18650586. 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)

Jorge De Luis of Cincinnati OH (US)

Douglas Downey Turner of West Chester OH (US)

Michael Macrorie of Winchester MA (US)

Keith W. Wilkinson of Portsmouth NH (US)

Arthur William Sibbach of Boxford MA (US)

Vincenzo Martina of Turin (IT)

GAS TURBINE ENGINE - A simplified explanation of the abstract

This abstract first appeared for US patent application 18650586 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 sequential flow order. The high pressure compressor and drive turbine define specific areas in square inches, with maximum exhaust gas temperature, maximum drive turbine shaft torque, and corrected specific power determined based on these parameters.

• Gas turbine engine with a turbomachine comprising compressor, combustion, and turbine sections
• High pressure compressor and drive turbine defining specific areas in square inches
• Maximum exhaust gas temperature, maximum drive turbine shaft torque, and corrected specific power calculated based on these parameters
• Drive turbine shaft coupled to the drive turbine
• Corrected specific power calculated as Newtons squared times degrees Celsius over meters squared

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

Problems Solved: - Efficient power generation with optimized performance - Reliable propulsion systems for various applications - Enhanced fuel efficiency and reduced emissions

Benefits: - Improved overall efficiency of gas turbine engines - Increased power output with minimal fuel consumption - Enhanced reliability and durability of propulsion systems

Commercial Applications: Title: Advanced Gas Turbine Engine Technology for Aerospace and Power Generation Industries This technology can be utilized in commercial aircraft, power plants, and marine vessels for efficient propulsion and power generation. The market implications include cost savings, improved performance, and reduced environmental impact.

Questions about Gas Turbine Engine Technology: 1. How does the drive turbine shaft torque affect the performance of the gas turbine engine?

  - The drive turbine shaft torque directly influences the power output and efficiency of the engine by determining the rotational force applied to the turbine.

2. What are the key factors that contribute to the calculation of corrected specific power in a gas turbine engine?

  - The corrected specific power is determined by the exhaust gas temperature, drive turbine shaft torque, and specific areas of the compressor and turbine sections in the engine design.

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: