This invention outlines the shape of a rotor blade, used in axial flow fans and compressors, that minimizes the variation in the gap between the tip and the casing, making the compressor more stable while operating. The design introduces a split hederal tip to the rotor blade that are twisted in opposite directions. This design also offers high aerodynamic efficiency and minimizes the aerodynamic tip loss. These improvements help reduce the tip gap sensitivity of axial compressors.
Figure (1) Illustrations of the new rotor tip design; (2) An efficiency comparison between the standard and modified rotor blades; (3) An aerodynamic comparison between the standard and modified rotor blades.
During the operation of an axial compressor, the gap between the tip of its rotor blade and the casing is subjected to various thermal and mechanical stresses. Hot gas passing through the structure differentially expands the casing, causing a gap change between the rotor tip and the casing. The efficiency of the compressor decreases a lot with gap enlargement, making it highly tip gap sensitive, a recurring problem which prior designs have failed to solve. Thus, there is a need for a blade shape design that reduces the sensitivity of the compressor efficiency to tip gap enlargements.
- Split dihedral tip: a new design which involves twisting the rotor blade in opposite direction, instead of one direction, to reduce the tip gap sensitivity of the compressor
- Insensitivity to tip gap variation: this design of the rotor blade minimizes gap variation caused during compressor operations, reducing the tip gap sensitivity
- Stable compressor performance: this design maximizes aerodynamic efficiency, increasing the efficiency insensitivity to tip gap variations and the performance stable
A scaled-down prototype of the rotor blade featuring the split dihedral tip has been tested under controlled lab conditions using aerodynamic rigs. Results indicate improved flow behavior and reduced sensitivity to tip gap variations compared to conventional blade designs.
The technology has been validated through aerodynamic simulations and experimental testing on scaled prototypes. Performance data confirms that the split dihedral tip design effectively reduces tip gap sensitivity and improves compressor efficiency.
5
This innovation can significantly improve the efficiency and reliability of jet engines and industrial gas turbines. It contributes to reduced fuel consumption and lower emissions, supporting both economic and environmental goals in aerospace and power generation sectors.
Jet engines, axial flow compressors in aircraft, industrial gas turbines, turbo machinery, and other systems where aerodynamic efficiency and stability are critical under thermal/mechanical stress.
Geography of IP
Type of IP
2856264
408281