18481515. Gas Turbine Engine simplified abstract (General Electric Company)

Gas Turbine Engine

Organization Name

General Electric Company

Inventor(s)

Daniel Alan Niergarth of Norwood OH (US)

Jeffrey Donald Clements of Mason OH (US)

Jeffrey S. Spruill of Hillsboro OH (US)

Daniel Endecott Osgood of Loveland OH (US)

Erich Alois Krammer of West Chester OH (US)

Matthew Kenneth Macdonald of Austin TX (US)

Scott Alan Schimmels of Miamisburg OH (US)

Gas Turbine Engine - A simplified explanation of the abstract

This abstract first appeared for US patent application 18481515 titled 'Gas Turbine Engine

The gas turbine engine described in the patent application consists of a turbomachine with a compressor section, a combustion section, and a turbine section arranged in serial flow order.

• The high pressure compressor in the compressor section defines a high pressure compressor exit area (A) in square inches.
• The engine has a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (Fn) in pounds, and a corrected specific thrust between 42 and 90, calculated as Fn×EGT/(A×1000).

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

Problems Solved: - Increased efficiency in gas turbine engines - Enhanced performance in terms of thrust output and specific thrust

Benefits: - Improved fuel efficiency - Higher thrust output - Enhanced overall performance of gas turbine engines

Commercial Applications: Gas turbine engines incorporating this innovation can be used in commercial aircraft, power plants, and marine vessels, leading to increased efficiency and performance in various industries.

Questions about Gas Turbine Engine Technology: 1. How does the high pressure compressor exit area affect the performance of the gas turbine engine? 2. What are the key factors influencing the corrected specific thrust calculation in this technology?

Frequently Updated Research: Researchers are constantly exploring ways to further optimize gas turbine engine performance, efficiency, and reliability through advancements in materials, design, and technology.

Original Abstract Submitted

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having 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; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (Fn) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: Fn×EGT/(A×1000).