18675270. GAS TURBINE ENGINE WITH THIRD STREAM simplified abstract (General Electric Company)
Contents
GAS TURBINE ENGINE WITH THIRD STREAM
Organization Name
Inventor(s)
Brandon Wayne Miller of Liberty Township OH (US)
Randy M. Vondrell of Cincinnati OH (US)
David Marion Ostdiek of Liberty Township OH (US)
Craig William Higgins of Liberty Township OH (US)
Alexander Kimberley Simpson of Cincinnati OH (US)
GAS TURBINE ENGINE WITH THIRD STREAM - A simplified explanation of the abstract
This abstract first appeared for US patent application 18675270 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 within the inlet duct.
- 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.
Key Features and Innovation:
- Unique configuration with primary and secondary fans.
- Specific thrust to power airflow ratio and core bypass ratio.
- Optimized airflow distribution for improved engine performance.
Potential Applications:
- Aircraft engines.
- Power generation systems.
- Marine propulsion systems.
Problems Solved:
- Improved engine efficiency.
- Enhanced thrust capabilities.
- Better control of airflow distribution.
Benefits:
- Increased fuel efficiency.
- Higher thrust output.
- Enhanced overall engine performance.
Commercial Applications:
Gas turbine engines with this configuration could be used in commercial aircraft, military jets, and power generation plants to improve efficiency and performance.
Prior Art:
Readers interested in prior art related to this technology may explore patents and research papers on gas turbine engine configurations, airflow ratios, and fan designs.
Frequently Updated Research:
Researchers are constantly studying ways to optimize gas turbine engine designs for better efficiency and performance. Stay updated on the latest advancements in this field.
Questions about Gas Turbine Engine with Primary and Secondary Fans:
1. What are the specific benefits of having a secondary fan in a gas turbine engine? 2. How does the thrust to power airflow ratio impact the overall performance of the engine?
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.
