17994549. AIRFOIL ASSEMBLY simplified abstract (General Electric Company)
Contents
- 1 AIRFOIL ASSEMBLY
- 1.1 Organization Name
- 1.2 Inventor(s)
- 1.3 AIRFOIL ASSEMBLY - 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 ASSEMBLY
Organization Name
Inventor(s)
Kishore Ramakrishnan of Rexford NY (US)
Valeria Andreoli of Watertown MA (US)
Trevor Howard Wood of Clifton Park NY (US)
AIRFOIL ASSEMBLY - A simplified explanation of the abstract
This abstract first appeared for US patent application 17994549 titled 'AIRFOIL ASSEMBLY
Simplified Explanation
The airfoil assembly for a gas turbine engine includes two blades, each with a leading edge and a trailing edge, and a feature on the leading edge of the first blade that is radially located at or inboard of the chord.
- The airfoil assembly consists of a first blade with a leading edge and a trailing edge, and a second blade spaced from the first blade with its own leading and trailing edges.
- The first blade has a feature on its leading edge that is radially located at or inboard of the chord, which extends from the leading edge to the trailing edge.
- The feature is positioned in such a way that it intersects with the leading edge of the second blade when a line normal to the intersection of the chord with the trailing edge of the first blade is projected radially.
Potential Applications
This technology could be applied in the aerospace industry for improving the performance and efficiency of gas turbine engines.
Problems Solved
This innovation helps in enhancing the aerodynamic performance and efficiency of gas turbine engines by optimizing the design of the airfoil assembly.
Benefits
- Improved aerodynamic performance - Increased efficiency of gas turbine engines - Enhanced overall performance of the aircraft
Potential Commercial Applications
- Aerospace industry for gas turbine engines - Aircraft manufacturing companies
Possible Prior Art
There may be prior art related to the optimization of airfoil designs for gas turbine engines, but specific examples are not provided in this abstract.
Unanswered Questions
How does the feature on the leading edge of the first blade impact the overall aerodynamic performance of the airfoil assembly?
The feature on the leading edge of the first blade is mentioned to be radially located at or inboard of the chord, but the specific aerodynamic effects of this positioning are not detailed in the abstract.
Are there any specific design considerations or limitations associated with the placement of the feature on the leading edge of the first blade?
While the abstract describes the feature being radially located at or inboard of the chord, it does not mention any potential design constraints or limitations that may arise from this specific placement.
Original Abstract Submitted
An airfoil assembly for a gas turbine engine includes a first blade having a first leading edge and a first trailing edge, and a second blade circumferentially spaced from the first blade where the second blade has a second leading edge and a second trailing edge. The first blade includes a feature formed on the first leading edge where the first blade includes a chord extending from the first leading edge to the first trailing edge. The chord is located radially where a projection of a line normal to an intersection of the chord with the first trailing edge intersects the second leading edge. At least a portion of the feature is radially located at or inboard of the chord.
