首页|A numerical simulation strategy for a compressor's underlying axisymmetric characteristic and its application in body force model

A numerical simulation strategy for a compressor's underlying axisymmetric characteristic and its application in body force model

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Accurate prediction of the aerodynamic response of a compressor under inlet distortion is crucial for next-generation civil aircraft,such as Boundary Layer Ingestion(BLI)silent aircraft.Therefore,research on the Body Force(BF)model plays a significant role in achieving this objec-tive.However,distorted inlet airflow can lead to varying operating conditions across different spa-tial locations of the compressor,which may cause some regions to operate outside the stability boundary.Consequently,the accuracy of BF model simulations might be compromised.To address this issue,this paper proposes a numerical simulation strategy for acquiring the steady axisymmetric three-dimensional flow field of a compressor operating at low mass flow rates,which is known as the Underlying Axisymmetric Pressure Rise Characteristic(UAPRC).The proposed simulation accounts for two different rotor speeds of a transonic compressor and identifies initial positions in the flow field where deterioration occurs based on prior experimental investigations.Moreover,simulation results are incorporated into the BF model to replicate hub instability observed in exper-iments.Obtained results demonstrate that this strategy provides valid predictions of the UAPRC of the compressor,thereby addressing the limitations associated with the BF model.

Compressor partial instabil-ityPerformance at low mass flow ratesUnderlying axisymmetric pressure rise characteristicNovel simulation strategyBody force model

Shijie LIU、Tianyu PAN、Qiushi LI

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School of Energy and Power Engineering,Beihang University,Beijing 100191,China

Research Institute of Aero-Engine,Beihang University,Beijing 100191,China

Key Laboratory of Fluid and Power Machinery,Ministry of Education,Xihua University,Chengdu 610039,China

National Natural Science Foundation of ChinaNational Natural Science Foundation of ChinaScience Center for Gas Turbine Project,ChinaScience Center for Gas Turbine Project,ChinaFundamental Research Funds for the Central UniversitiesBeijing Nova Program,ChinaBeijing Nova Program,China

5232260351976005P2022-B-Ⅱ-004-001P2023-B-Ⅱ-001-0012022048407420230484479

2024

10.1016/j.cja.2024.01.032

中国航空学报(英文版)
中国航空学会

中国航空学报(英文版)

CSTPCDEI
影响因子：0.847
ISSN：1000-9361
年,卷(期)：2024.37(8)
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