18337841. AIRFOIL FOR A TURBINE ENGINE simplified abstract (General Electric Company)
Contents
- 1 AIRFOIL FOR A TURBINE ENGINE
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 AIRFOIL FOR A TURBINE ENGINE - 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
AIRFOIL FOR A TURBINE ENGINE
Organization Name
Inventor(s)
Douglas Gerard Konitzer of West Chester (OH)
Ronald Scott Bunker of West Chester OH (US)
Robert David Briggs of West Chester OH (US)
AIRFOIL FOR A TURBINE ENGINE - A simplified explanation of the abstract
This abstract first appeared for US patent application 18337841 titled 'AIRFOIL FOR A TURBINE ENGINE
Simplified Explanation
The patent application describes a method and apparatus for reducing engine weight in a turbine engine by incorporating discrete protuberances on an engine component wall. These protuberances increase the thickness of the wall in specific areas to allow for the creation of cooling holes, while maintaining an overall reduced weight of the engine.
- The wall of the engine component has a nominal thickness to decrease engine weight.
- Discrete protuberances are added to the wall to provide increased thickness in specific areas.
- The increased thickness at the protuberances allows for the creation of cooling holes.
- The cooling holes increase cooling effectiveness without adding significant weight to the engine.
Potential Applications
This technology could be applied in the aerospace industry for the development of lighter and more efficient turbine engines.
Problems Solved
This innovation addresses the challenge of reducing engine weight while maintaining or improving cooling effectiveness in turbine engines.
Benefits
- Reduced engine weight - Improved cooling efficiency - Enhanced overall engine performance
Potential Commercial Applications
"Lightweight Turbine Engine Design for Aerospace Applications"
Possible Prior Art
There may be prior art related to methods of reducing engine weight in turbine engines, but the specific approach of utilizing discrete protuberances on an engine component wall for cooling purposes may be novel.
Unanswered Questions
1. How does the incorporation of discrete protuberances affect the structural integrity of the engine component wall? 2. Are there any limitations to the size or shape of the protuberances that can be added to the wall for cooling hole creation?
Original Abstract Submitted
A method and apparatus for minimizing engine weight for a turbine engine by utilizing one or more discrete protuberances disposed on an engine component wall. The wall can have a nominal thickness to decrease engine weight while the protuberances can provide increased discrete thicknesses for providing one or more cooling holes. The increased thickness at the protuberances provides for an increased thickness to provide sufficient length to increase cooling hole effectiveness.
