18663324. GAS TURBINE ENGINE COMBUSTOR WITH OPENINGS simplified abstract (General Electric Company)

GAS TURBINE ENGINE COMBUSTOR WITH OPENINGS

Organization Name

General Electric Company

Inventor(s)

Perumallu Vukanti of Bengaluru (IN)

Sibtosh Pal of Mason OH (US)

Pradeep Naik of Bengaluru (IN)

R Narasimha Chiranthan of Bengaluru (IN)

Ajoy Patra of Bengaluru (IN)

Michael T. Bucaro of Arvada CO (US)

Aritra Chakraborty of Bengaluru (IN)

Arijit Sinha Roy of Bengaluru (IN)

Pabitra Badhuk of Bengaluru (IN)

Bhavya Naidu Panduri of Bengaluru (IN)

GAS TURBINE ENGINE COMBUSTOR WITH OPENINGS - A simplified explanation of the abstract

This abstract first appeared for US patent application 18663324 titled 'GAS TURBINE ENGINE COMBUSTOR WITH OPENINGS

Simplified Explanation: The patent application describes a gas turbine engine with a unique combustor section design that enhances combustion efficiency.

• The engine includes a compressor section, a combustor section, and a turbine section arranged in a fore-to-aft serial flow.
• The combustor section features a combustor liner and a dome wall that define the combustion chamber.
• A fuel nozzle on the dome wall injects fuel into the combustion chamber.
• Compressed air is emitted into the combustion chamber through two sets of openings along intersecting flow paths, creating a sheet of air.

Key Features and Innovation:

• Unique combustor section design for enhanced combustion efficiency.
• Intersection of two compressed air flow paths to create a sheet of air for improved combustion.
• Efficient fuel injection system with a fuel nozzle on the dome wall.

Potential Applications:

• Aerospace industry for aircraft engines.
• Power generation for gas turbine power plants.

Problems Solved:

• Improved combustion efficiency.
• Enhanced engine performance.
• Reduced emissions.

Benefits:

• Increased fuel efficiency.
• Lower emissions.
• Improved engine reliability.

Commercial Applications: Gas turbine engines with this innovative combustor design could be used in commercial aircraft, military aircraft, and power generation plants, offering improved performance and efficiency.

Prior Art: Prior research on gas turbine engine combustor designs and combustion efficiency could provide valuable insights into the development of this technology.

Frequently Updated Research: Ongoing research on gas turbine engine technology, combustion efficiency, and emissions reduction could impact the further development and application of this innovative combustor design.

Questions about Gas Turbine Engine Combustor Design: 1. How does the unique combustor design improve combustion efficiency in gas turbine engines? 2. What are the potential challenges in implementing this innovative combustor design in existing gas turbine engines?

Original Abstract Submitted

A gas turbine engine includes a compressor section, a combustor section, and a turbine section in fore-to-aft serial flow arrangement and defines an engine centerline. The combustor section includes a combustor liner at least partially defining a combustor chamber and a dome wall, coupled to the combustor liner, and defining a forward end of the combustion chamber. A fuel nozzle is located on the dome wall and fluidly coupled to the combustion chamber. A first set of compressed air openings emit compressed air into the combustion chamber along a first flow path and a second set of compressed air openings emit compressed air into the combustion chamber along a second flow path. The first and second flow paths intersect at an intersection point to form a sheet of air.