Compressor Rotor Leading-Edge Geometry for Super-Cooled Ice Protection
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing anti-icing systems for gas turbine engines, such as electrical heaters and hot air conduits, are complex and detrimental to efficiency, necessitating a more effective and efficient solution for super-cooled ice protection.
Innovation Solution
Designing the first rotor blades in the compressor with a larger leading edge radius than the downstream blades to act as a shield against super-cooled ice impacts, allowing the downstream rotors to optimize aerodynamic efficiency without additional thickness for ice protection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If electrical heaters or hot air conduits are used for anti-icing, then ice protection is achieved, but system complexity and efficiency loss increase
Solution Approach 1:
The patent extracts the ice protection function from complex active systems (heaters, hot air conduits) and transfers it to the blade geometry itself. The first rotor blades are designed with increased leading edge radius specifically to resist ice impact, while downstream blades maintain optimized aerodynamic shapes. This separates the protection function from the aerodynamic function, eliminating the need for additional anti-icing systems.
Solution Approach 2:
The patent applies local quality by differentiating the leading edge radius of the first rotor blades from that of downstream blades. The first rotor blades have a larger leading edge radius (greater than 2.8 times that of downstream blades) specifically at the ice impact zone, while other portions of the blades maintain their aerodynamic optimization. This localized geometric modification provides ice protection exactly where needed without compromising overall aerodynamic efficiency.
2Reliability
If downstream rotor blades are thickened for ice protection, then ice resistance improves, but aerodynamic efficiency deteriorates
Solution Approach 1:
The patent segments the ice protection function to be performed exclusively by the first rotor blades, which are positioned upstream to intercept ice particles. This segmentation allows downstream rotor blades to maintain their thin, aerodynamically optimized profiles without ice protection modifications, as the first rotor blades already provide sufficient protection for the entire compressor section.
Solution Approach 2:
The first rotor blades perform preliminary ice impact absorption before ice particles can reach downstream blades. By positioning the ice-resistant blades upstream and giving them enhanced leading edge radius, the system provides preliminary protection that prevents ice from reaching and damaging the aerodynamically optimized downstream blades.
Data Source
AI summary
A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.