.... 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...

... data on axial compressor rotor test objects in a controlled manner. The test facility is built as a closed loop and thus enables operation at variable pressure levels ranging from near-vacuum to overpressure and with different operating media. Overall damping test data are acquired at controlled...

... by a turbine vane frame (TVF), an S-shaped duct with turning struts and splitters, and a shrouded counter-rotating LP rotor. The inlet temperature of the rig can be adjusted between 40 °C and 185 °C by cooling the air from the compressor station. The air enters the rig through the mixing chamber and passes...

... region close to the tip, known as belly, as an effective method of extending the operating range of low-speed axial compressor rotors. In the literature, circumferential grooves are another well-described technique for improving the stable working range of a compressor rotor. No research has been...

... of the 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit , Indianapolis, IN , July 5–10 p. 3790 . [3] Cumpsty , N. A. , 2004 , Compressor Aerodynamics , Krieger , Malabar, FL . [4] Denton , J. D. , 1993 , “ IGTI Scholar Lecture: Loss Mechanisms in Turbomachines...

...Giuliano Agati; Paolo Venturini; Serena Gabriele; Franco Rispoli; Domenico Borello One of the main reasons for gas turbines’ performance losses is the deposition of dirt on the compressor blades. Dirt deposit has to be periodically removed to keep the engine performance as high as possible...

... Turbine Institute (IGTI) of ASME for publication in the J ournal of T urbomachinery . 23 08 2023 06 11 2023 06 11 2023 16 01 2024 boundary layer development computational fluid dynamics (CFD) fan compressor turbine aerodynamic design To transform global air...