General electric company (20240247807). COMBUSTOR FOR A GAS TURBINE ENGINE simplified abstract

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 20240247807 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 to define a combustion chamber.

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

Potential Applications: - Aerospace industry for gas turbine engines. - Power generation for gas turbine applications.

Problems Solved: - Efficient combustion chamber design. - Enhanced performance and durability of gas turbine engines.

Benefits: - Improved fuel efficiency. - Reduced emissions. - Increased engine lifespan.

Commercial Applications: - Aircraft engines. - Power plants. - Marine propulsion systems.

Questions about Combustor Technology: 1. How does the arrangement of the liner segments contribute to combustion efficiency? 2. What materials are commonly used for the construction of combustors in gas turbine engines?

Frequently Updated Research: - Ongoing studies on optimizing combustion processes in gas turbine engines. - Research on advanced materials for increased durability and performance in combustor components.

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.