View source for 20240052785. DUCTED TURBOMACHINERY ENGINES simplified abstract (General Electric Company)

=DUCTED TURBOMACHINERY ENGINES=


==Organization Name==

[[:Category:General Electric Company|General Electric Company]]


[[Category:General Electric Company]]

==Inventor(s)==

[[:Category:Jeffrey D. Clements of Evendale OH (US)|Jeffrey D. Clements of Evendale OH (US)]][[Category: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.



[[Category:F02C7/36]]