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Updated: Sep 6, 2025

A Rapid Method for Modeling a Variable Cycle Engine

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Published on: August 13, 2019

Novel Optimization Design Methods of Highly Loaded Compressor Cascades Considering Endwall Effect.

Bo Liu^1,2, Qidong Chen^1,2, Jun Li³

¹School of Power and Energy, Northwestern Polytechnical University, Xi'an 710129, China.

Entropy (Basel, Switzerland)

|June 24, 2022

Summary

The bowed leading-edge strake blade (LESB) modeling method significantly enhances compressor blade aerodynamic performance. This advanced design reduces total pressure loss by 59.7% while lowering solidity.

Keywords:

blade modeling methods compressor cascade endwall effect optimization design

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Area of Science:

Aerodynamics
Turbomachinery
Computational Fluid Dynamics

Background:

The endwall effect critically influences compressor blade aerodynamic performance.
Conventional near-endwall blade modeling methods include bowed blades, endbend blades, and leading-edge strake blades (LESB).

Purpose of the Study:

To develop and evaluate combined optimization design methods for highly loaded compressor blades considering the endwall effect.
To compare the aerodynamic performance of two combined methods (bowed LESB and endbend LESB) against three conventional methods.

Main Methods:

Developed two combined modeling methods: bowed blade with LESB (bowed LESB blade) and endbend blade with LESB (endbend LESB blade).
Conducted optimization designs for a low solidity compressor cascade using these two combined methods and three conventional methods.
Analyzed and compared the aerodynamic performance of the optimized cascades.

Main Results:

All five optimization modeling methods improved the original cascade's performance.
The optimal bowed LESB cascade demonstrated the best aerodynamic performance.
The optimal bowed LESB cascade achieved 40.3% of the original cascade's total pressure loss, reduced solidity from 1.53 to 1.25, and maintained static pressure rise and diffusion factor.

Conclusions:

Combined modeling methods, particularly the bowed LESB approach, offer superior aerodynamic performance improvements for compressor cascades.
The radial migration of low-energy fluid and associated vortex dynamics significantly impact performance, with the bowed LESB cascade showing advantages in managing these effects.