20240011407. TURBINE ENGINE WITH A ROTATING BLADE HAVING A FIN simplified abstract (General Electric Company)

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TURBINE ENGINE WITH A ROTATING BLADE HAVING A FIN

Organization Name

General Electric Company

Inventor(s)

Valeria Andreoli of Watertown MA (US)

Shashwat Swami Jaiswal of Bengaluru (IN)

Thomas William Vandeputte of Scotia NY (US)

TURBINE ENGINE WITH A ROTATING BLADE HAVING A FIN - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240011407 titled 'TURBINE ENGINE WITH A ROTATING BLADE HAVING A FIN

Simplified Explanation

The abstract describes a blade assembly for a gas turbine engine that is designed to rotate around a rotational axis. The blade assembly consists of a blade and at least one fin. The blade extends between a root and a tip, with the tip being spaced radially from the engine casing to create a space in between. The at least one fin extends radially with respect to the tip and into the space.

  • The blade assembly is configured to rotate around a rotational axis.
  • It includes a blade and at least one fin.
  • The blade extends between a root and a tip.
  • The tip is spaced radially from the engine casing, creating a space.
  • The at least one fin extends radially with respect to the tip and into the space.

Potential applications of this technology:

  • Gas turbine engines in various industries such as aviation, power generation, and marine propulsion.
  • Enhancing the performance and efficiency of gas turbine engines.

Problems solved by this technology:

  • Improved aerodynamic performance by utilizing the space between the blade tip and engine casing.
  • Reducing turbulence and losses caused by the interaction between the blade tip and engine casing.

Benefits of this technology:

  • Increased power output and efficiency of gas turbine engines.
  • Reduced fuel consumption and emissions.
  • Improved overall performance and reliability of the engine.


Original Abstract Submitted

a blade assembly for a gas turbine engine having an engine casing, with the blade assembly being configured to rotate about a rotational axis. the blade assembly having a blade, and at least one fin. the blade extending between a root and a tip, with the tip being spaced radially from the engine casing to define a space therebetween. the at least one fin extending radially with respect to the tip and into the space.

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