A data-driven non-intrusive polynomial chaos for performance impact of high subsonic compressor cascades with stagger angle and profile errors

Guo, Zhengtao; Chu, Wuli; Zhang, Haoguang

doi:10.1016/j.ast.2022.107802

Cited by 22 publications

(12 citation statements)

References 42 publications

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“…Therefore, in this work, the response surface-based NIPC method is chosen to calculate the polynomial coefficients. The detailed derivation process of the surface-based NIPC method is described in Guo et al (2022). In reference to previous relevant studies, this work selects the fifth-order NIPC method for UQ analysis.…”

Section: Uncertainty Quantification Methodsmentioning

confidence: 99%

“…Based on the requirements for various types of geometric tolerances of the compressor rotor blades as specified by Guo et al (2022), Table 1 presents the distribution ranges of different geometric deviations considered in this work.…”

Section: Nominal Blade and Sample Blade Constructionmentioning

confidence: 99%

“…In this work, the rotor blades of a subsonic compressor are chosen as the research object. Referring to the requirements of the blade geometric parameter tolerances introduced by Guo et al (2022), a total of 200 sample blades are generated uniformly in the spatial domain using the Halton sequence. Using the NIPC method as the UQ approach, this work investigates the uncertainty impact of suction surface thickness deviation, pressure surface thickness deviation, leading edge radius deviation, trailing edge radius deviation, chord length deviation, stagger angle deviation and blade tip clearance deviation on the compressor stability.…”

Section: Introductionmentioning

confidence: 99%

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Uncertainty quantification of blade geometric deviation on compressor stability

Ji,

Chu

2023

AEAT

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Purpose The geometric parameters of the compressor blade have a noteworthy influence on compressor stability, which should be meticulously designed. However, machining inaccuracies cause the blade geometric parameters to deviate from the ideal design, and the geometric deviation exhibits high randomness. Therefore, the purpose of this study is to quantify the uncertainty and analyze the sensitivity of the impact of blade geometric deviation on compressor stability. Design/methodology/approach In this work, the influence of blade geometric deviation is analyzed based on a subsonic compressor rotor stage, and three-dimensional numerical simulations are used to compute samples with different geometric features. A method of combining Halton sequence and non-intrusive polynomial chaos is adopted to carry out uncertainty quantitative analysis. Sobol’ index and Spearman correlation coefficient are used to analysis the sensitivity and correlation between compressor stability and blade geometric deviation, respectively. Findings The results show that the compressor stability is most sensitive to the tip clearance deviation, whereas deviations in the leading edge radius, trailing edge radius and chord length have minimal impact on the compressor stability. And, the effects of various blade geometric deviations on the compressor stability are basically independent and linearly superimposed. Originality/value This work provided a new approach for uncertainty quantification in compressor stability analysis. The conclusions obtained in this work provide some reference value for the manufacturing and maintenance of rotor blades.

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Section: Uncertainty Quantification Methodsmentioning

confidence: 99%

Section: Nominal Blade and Sample Blade Constructionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Uncertainty quantification of blade geometric deviation on compressor stability

Ji,

Chu

2023

AEAT

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“…Although the deviations of various geometric parameters on the blade are very small, the aerodynamic performance changes caused by the machining deviations cannot be ignored. 2 Through a large number of experimental studies, Pratt & Whitney found that the geometric deviation from 0.0254 mm to 0.0762 mm in certain areas can have a significant impact on the aerodynamic performance and service life of a large fan blade. 3 Roberts 4 found that the change of airfoil caused by blade wear leads to worse blade performance and an increase in engine fuel consumption.…”

Section: Introductionmentioning

confidence: 99%

“…Although the deviations of various geometric parameters on the blade are very small, the aerodynamic performance changes caused by the machining deviations cannot be ignored. 2…”

Section: Introductionmentioning

confidence: 99%

Mechanism analysis and uncertainty quantification of blade thickness deviation on rotor performance

Chu

Chen

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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The blade thickness distribution is an important geometric parameter of a compressor rotor blade. It determines the aerodynamic performance of a rotor, which should be carefully designed. However, the manufacturing inaccuracies cause the blade thickness distribution to deviate from the ideal design. These geometric deviations alter the flow field near the blade surface, which affects the aerodynamic performance of the rotor. Therefore, it is of great significance to quantitatively investigate the effects of blade thickness deviation on the aerodynamic performance. In this paper, the influence of blade thickness deviation on the flow field is analyzed based on a transonic compressor rotor, and an uncertainty quantification process is performed to study the effects of blade thickness deviation on the aerodynamic performance. Cases with different geometry features are checked in the current study using 3-dimensional Reynolds-averaged Navier–Stokes simulations. Results show that the blade thickness deviation leads to changes in the intensities of the expansion wave in the upper part of the blade suction and the passage shock wave, which affects the supercharging process of the rotor. The influence of thickness deviation on the strength of the tip leakage vortex changes the isentropic efficiency of the rotor. The results of the uncertainty quantitative analysis indicate that the linear correlation between the variation of rotor performance and the thickness deviation is strong when the machining accuracy is high, whereas the linear correlation between the two is weakened when the tolerance range is larger.

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Multi-condition Robust Optimization Design of High Subsonic Cascades Considering the Uncertain Changes of Inlet Flow Condition

Wuan,

Jiang,

et al. 2024

2023 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2023) Proceedings

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A data-driven non-intrusive polynomial chaos for performance impact of high subsonic compressor cascades with stagger angle and profile errors

Cited by 22 publications

References 42 publications

Uncertainty quantification of blade geometric deviation on compressor stability

Uncertainty quantification of blade geometric deviation on compressor stability

Mechanism analysis and uncertainty quantification of blade thickness deviation on rotor performance

Multi-condition Robust Optimization Design of High Subsonic Cascades Considering the Uncertain Changes of Inlet Flow Condition

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