18432818. GAS TURBINE ENGINES AND METHODS ASSOCIATED THEREWITH simplified abstract (General Electric Company)
Contents
- 1 GAS TURBINE ENGINES AND METHODS ASSOCIATED THEREWITH
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 GAS TURBINE ENGINES AND METHODS ASSOCIATED THEREWITH - 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 Original Abstract Submitted
GAS TURBINE ENGINES AND METHODS ASSOCIATED THEREWITH
Organization Name
Inventor(s)
Daniel Endecott Osgood of Loveland OH (US)
Gregory Terrence Garay of West Chester OH (US)
Ryan Christopher Jones of Cincinnati OH (US)
Tingfan Pang of West Chester OH (US)
GAS TURBINE ENGINES AND METHODS ASSOCIATED THEREWITH - A simplified explanation of the abstract
This abstract first appeared for US patent application 18432818 titled 'GAS TURBINE ENGINES AND METHODS ASSOCIATED THEREWITH
Simplified Explanation
The method described in the patent application involves forming cooling apertures in a preform structure of a gas turbine engine component and then applying a coating to the structure to form the final component. The key innovation lies in the fact that the cross-sectional shapes of the cooling apertures in the preform structure are different from each other, but once the coating is applied, the cross-sectional shapes of the cooling apertures in the final component become approximately the same.
- Different cross-sectional shapes of cooling apertures in preform structure
- Coating applied to form final component with approximately same cross-sectional shapes of cooling apertures
Potential Applications
This technology could be applied in the manufacturing of gas turbine engine components, specifically in improving the cooling efficiency of these components.
Problems Solved
This technology solves the problem of efficiently cooling gas turbine engine components by providing a method to form cooling apertures with different shapes in the preform structure, which then become uniform in shape in the final component.
Benefits
- Improved cooling efficiency of gas turbine engine components - Enhanced performance and longevity of the components
Potential Commercial Applications
"Enhanced Cooling Aperture Formation Method for Gas Turbine Engine Components"
Possible Prior Art
There may be prior art related to methods of forming cooling apertures in gas turbine engine components, but the specific innovation of having different cross-sectional shapes in the preform structure before applying a coating may be unique to this patent application.
Unanswered Questions
How does this technology compare to traditional methods of forming cooling apertures in gas turbine engine components?
This article does not provide a direct comparison to traditional methods, so it is unclear how this innovation stacks up against existing techniques in terms of efficiency, cost, and performance.
What are the specific materials and processes used in applying the coating to the preform structure?
The article does not delve into the details of the coating application process, leaving a gap in understanding the practical implementation of this technology.
Original Abstract Submitted
A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.
