20240052785. DUCTED TURBOMACHINERY ENGINES simplified abstract (General Electric Company)
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Contents
DUCTED TURBOMACHINERY ENGINES
Organization Name
Inventor(s)
Jeffrey D. Clements of Evendale OH (US)
DUCTED TURBOMACHINERY ENGINES - A simplified explanation of the abstract
This abstract first appeared for US patent application 20240052785 titled 'DUCTED TURBOMACHINERY ENGINES
Simplified Explanation
The patent application describes a turbomachinery engine with specific correlation parameters for optimal performance.
- Ducted fan
- High-pressure compressor
- Low-pressure turbine
- Gearbox
- Ducted engine correlation parameter (DECP) within the range of 0.10-0.25
- DECP formula: 10*d/gr/n/n, where d is fan blade tip diameter, gr is gear ratio, n is stage count of low-pressure turbine, and n is stage count of high-pressure compressor
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- Potential Applications
- Aerospace industry for aircraft engines
- Power generation for gas turbines
- Marine propulsion systems
- Problems Solved
- Improved efficiency of turbomachinery engines
- Optimal performance under various operating conditions
- Reduction in fuel consumption and emissions
- Benefits
- Increased fuel efficiency
- Enhanced engine performance
- Lower operating costs
- Reduced environmental impact
Original Abstract Submitted
a turbomachinery engine comprises a ducted fan, a high-pressure compressor, a low-pressure turbine, a gearbox, and a ducted engine correlation parameter (decp). the decp is within a range of 0.10-0.25 and is defined as 10*d/gr/n/n, where d is a fan blade tip diameter at a leading edge of the ducted fan measured in feet, gr is a gear ratio of the gearbox, nis a stage count of the low-pressure turbine, and nis a stage count of the high-pressure compressor.
