About this document
Gas Turbine Combustor Design Patent by Rohit is a document available to read on EtoBox.
This patent describes a gas turbine combustor design with features to reduce combustion instability. The combustor contains a central pilot nozzle surrounded by eight main nozzles. An annular flow ring and porous plate are placed upstream to straighten the airflow entering the combustor without disturbances, ensuring homogeneous air around the nozzles. This improves combustion stability and allows operation over a wider range of conditions.
- Author
- Rohit
- Language
- EN