18680469. GAS TURBINE ENGINE WITH THIRD STREAM simplified abstract (General Electric Company)

GAS TURBINE ENGINE WITH THIRD STREAM

Organization Name

General Electric Company

Inventor(s)

Brandon Wayne Miller of Middletown OH (US)

Randy M. Vondrell of Newport KY (US)

David Marion Ostdiek of Liberty Township OH (US)

Craig Williams Higgins of Liberty Township OH (US)

Alexander Kimberley Simpson of Cincinnati OH (US)

Syed Arif Khalid of West Chester OH (US)

Jeffrey S. Spruill of Hillsboro OH (US)

Daniel Lawrence Tweedt of West Chester OH (US)

William Joseph Solomon of Montgomery OH (US)

Kevin Edward Hinderliter of Cincinnati OH (US)

GAS TURBINE ENGINE WITH THIRD STREAM - A simplified explanation of the abstract

This abstract first appeared for US patent application 18680469 titled 'GAS TURBINE ENGINE WITH THIRD STREAM

Simplified Explanation:

This patent application describes a gas turbine engine with a unique configuration that includes a primary fan, a secondary fan, and specific airflow ratios.

• The gas turbine engine has a primary fan and a secondary fan located downstream of the primary fan.
• The engine has a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10.
• The thrust to power airflow ratio is the ratio of airflow through the bypass passage and the fan duct to the airflow through the core duct.
• The core bypass ratio is the ratio of airflow through the fan duct to the airflow through the core duct.

Potential Applications:

This technology could be used in aircraft engines, power generation systems, and other applications requiring efficient gas turbine engines.

Problems Solved:

This innovation addresses the need for improved efficiency and performance in gas turbine engines by optimizing airflow ratios and fan configurations.

Benefits:

The benefits of this technology include increased efficiency, reduced fuel consumption, and enhanced overall performance of gas turbine engines.

Commercial Applications:

Commercial applications of this technology could include aircraft propulsion systems, power plants, and marine propulsion systems.

Prior Art:

Readers interested in prior art related to this technology may explore patents and research papers on gas turbine engine design and optimization.

Frequently Updated Research:

Researchers are continually exploring ways to improve gas turbine engine efficiency and performance, making this a rapidly evolving field of study.

Questions about Gas Turbine Engine Technology:

1. How does the configuration of the primary and secondary fans impact the overall performance of the gas turbine engine? 2. What are the potential environmental benefits of using more efficient gas turbine engines in various industries?

Original Abstract Submitted

A gas turbine engine is provided. The gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10, wherein the thrust to power airflow ratio is a ratio of an airflow through a bypass passage over the turbomachine plus an airflow through the fan duct to an airflow through the core duct, and wherein the core bypass ratio is a ratio of the airflow through the fan duct to the airflow through the core duct.