17835091. GAS TURBINE ENGINE WITH AN AIRFOIL simplified abstract (General Electric Company)

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GAS TURBINE ENGINE WITH AN AIRFOIL

Organization Name

General Electric Company

Inventor(s)

Rathakrishnan Bhaskaran of Niskayuna NY (US)

Thomas W. Vandeputte of Scotia NY (US)

GAS TURBINE ENGINE WITH AN AIRFOIL - A simplified explanation of the abstract

This abstract first appeared for US patent application 17835091 titled 'GAS TURBINE ENGINE WITH AN AIRFOIL

Simplified Explanation

Abstract: A turbine engine consists of three sections: a compressor section, a combustion section, and a turbine section. The combustion section burns fuel, which in turn powers the turbine section to drive the compressor section. The airfoils in the turbine section have a specific design near the trailing edge to minimize the shock generated in their wake.

  • The turbine engine has a compressor section, combustion section, and turbine section.
  • Fuel is burned in the combustion section.
  • The combustion process powers the turbine section.
  • The turbine section drives the compressor section.
  • The airfoils in the turbine section have a unique design near the trailing edge.
  • The design includes a linear portion between the pressure side and a curved portion.
  • The purpose of the design is to reduce the shock generated in the wake of the airfoils.

Potential Applications:

  • Aircraft engines
  • Power generation turbines
  • Industrial gas turbines

Problems Solved:

  • Minimizing shock generated in the wake of airfoils
  • Improving the efficiency and performance of turbine engines

Benefits:

  • Increased efficiency of turbine engines
  • Reduced fuel consumption
  • Improved overall performance of the engine


Original Abstract Submitted

A turbine engine includes a compressor section, a combustion section, and a turbine section. Fuel combusted in the combustion section drive stages of airfoils in the turbine section to drive the compressor section. The airfoils can include a geometry near or at the trailing edge with a linear portion provided between the pressure side and a first curved portion, to reduce shock generated in the wake of the airfoils.

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