The Experts below are selected from a list of 6801 Experts worldwide ranked by ideXlab platform
Hua Ouyang - One of the best experts on this subject based on the ideXlab platform.
-
internal flow mechanism and experimental research of low pressure axial fan with forward skewed Blades
Journal of Hydrodynamics, 2008Co-Authors: Jie Liu, Hua OuyangAbstract:This article presents the flow mechanism analysis and experimental study of a forward-skewed impeller and a Radial impeller in low pressure axial fan. The forward-skewed Blade was obtained by the optimization design of the Radial Blade and CFD technique. Measurement of the two Blades was carried out in aerodynamic and aeroacoustic performance. Compared to the Radial Blade, the forward-skewed Blade has demonstrated the improvements in efficiency, total pressure ratio, Stable Operating Range (SOR) and less aerodynamic noise. Detailed flow measurement and computation were performed for outlet flow field for investigating the responsible flow mechanisms. The results show the forward-skewed Blade can cause a spanwise redistribution of flow toward the Blade mid-span and reduce tip loading. This results in reduced significantly total pressure loss near hub and shroud endwall region, despite the slight increase of total pressure loss at mid-span.
-
experimental research on aerodynamic performance and exit flow field of low pressure axial flow fan with circumferential skewed Blades
Journal of Hydrodynamics, 2007Co-Authors: L I Yang, Hua Ouyang, D U ZhaohuiAbstract:In this article, the low pressure axial flow fan with circumferential skewed rotor Blade, including the Radial Blade, the forward-skewed Blade and the backward-skewed Blade, was studied with experimental methods. The aerodynamic performance of the rotors was measured. At the design condition at outlet of the rotors, detailed flow measurements were performed with a five-hole probe and a Hot-Wire Anemometer (HWA). The results show that compared to the Radial rotor, the forward-skewed rotor demonstrates a wider Stable Operating Range (SOR), is able to reduce the total pressure loss in the hub region and make main loading of Blade accumulating in the mid-span region. There is a wider wake in the upper mid-span region of the forward-skewed rotor. Compared to the Radial rotor, in the backward-skewed rotor there is higher total pressure loss near the hub and shroud regions and lower loss in the mid-span region. In addition, the velocity deficit in the wake is lower at mid-span of the backward-skewed rotor than the forward-skewed rotor.
Janos Vad - One of the best experts on this subject based on the ideXlab platform.
-
aerodynamic effects of Blade sweep and skew in low speed axial flow rotors at the design flow rate an overview
Proceedings of the Institution of Mechanical Engineers Part A: Journal of Power and Energy, 2008Co-Authors: Janos VadAbstract:AbstractA detailed literature survey is presented herein in order to overview the aerodynamic impact of non-Radial Blade stacking techniques applied to axial flow fan and compressor rotors. The literature suggests a consensus that forward Blade sweep and skew provides a means for the following advantages in the part load operational range of low-speed axial flow turbofan and compressor rotors: improvement of efficiency and performance, and extension of stall-free operating range. However, the published research results are rather diversified regarding the judgment of performance and loss modifying effects of sweep and skew at the design point. The current paper summarizes the major aerodynamic phenomena related to such Blade stacking techniques, in order to contribute to a general reasoning of performance and efficiency modification at the design flow rate. Furthermore, it provides guidelines how to consider these phenomena in tailoring the Blade geometry for potential efficiency gain and for achievement ...
D U Zhaohui - One of the best experts on this subject based on the ideXlab platform.
-
experimental research on aerodynamic performance and exit flow field of low pressure axial flow fan with circumferential skewed Blades
Journal of Hydrodynamics, 2007Co-Authors: L I Yang, Hua Ouyang, D U ZhaohuiAbstract:In this article, the low pressure axial flow fan with circumferential skewed rotor Blade, including the Radial Blade, the forward-skewed Blade and the backward-skewed Blade, was studied with experimental methods. The aerodynamic performance of the rotors was measured. At the design condition at outlet of the rotors, detailed flow measurements were performed with a five-hole probe and a Hot-Wire Anemometer (HWA). The results show that compared to the Radial rotor, the forward-skewed rotor demonstrates a wider Stable Operating Range (SOR), is able to reduce the total pressure loss in the hub region and make main loading of Blade accumulating in the mid-span region. There is a wider wake in the upper mid-span region of the forward-skewed rotor. Compared to the Radial rotor, in the backward-skewed rotor there is higher total pressure loss near the hub and shroud regions and lower loss in the mid-span region. In addition, the velocity deficit in the wake is lower at mid-span of the backward-skewed rotor than the forward-skewed rotor.
Tianyu Pan - One of the best experts on this subject based on the ideXlab platform.
-
Effects of the Radial Blade loading distribution and B parameter on the type of flow instability in a low-speed axial compressor
Chinese Journal of Aeronautics, 2018Co-Authors: Qiushi Li, Simin Li, Tianyu PanAbstract:Previous studies showed that an axisymmetric hub-initiated disturbance defined as partial surge may initiate the stall of a transonic compressor; to reveal the instability evolution under full-span incompressible flow for different levels of hub loading and B parameter, an experimental investigation is conducted on a single-stage low-speed compressor. Experimental results show that under a uniform inflow condition without inlet flow distortion, a modal-type stall inception dominates in this low-speed compressor. When an inlet screen introducing hub distortion is used to increase the hub loading, a compressor stall is initiated by a modal wave, but large disturbances are present in the hub region before the compressor stall, which become stronger as the hub loading increases. Under high hub loading and large B parameter (implemented by adding hub distortion through an inlet screen and enlarging the outlet plenum volume, respectively), a compressor stall is triggered by an axisymmetric hub-initiated disturbance, which is much different from the modal-like disturbances. The beginning of this axisymmetric disturbance may be captured over 800 rotor revolutions prior to the onset of stall, and the amplitude grows with time. The disturbance is hub-initiated because the disturbance signal at the hub is detected much earlier than that at the tip; meanwhile, the frequency of this axisymmetric disturbance changes with the length of the inlet duct. The characteristics of instability evolution in the low-speed compressor are also compared with those in a transonic compressor.
Jie Liu - One of the best experts on this subject based on the ideXlab platform.
-
internal flow mechanism and experimental research of low pressure axial fan with forward skewed Blades
Journal of Hydrodynamics, 2008Co-Authors: Jie Liu, Hua OuyangAbstract:This article presents the flow mechanism analysis and experimental study of a forward-skewed impeller and a Radial impeller in low pressure axial fan. The forward-skewed Blade was obtained by the optimization design of the Radial Blade and CFD technique. Measurement of the two Blades was carried out in aerodynamic and aeroacoustic performance. Compared to the Radial Blade, the forward-skewed Blade has demonstrated the improvements in efficiency, total pressure ratio, Stable Operating Range (SOR) and less aerodynamic noise. Detailed flow measurement and computation were performed for outlet flow field for investigating the responsible flow mechanisms. The results show the forward-skewed Blade can cause a spanwise redistribution of flow toward the Blade mid-span and reduce tip loading. This results in reduced significantly total pressure loss near hub and shroud endwall region, despite the slight increase of total pressure loss at mid-span.
