20240011399. BLADE WITH TIP RAIL COOLING simplified abstract (General Electric Company)

BLADE WITH TIP RAIL COOLING

Organization Name

General Electric Company

Inventor(s)

Thomas Earl Dyson of Niskayuna NY (US)

Nicholas William Rathay of Rock City Falls NY (US)

Brendon James Leary of Simpsonville SC (US)

Gregory Terrence Garay of West Chester OH (US)

Gustavo Adolfo Ledezma of Delmar NY (US)

David Wayne Weber of Simpsonville SC (US)

Aaron Ezekiel Smith of Hermosa Beach CA (US)

BLADE WITH TIP RAIL COOLING - A simplified explanation of the abstract

This abstract first appeared for US patent application 20240011399 titled 'BLADE WITH TIP RAIL COOLING

Simplified Explanation

The abstract describes an airfoil design that includes a body with a cooling passage, first and second cooling cavities, a cooling conduit, and a connecting conduit. The body has a tip rail with an exterior surface between three surfaces. The cooling passage is formed within the interior of the body. The first and second cooling cavities are spaced within the tip rail, and the cooling conduit connects the cooling passage to the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.

• The airfoil design includes a body with cooling features to prevent overheating.
• The body has a tip rail with an exterior surface and three surfaces.
• A cooling passage is formed within the interior of the body.
• The first and second cooling cavities are located within the tip rail.
• A cooling conduit connects the cooling passage to the first cooling cavity.
• A connecting conduit allows fluid communication between the first and second cooling cavities.

Potential Applications:

• This airfoil design can be used in aircraft wings to improve cooling and prevent overheating.
• It can also be applied in gas turbine engines to enhance cooling efficiency.

Problems Solved:

• The airfoil design addresses the issue of overheating in high-performance applications.
• It provides an effective cooling system to maintain optimal operating temperatures.

Benefits:

• Improved cooling capabilities enhance the performance and lifespan of the airfoil.
• Preventing overheating reduces the risk of structural damage and improves safety.
• The design can potentially increase the efficiency and reliability of aircraft and gas turbine engines.

Original Abstract Submitted

an airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. the body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. the cooling passage is formed within the interior. the first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. the cooling conduit fluidly couples the cooling passage with the first cooling cavity. the connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.