17987299. GAS TURBINE ENGINE WITH THIRD STREAM simplified abstract (General Electric Company)
Contents
GAS TURBINE ENGINE WITH THIRD STREAM
Organization Name
Inventor(s)
Arthur William Sibbach of Boxford MA (US)
Jeffrey Donald Clements of Mason OH (US)
GAS TURBINE ENGINE WITH THIRD STREAM - A simplified explanation of the abstract
This abstract first appeared for US patent application 17987299 titled 'GAS TURBINE ENGINE WITH THIRD STREAM
Simplified Explanation
A gas turbine engine described in the patent application includes a turbomachine with a compressor section, a combustion section, and a turbine section in serial flow order. The engine has an inlet duct, a fan duct inlet, and a core inlet. A primary fan is coupled to the turbomachine, and a secondary fan assembly is located downstream of the primary fan within the inlet duct. The secondary fan assembly consists of two secondary fans rotating in opposite directions.
- Explanation of the patent:
- Gas turbine engine with a turbomachine including compressor, combustion, and turbine sections. - Primary fan coupled to the turbomachine. - Secondary fan assembly with two secondary fans rotating in opposite directions.
Potential applications of this technology: - Aircraft engines - Power generation systems - Marine propulsion systems
Problems solved by this technology: - Improved engine efficiency - Enhanced airflow control - Increased power output
Benefits of this technology: - Higher performance - Reduced fuel consumption - Lower emissions
Potential commercial applications of this technology: - Aerospace industry: for aircraft engines - Energy sector: for power generation - Marine industry: for propulsion systems
Possible prior art: - Previous gas turbine engine designs with single fans - Traditional turbomachine configurations without secondary fan assemblies
Unanswered questions: 1. How does the secondary fan assembly impact the overall efficiency of the gas turbine engine? 2. What are the specific design considerations for integrating the secondary fan assembly into existing turbomachine systems?
Original Abstract Submitted
A gas turbine engine may include a turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine defines 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 is drivingly coupled to the turbomachine, and a secondary fan assembly is disposed downstream of the primary fan within the inlet duct. The secondary fan assembly includes a first secondary fan drivingly coupled to the turbomachine in a first rotational direction, and a second secondary fan drivingly coupled to the turbomachine in a second rotational direction opposite the first rotational direction.
