17836023. TURBINE ENGINE WITH A BLADE simplified abstract (General Electric Company)

TURBINE ENGINE WITH A BLADE

Organization Name

General Electric Company

Inventor(s)

Jonathan Michael Rausch of West Chester OH (US)

Zachary Daniel Webster of Cincinnati OH (US)

Kevin Robert Feldmann of Mason OH (US)

Andrew David Perry of Cincinnati OH (US)

Kirk Douglas Gallier of Liberty Township OH (US)

Daniel Endecott Osgood of Loveland OH (US)

TURBINE ENGINE WITH A BLADE - A simplified explanation of the abstract

This abstract first appeared for US patent application 17836023 titled 'TURBINE ENGINE WITH A BLADE

Simplified Explanation

The abstract describes a blade for a turbine engine that has a wall separating a cooling fluid flow and a hot gas fluid flow. The blade has a heated surface along which the hot gas fluid flows and a cooled surface facing the cooling fluid flow. There are multiple cooling holes in the blade, each with a passage that extends between an inlet at the cooled surface and an outlet at the heated surface. The outlet of each cooling hole defines a distance between an upstream end and a downstream end with respect to the hot gas fluid flow, and the passage of each cooling hole forms a first angle (θ) with the heated surface.

• The blade has a wall that separates the cooling fluid flow and the hot gas fluid flow.
• The blade has a heated surface where the hot gas fluid flows and a cooled surface facing the cooling fluid flow.
• There are multiple cooling holes in the blade, each with a passage that connects the cooled surface to the heated surface.
• The outlet of each cooling hole defines a distance between an upstream and downstream end with respect to the hot gas fluid flow.
• The passage of each cooling hole forms a first angle (θ) with the heated surface.

Potential Applications

• Turbine engines in aircraft
• Power generation turbines
• Industrial gas turbines

Problems Solved

• Preventing overheating of turbine blades
• Maintaining optimal operating temperatures
• Enhancing the efficiency and performance of turbine engines

Benefits

• Improved cooling of turbine blades
• Increased durability and lifespan of turbine blades
• Enhanced efficiency and performance of turbine engines

Original Abstract Submitted

A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (θ) with the heated surface.