View source for General electric company (20240280049). GAS TURBINE ENGINE simplified abstract

=GAS TURBINE ENGINE=


==Organization Name==

[[:Category:general electric company|general electric company]]


[[Category:general electric company]]

==Inventor(s)==

[[:Category:Daniel Alan Niergarth of Norwood OH (US)|Daniel Alan Niergarth of Norwood OH (US)]][[Category:Daniel Alan Niergarth of Norwood OH (US)]]

[[:Category:Jorge De Luis of Cincinnati OH (US)|Jorge De Luis of Cincinnati OH (US)]][[Category:Jorge De Luis of Cincinnati OH (US)]]

[[:Category:Douglas Downey Turner of West Chester OH (US)|Douglas Downey Turner of West Chester OH (US)]][[Category:Douglas Downey Turner of West Chester OH (US)]]

[[:Category:Michael Macrorie of Winchester MA (US)|Michael Macrorie of Winchester MA (US)]][[Category:Michael Macrorie of Winchester MA (US)]]

[[:Category:Keith W. Wilkinson of Portsmouth NH (US)|Keith W. Wilkinson of Portsmouth NH (US)]][[Category:Keith W. Wilkinson of Portsmouth NH (US)]]

[[:Category:Arthur William Sibbach of Boxford MA (US)|Arthur William Sibbach of Boxford MA (US)]][[Category:Arthur William Sibbach of Boxford MA (US)]]

[[:Category:Vincenzo Martina of Turin (IT)|Vincenzo Martina of Turin (IT)]][[Category:Vincenzo Martina of Turin (IT)]]

==GAS TURBINE ENGINE - A simplified explanation of the abstract==


This abstract first appeared for US patent application 20240280049 titled 'GAS TURBINE ENGINE

The abstract describes a gas turbine engine with a turbomachine consisting of a compressor section, a combustion section, and a turbine section in serial flow order. The high pressure compressor and drive turbine define specific areas, and the engine has maximum exhaust gas temperature, maximum drive turbine shaft torque, and corrected specific power.

* Gas turbine engine with a turbomachine comprising compressor, combustion, and turbine sections.
* High pressure compressor and drive turbine define specific areas.
* Engine has maximum exhaust gas temperature, maximum drive turbine shaft torque, and corrected specific power.

Potential Applications:
- Aerospace industry for aircraft propulsion systems.
- Power generation for electricity production.
- Marine propulsion for ships and boats.

Problems Solved:
- Improved efficiency in power generation.
- Enhanced performance in aircraft propulsion.
- Increased reliability in marine propulsion systems.

Benefits:
- Higher power output.
- Lower fuel consumption.
- Reduced emissions.

Commercial Applications:
Title: Advanced Gas Turbine Engines for Various Industries
This technology can be used in aircraft, power generation plants, and marine vessels, offering improved efficiency and performance.

Prior Art:
Research on gas turbine engines, turbomachinery design, and combustion systems can provide insights into the development of this technology.

Frequently Updated Research:
Ongoing studies focus on enhancing the efficiency and durability of gas turbine engines, exploring new materials and design techniques.

Questions about Gas Turbine Engines:
1. How do gas turbine engines compare to other types of propulsion systems?
Gas turbine engines are known for their high power-to-weight ratio and efficiency compared to reciprocating engines or electric motors.

2. What advancements have been made in gas turbine engine technology in recent years?
Recent advancements include improved materials, aerodynamics, and control systems, leading to higher performance and efficiency.


==Original Abstract Submitted==

a gas turbine engine is provided having a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (a) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (a) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine; wherein the gas turbine engine defines a maximum exhaust gas temperature (egt) in degrees celsius, a maximum drive turbine shaft torque (t) in newton meters, and a corrected specific power (csp) in newtons squared times degrees celsius over meters squared, wherein the corrected specific power is determined as follows:



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