17960230. TURBINE ENGINE WITH COMPONENT HAVING A COOLING HOLE WITH A LAYBACK SURFACE simplified abstract (General Electric Company)
Contents
- 1 TURBINE ENGINE WITH COMPONENT HAVING A COOLING HOLE WITH A LAYBACK SURFACE
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 TURBINE ENGINE WITH COMPONENT HAVING A COOLING HOLE WITH A LAYBACK SURFACE - A simplified explanation of the abstract
- 1.4 Simplified Explanation
- 1.5 Potential Applications
- 1.6 Problems Solved
- 1.7 Benefits
- 1.8 Potential Commercial Applications
- 1.9 Possible Prior Art
- 1.10 Unanswered Questions
- 1.11 Original Abstract Submitted
TURBINE ENGINE WITH COMPONENT HAVING A COOLING HOLE WITH A LAYBACK SURFACE
Organization Name
Inventor(s)
Brian Kenneth Corsetti of Reading MA (US)
John Curtis Calhoun of Cincinnati OH (US)
Dane Michael Dale of Cincinnati OH (US)
TURBINE ENGINE WITH COMPONENT HAVING A COOLING HOLE WITH A LAYBACK SURFACE - A simplified explanation of the abstract
This abstract first appeared for US patent application 17960230 titled 'TURBINE ENGINE WITH COMPONENT HAVING A COOLING HOLE WITH A LAYBACK SURFACE
Simplified Explanation
The patent application describes an apparatus for an engine component in a turbine engine, specifically focusing on a cooling hole within the engine component.
- The engine component includes a wall with a cooling hole that has a passage connecting an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface.
- The cooling hole features a layup surface defining a first angle (α) and a layback surface defining a second angle (β).
Potential Applications
The technology described in the patent application could be applied in various turbine engines, such as aircraft engines, power generation turbines, and industrial gas turbines.
Problems Solved
This technology addresses the challenge of efficiently cooling engine components in high-temperature environments, ensuring optimal performance and longevity of the turbine engine.
Benefits
The apparatus improves the cooling efficiency of engine components, reducing the risk of overheating and potential damage. This leads to increased engine reliability and overall performance.
Potential Commercial Applications
Potential commercial applications of this technology include aerospace companies, turbine engine manufacturers, and companies involved in power generation using turbines.
Possible Prior Art
One possible prior art could be related to existing cooling hole designs in turbine engines, but the specific configuration and angles described in this patent application may offer a novel approach to enhancing cooling efficiency.
Unanswered Questions
How does the apparatus impact the overall weight and size of the turbine engine?
The article does not provide information on the potential impact of this technology on the weight and size of the turbine engine. This aspect is crucial for understanding the overall feasibility and practicality of implementing the apparatus in real-world applications.
Are there any specific maintenance requirements or considerations for the cooling hole apparatus?
The article does not address any maintenance requirements or considerations for the cooling hole apparatus. Understanding the maintenance needs of this technology is essential for ensuring its long-term effectiveness and reliability in turbine engines.
Original Abstract Submitted
An apparatus for an engine component in a turbine engine. The engine component including a wall with a cooling hole having a passage extending between an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface. The cooling hole including a layup surface defining a first angle (α) and a layback surface defining a second angle (β).
