Improvement of the Parallel Compressor Model and Application to Inlet Flow Distortion

The determination of the rotational speed and massflow of the fan of a turbofan at windmill is critical in the design of the engine-supporting structure and the sizing of the vertical stabilizer. Given the very high bypass ratio obtained at windmill, the flow in the fan stage and bypass duct is of prime interest. Classical CFD simulations have been shown to predict such flows accurately, but extensive parametric studies can be needed, stressing the need for reduced-cost modeling of the flow in the engine. A Body Force Modeling (BFM) approach for windmilling simulations is examined in the present contribution. The BFM approach replaces turbomachinery rows by source terms, reducing the computational cost (here by a factor 5). A shaft model is coupled to the BFM source terms, to drive the simulation to a power balance of the low-pressure shaft. The overall approach is thus self-contained and can predict both the massflow and the rotational speed in the windmilling regime. Comparisons with engine experimental results show the proposed model can predict the rotational speed within 7 %, and the massflow within 5 %. Local analysis and comparisons with experimental data and reference blade calculations show that the work exchange, in term of total temperature variation, is predicted within 0.5 K, and the overall total pressure ratio within 1 %. However, the losses in the stator are largely underestimated, which explains the discrepancy for the massflow predictions.

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A Modified Circumferentially Averaged Method for Compressor Performance under Inlet Distortion

Yang

Jin

Gui

2023

Aerospace

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Inlet distortion detrimentally affects the aerodynamic performance and lessens the stability of compressors, and has received considerable attention. The need to accurately estimate its effect on the performance and stability of compressor as early as possible in a pre-design cycle is emphasized herein. This work presents a modified circumferential average through flow method (CAM) based on parallel compressor (PC) theory for compressor performance and stability analysis under inlet distortion. The PC approach classically considers independent circumferential flow zones evolving through a compressor, with the same outlet static pressure. In the present work, this theory has been modified in order to create a parametric outlet static pressure boundary condition. It enables us to deal with an upstream flow distortion map, and the meridian plane flow field can then be calculated in order to update the corresponding compressor performance. The model is applied in a compressor which has been tested for its performance characteristics under uniform inlet conditions. Utilizing the new model, the stability and performance of the compressor under inlet distortion can be estimated.

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Improvement of the Parallel Compressor Model and Application to Inlet Flow Distortion

Cited by 3 publications

References 32 publications

A review on aero-engine inlet-compressor integration and inlet flow distortion in axial compressors

A review on aero-engine inlet-compressor integration and inlet flow distortion in axial compressors

Body Force Modeling of the Fan Stage of a Windmilling Turbofan

A Modified Circumferentially Averaged Method for Compressor Performance under Inlet Distortion

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