Effect of rotor axial blade loading distribution on compressor stability

Xu, Dengke; Dong, Xu; Zhou, Chenghua; Sun, Dakun; Gui, Xingmin; Sun, Xiaofeng

doi:10.1016/j.ast.2021.107230

Cited by 10 publications

(3 citation statements)

References 31 publications

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“…The rotor blade loading distribution affects the compressor stability, mainly in nearstall points [36]. Thus, to analyze the blade loading [37], the pressure coefficient (C p ) can be determined along the blade chord by…”

Section: Aerodynamic Parametersmentioning

confidence: 99%

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Aerospace

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The ratio between blade height and chord, named the aspect ratio (AR), plays an important role in compressor aerodynamic design. Once selected, it influences stage performance, blade losses and the stage stability margin. The choice of the design AR involves both aerodynamic and mechanical considerations, and an aim is frequently to achieve the desired operating range while maximizing efficiency. For a fixed set of aerodynamic and geometric parameters, there will be an optimal choice of AR that achieves a maximum efficiency. However, for a state-of-the-art aero-engine design, optimality means multi-objective optimality, that is, reaching the highest possible efficiency for a number of operating points while achieving a sufficient stability margin. To this end, the influence of the AR on the performance of the first rotor row of a multistage, multi-objective, high-speed compressor design is analyzed. A careful setup of the high-speed aerodynamic design problem allows the effect of the AR to be isolated. Close to the optimal AR, only a modest efficiency variation is observed, but a considerable change in compressor stability margin (SM) is noted. Decreasing the AR allows for increasing efficiency, but at the expense of a reduced surge margin. This allows the designer to trade efficiency for stability. Increasing the AR, however, is shown to reduce both the surge margin and efficiency; hence, a distinct optimality in stability is observed for the analyzed rotor blade row. In this work, optimality in the surge margin with respect to the AR is observed, whereas there is a close to optimal efficiency. The predicted range from AR = 1.10 to AR = 1.64 is only indicative, considering that the definition of multi-objective optimality requires balancing efficiency and the surge margin and that the choice of balancing these two criteria requires making a design choice along a pareto optimal front.

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Section: Aerodynamic Parametersmentioning

confidence: 99%

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Aerospace

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show abstract

“…The equations presented in ( 21) account for a variety of phenomena and features of the compression system, such as system volumes, inlet and diffuser shapes, axisymmetric compressor characteristics, throttle characteristics, system hysteresis, compressor geometry, and internal lag processes in the subsystems. Modifications of the MG model to include effects generated by inlet distortion, compressibility inside the compressor, rotational speed variation, and many other improvements have been proposed from other researchers [14,18,[31][32][33].…”

Section: Mathematical Modelmentioning

confidence: 99%

AI-Based Detection of Surge and Rotating Stall in Axial Compressors via Dynamic Model Parameter Estimation

Zanotti,

Ceschini,

Ferlauto

2024

Fluids

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Compressors are an essential component of aircraft engines. Their design and operation must be extremely reliable as engine safety and performance depend greatly on these elements. Axial compressors exhibit instabilities, such as surge or rotating stall, in a region close to the peak of their performance curves. These fluid dynamic instabilities can cause drops in efficiency, stress on the blades, fatigue, and even failures. Compressors are handled therefore by operating with a safety margin far from the surge line. Moreover, models able to predict onset instabilities and to reproduce them are of great interest. A dynamic system able to describe successfully both surge and rotating stall is the model presented by Moore and Greitzer That model has also been used for developing control laws of the compressor dynamics. The present work aims at developing an artificial neural network (ANN) approach able to predict either the permanence of the system in stable working condition or the onset instabilities from a time sequence of the compressor dynamics. Different solutions were tried to find the most suitable model for identifying the system, as well as the effects of the duration of the time sequence on the accuracy of the predicted compressor working conditions. The network was further tried for sequences with different initial values in order to perform a system analysis that included multiple variations from the initial database. The results show how it is possible to identify with high accuracy both rotating stall and surge with the ANN approach. Moreover, the presence of an underlying fluid dynamic model shares some similarities with physically informed AI procedures.

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“…The rotor blade loading distribution affects the compressor stability, mainly in near-stall points [38]. Thus, to analyze the blade loading [39], the pressure coefficient (𝐶 ), can be determined along the blade chord by:…”

Section: Aerodynamic Parametersmentioning

confidence: 99%

Analysis of Blade Aspect Ratio Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Preprint

View full text Add to dashboard Cite

The ratio between blade height and chord, named aspect ratio (AR), plays an important role in compressor aerodynamic design. Once selected, it influences stage performance, blade losses, and the stage stability margin. The choice of the design AR involves both aerodynamic and mechanical considerations, and a reasonable aim is frequently to achieve a desired operating range while maximizing efficiency. For a fixed set of aerodynamic and geometric parameters there will be an optimal choice in AR that achieves a maximum efficiency. However, for a state-of-the-art aero-engine design optimality means multi-objective optimality, that is reaching the highest possible efficiency for a number of operating points while achieving a sufficient stability margin. To this end, the influence of the AR on the performance of the first rotor row of a multistage multi-objective high-speed compressor design is analyzed. A careful setup of the high-speed aerodynamic design problem allows the effect of the AR to be isolated. Close to the optimal AR, only a modest efficiency variation is observed, but a considerable change in compressor stability margin (SM) is noted. Decreasing the AR allows for an increasing efficiency, but at the expense of a reduced surge margin. This allows the designer to trade efficiency for stability. Increasing the AR, however, is shown to reduce both surge margin and efficiency, hence a distinct optimality in stability is observed for the analyzed rotor blade row. In this work, the optimality in surge margin with respect to AR is observed whereas a close to optimal efficiency. The predicted range from AR=1.10 to AR=1.64, is only indicative, considering that the definition of a multi-objective optimality requires balancing efficiency and surge margin and that the choice of balancing these two criteria requires making a design choice along a pareto optimal front.

show abstract

Effect of rotor axial blade loading distribution on compressor stability

Cited by 10 publications

References 31 publications

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

AI-Based Detection of Surge and Rotating Stall in Axial Compressors via Dynamic Model Parameter Estimation

Analysis of Blade Aspect Ratio Influence on High-Speed Axial Compressor Performance

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