18314418. COMPONENTS FOR COMBUSTOR simplified abstract (GENERAL ELECTRIC COMPANY)
Contents
COMPONENTS FOR COMBUSTOR
Organization Name
Inventor(s)
Karthikeyan Sampath of Bengaluru (IN)
Rimple Rangrej of Bengaluru (IN)
Pradeep Naik of Bengaluru (IN)
Deepak Ghiya of Bengaluru (IN)
Perumallu Vukanti of Bengaluru (IN)
COMPONENTS FOR COMBUSTOR - A simplified explanation of the abstract
This abstract first appeared for US patent application 18314418 titled 'COMPONENTS FOR COMBUSTOR
The patent application describes a combustor for a turbomachine engine that includes a component with a porous structure to reduce combustion dynamics and improve backflow margin of cooling air.
- The component in the combustor has a porous structure defining multiple channels to act as a damper, reducing combustion dynamics.
- A support structure positioned between the diffuser and the combustor component also has a porous structure with multiple channels to improve the backflow margin of cooling air by reducing turbulence.
Potential Applications: - Aerospace industry for turbomachine engines - Gas turbines - Power generation systems
Problems Solved: - Reducing combustion dynamics in a combustor - Improving backflow margin of cooling air
Benefits: - Enhanced engine performance - Increased efficiency - Improved durability of components
Commercial Applications: - Aircraft engines - Industrial gas turbines - Power plants
Prior Art: - Previous patents related to combustor components and support structures in turbomachine engines.
Frequently Updated Research: - Ongoing studies on combustor design for turbomachine engines and their impact on engine performance.
Questions about Combustor for Turbomachine Engine: 1. How does the porous structure of the component reduce combustion dynamics? 2. What are the specific benefits of improving the backflow margin of cooling air in a turbomachine engine?
Original Abstract Submitted
In one aspect, a combustor for a turbomachine engine includes a combustion chamber and a component in operable flow with the combustion chamber. The component has a porous structure that defines multiple channels, that are adapted to configure the component as a damper to reduce combustion dynamics of the combustor. In another aspect, a combustor of a turbomachine engine includes a diffuser, a combustor component positioned aft of the diffuser to receive cooling air therefrom, and a support structure in operable flow with the diffuser and the combustor component and positioned therebetween. The support structure has a porous structure that defines multiple channels, which are adapted to improve a backflow margin of the cooling air by reducing turbulence of the cooling air.
