18585509. COMBUSTOR FOR A GAS TURBINE ENGINE simplified abstract (General Electric Company)

COMBUSTOR FOR A GAS TURBINE ENGINE

Organization Name

General Electric Company

Inventor(s)

Karthikeyan Sampath of Bengaluru (IN)

Pradeep Naik of Bengaluru (IN)

Veeraraju Vanapalli of Bengaluru (IN)

Perumallu Vukanti of Bengaluru (IN)

Shai Birmaher of Cincinnati OH (US)

Daniel J. Kirtley of Blue Ash OH (US)

Deepak Ghiya of Bengaluru (IN)

Rample Rakeshkumar Rangrej of Bengaluru (IN)

Saket Singh of Bengaluru (IN)

Ravindra Shankar Ganiger of Bengaluru (IN)

Hiranya Kumar Nath of Bengaluru (IN)

Michael Anthony Benjamin of Cincinnati OH (US)

Rajendra Mahadeorao Wankhade of Bengaluru (IN)

COMBUSTOR FOR A GAS TURBINE ENGINE - A simplified explanation of the abstract

This abstract first appeared for US patent application 18585509 titled 'COMBUSTOR FOR A GAS TURBINE ENGINE

The abstract describes a combustor for a gas turbine engine, with components arranged along the longitudinal, radial, and circumferential directions.

• The combustor includes a forward liner segment and an aft liner segment that define a combustion chamber.
• An intermediate member is positioned between the forward and aft liner segments, extending in the circumferential direction.

Potential Applications: - This technology can be used in gas turbine engines for various applications such as power generation, aviation, and industrial processes.

Problems Solved: - The combustor design improves combustion efficiency and reduces emissions in gas turbine engines.

Benefits: - Enhanced combustion efficiency - Reduced emissions - Improved overall performance of gas turbine engines

Commercial Applications: - This technology can be applied in the aerospace industry for aircraft propulsion systems, as well as in power plants for electricity generation.

Questions about Combustor for Gas Turbine Engine: 1. How does the design of the combustor contribute to improved combustion efficiency? 2. What are the specific advantages of having an intermediate member in the combustor design?

Frequently Updated Research: - Ongoing research focuses on further optimizing the design of combustors for gas turbine engines to enhance performance and reduce environmental impact.

Original Abstract Submitted

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.