.... , 132 ( 4 ), p. 041015 . 10.1115/1.3148479 [3] Mito , R. , and Yamashita , S. , 2019 , “ Prediction of Rotating Stall During Startup for Axial Compressors ,” ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition , Phoenix, AZ , June 17–21 , p. V02AT39A028. [4...

...Yangwei Liu; Weibo Zhong; Yumeng Tang Blade end slots have been proven to be an effective method to suppress corner separation, thereby improving the aerodynamic performance of the compressor. The unsteady effects of blade end slots affiliated with a highly loaded compressor cascade on corner...

... Gas Turbine Institute (IGTI) of ASME for publication in the J ournal of T urbomachinery . 15 08 2024 04 10 2024 04 10 2024 13 01 2025 computational fluid dynamics (CFD) fan compressor and turbine aerodynamic design European Commission 10.13039/501100000780...

... for publication in the J ournal of T urbomachinery . 29 07 2024 02 11 2024 04 11 2024 20 12 2024 Graphical Abstract Figure boundary layer development losses turbine aerodynamic design fan compressor and turbine aerodynamic design Engineering and Physical...

... 2024 fan compressor and turbine aerodynamic design Beihang University 10.13039/501100002358 the Academic Excellence Foundation of BUAA for PhD Students Fan-stage rotor–stator interaction noise has been a major noise source for turbofan aircraft engines, which are wildly...

... of high-fidelity scale-resolving simulations. We use this data to construct energy budgets for a variety of mid-span compressor cases with varying Reynolds numbers and inflow turbulence intensities. This allows us to systematically assess the impact of inflow conditions on loss prediction when using...

.... The optimizer is surrogate model-based and can handle constraints. The developed methods are then applied to a compressor test case of a high pressure compressor blade row with 9 uncertainty and 24 design parameters of the geometry. The 2.5% quantile of the stage efficiency is used as a robustness measure...

...Zhenhao Jing; Yedidia Neumeier; J. V. R. Prasad; Darrell K. James This article presents results from a comprehensive sensitivity analysis focused on loss models used in a recently developed compressor unsteady mean line flow model for a transonic axial-centrifugal compressor. The mean line flow...

... by the International Gas Turbine Institute (IGTI) of ASME for publication in the J ournal of T urbomachinery . 20 08 2024 23 09 2024 23 09 2024 25 10 2024 aeromechanical instabilities fan compressor and turbine aerodynamic design Flutter bite (as shown in Fig. 1 ) is a fan...

... compressor and turbine aerodynamic design National Natural Science Foundation of China 10.13039/501100001809 52376021 Natural Science Foundation of Jiangxi Province 10.13039/501100004479 20242BAB26008 As design specifications for turbomachinery continue to evolve, the need...

...), and resulting evaluation time. This article discusses a framework for designing axial compressors and its application to the aeromechanical optimization of a high-speed compressor rotor. The design environment integrates geometry parametrization, a modular evaluation with different levels of fidelity...

... Graphical Abstract Figure compressor supersonic through-flow variable-pitch tandem fan CFD transonic flow supersonic flow computational fluid dynamics (CFD) fan compressor and compressor aerodynamic design fluid dynamics and heat transfer phenomena in compressor and turbine components...

... compressor computations, this paper maps efficiency as a function of mean-line aerodynamics, and determines the governing loss mechanisms. An open-source turbomachinery design code creates annulus and blade geometry, then runs a Reynolds-averaged Navier–Stokes simulation for compressors sampled from the mean...

... , X. , 2013 , “ Experimental Study of Surge Precursors in a High-Speed Multistage Compressor ,” ASME J. Turbomach. , 135 ( 6 ), p. 061018 . 10.1115/1.4023462 [3] Vo , H. D. , Tan , C. S. , and Greitzer , E. M. , 2008 , “ Criteria for Spike Initiated Rotating Stall ,” ASME...

... compressor and turbine aerodynamic design fluid dynamics and heat transfer phenomena in compressor and turbine components of gas turbine engines References [1] Liepmann , H. W. , 1946 , “ The Interaction Between Boundary Layer and Shock Waves in Transonic Flow ,” J. Aeronaut. Sci...

...Jichao Li; Yang Liu; Feng Peng; Hongwu Zhang Adaptive stability control is experimentally implemented in a single-stage axial flow compressor subjected to rotating inlet distortion. Stall margin variations are examined as a function of the distorted area and rotational speed. A critical minimum...

.... 10.1115/GT2020-15479 [5] Mårtensson , H. , 2021 , “ Harmonic Forcing From Distortion in a Boundary Layer Ingesting Fan ,” Aerospace , 8 ( 3 ), p. 58 . 10.3390/aerospace8030058 [6] Tyler , J. M. , and Sofrin , T. G. , 1962 , “ Axial Flow Compressor Noise Studies ”, SAE...

...Laura McLaughlin; Stephen Spence; Daniel Rusch; Charles Stuart; Marco Geron; Kwok Kai So; Magnus Fischer Often, an improvement in performance at one operating point in a compressor/turbine operating map will lead to a reduction in performance at another area. For example, improving the efficiency...

... of secondary flow phenomena. This article experimentally investigates the secondary flow effects in the 3D-optimized shrouded stator of the TUDa-GLR-OpenStage, representative of a transonic high-pressure compressor front stage, and its susceptibility to typical hub leakage flows. The impact of stator hub...

...Helmut Sauer; Martin Lange A group of unsteady flow phenomena in turbomachinery is often referred to as “rotating instabilities.” They occur at flow conditions with very asymmetric velocity profiles, as found downstream of blade rows in axial compressors with large rotor tip clearance in stable...