18597287. COMBUSTOR WITH BAFFLE simplified abstract (GENERAL ELECTRIC COMPANY)

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COMBUSTOR WITH BAFFLE

Organization Name

GENERAL ELECTRIC COMPANY

Inventor(s)

Michael T. Bucaro of Arvada CO (US)

Clayton S. Cooper of Evendale OH (US)

COMBUSTOR WITH BAFFLE - A simplified explanation of the abstract

This abstract first appeared for US patent application 18597287 titled 'COMBUSTOR WITH BAFFLE

Simplified Explanation:

This patent application describes a turbine engine with a unique combustor design that includes a combustor liner with dilution openings and a changing geometry along the axial direction. The combustor also features a baffle surrounding the liner to define a combustion chamber. The method outlined in the patent involves controlling nitrogen oxides by injecting compressed air into the combustion chamber through the dilution openings.

  • The turbine engine includes a combustor with a combustor liner that has dilution openings and a geometry that varies along the axial direction.
  • A baffle surrounds the combustor liner to define a combustion chamber within the combustor.
  • The method for controlling nitrogen oxides involves injecting compressed air into the combustion chamber through the dilution openings.

Potential Applications:

1. Aerospace industry for aircraft engines. 2. Power generation for gas turbines. 3. Industrial applications for combustion systems.

Problems Solved:

1. Reduction of nitrogen oxides emissions. 2. Improved combustion efficiency. 3. Enhanced durability of combustor components.

Benefits:

1. Lower environmental impact. 2. Increased fuel efficiency. 3. Extended lifespan of turbine engine components.

Commercial Applications:

Title: Innovative Combustor Design for Turbine Engines

This technology can be utilized in aircraft engines, power generation systems, and industrial combustion applications. The market implications include improved performance, reduced emissions, and cost savings for operators.

Questions about Turbine Engine Combustor Design:

1. How does the unique geometry of the combustor liner contribute to improved combustion efficiency? 

  - The changing geometry optimizes airflow and fuel mixing, leading to more efficient combustion.

2. What are the potential cost savings for operators implementing this technology? 

  - Operators can benefit from reduced fuel consumption and maintenance costs over the lifespan of the turbine engine.


Original Abstract Submitted

A turbine engine and associated methods for a combustor as shown and described. The turbine engine including a combustor with a combustor liner having dilution openings and a geometry that changes along an axial direction. The combustor further having a baffle surrounding a combustor liner defining a combustion chamber of the combustor. A method for controlling nitrogen oxides within the combustor, including injecting compressed air into the annular combustion chamber through any of the dilution openings described herein.

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