve

Joseph Scott Markovitz

Khalil Farid Abou-Jaoude

David P Holzapfel

Urmi B Dave

Vaidyanathan Krishnan

Michael C Escandon

An improved combustion section for a gas turbine engine is disclosed. A fuel nozzle includes new features which provide improved injection patterns of oil fuel and cooling water, resulting in better control of combustion gas temperature and NOx emissions, and eliminated impingement of cooling water on walls of the combustor. A new combustor includes a plate-fin design which provides improved cooling, while the combustor also makes more efficient use of available cooling air and has an improved component life. A new transition component has a smoother shape which reduces stagnation of combustion gas flow and impingement of combustion gas on transition component walls, improved materials and localized thickness increases for better durability, and improved cooling features for more efficient usage of cooling air.

W501D5/D5A DF42 combustion system

Effusion cooling holes formed through a transition component provided in a combustion section of a gas turbine engine. The transition component directs a hot working gas from a combustion basket to a first row of vanes in a turbine section of the engine. The effusion cooling holes are formed through an outer wall of the transition component in a direction so that the flow of air through the effusion holes is in a direction substantially opposite to the bulk flow direction of the working gas through the transition component.

Reverse bulk flow effusion cooling

Growing community of inventors

Orlando, FL, United States of America

Blake R Cotten