Siemens Aktiengesellschaft

Siemens Energy Global Gmbh & Co. Kg

Sachin Terdalkar

Timothy A Fox

Robert H Bartley

Vinayak V Barve

Rajesh Rajaram

Wojciech Dyszkiewicz

Daniel Cassar

John M Crane

A gas turbine engine has a resonator ring that is formed by two circumferentially extending rings. The first and second circumferentially extending rings have located within them baffles. Both the first ring and the second ring are able to mitigate acoustic frequencies generated by the gas turbine engine.

Gas turbine engine with resonator rings

A fuel burner system () configured to inject a liquid fuel and a gas fuel into a combustor () of a turbine engine () such that the engine () may operate on the combustion of both fuel sources () is disclosed. The fuel burner system () may be formed from a nozzle cap () including one or more first fuel injection ports () in fluid communication with a first fuel source () of syngas and one or more second fuel injection ports () in fluid communication with a second fuel source () of natural gas. The fuel burner system () may also include an oil lance () with one or more oil injection passages () that is in fluid communication with at least one oil source () and is configured to emit oil into the combustor (). The oil lance () may include one or more fluid injection passages () configured to emit air to break up the oil spray and water to cool the combustor (), or both.

Flexible fuel combustion system for turbine engines

Growing community of inventors

Oviedo, FL, United States of America

Sachin Terdalkar