18625749. TURBINE ENGINE WITH SHOCKWAVE ATTENUATION simplified abstract (General Electric Company)
Contents
TURBINE ENGINE WITH SHOCKWAVE ATTENUATION
Organization Name
Inventor(s)
Christopher Ryan Johnson of Fairfield OH (US)
Paul Hadley Vitt of Liberty Twp OH (US)
Eric Joseph Schroeder of Loveland OH (US)
Carlos Gilberto Fernandez-soto of Fairfield Twp OH (US)
TURBINE ENGINE WITH SHOCKWAVE ATTENUATION - A simplified explanation of the abstract
This abstract first appeared for US patent application 18625749 titled 'TURBINE ENGINE WITH SHOCKWAVE ATTENUATION
Simplified Explanation: The patent application describes a turbine engine with a compressor, combustor, and turbine arranged in axial flow. The engine core has a flow path for working airflow from the compressor to the turbine.
- The turbine engine includes a compressor, combustor, and turbine in axial flow arrangement.
- The engine core has a flow path for working airflow from the compressor to the turbine.
- The flow path defines the direction of airflow through the engine core.
Key Features and Innovation:
- Axial flow arrangement of compressor, combustor, and turbine.
- Defined flow path for working airflow through the engine core.
Potential Applications: The technology can be used in aircraft engines, power generation systems, and other applications requiring efficient turbine engines.
Problems Solved: The technology improves the efficiency and performance of turbine engines by optimizing the flow path of working airflow.
Benefits:
- Increased efficiency of turbine engines.
- Enhanced performance of aircraft engines and power generation systems.
Commercial Applications: The technology can be applied in the aerospace industry for aircraft engines, as well as in power generation for more efficient energy production.
Questions about Turbine Engine Technology: 1. How does the axial flow arrangement improve the performance of turbine engines? 2. What are the potential applications of this technology in the aerospace industry?
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Original Abstract Submitted
A turbine engine and method of operating includes an engine core with a compressor, a combustor, and a turbine in axial flow arrangement. A flow path extends through the engine core from the compressor to the turbine to define a flow direction for a working airflow through the engine core.
