Aerodynamic performance effects of leading-edge geometry in gas-turbine blades

Hamakhan, Idres Azzat; Korakianitis, Theodosios

doi:10.1016/j.apenergy.2009.09.017

Cited by 48 publications

(19 citation statements)

References 31 publications

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“…On the other hand, in terms of surface curvature effects, researchers have shown that aerofoil boundary layer behaviour can be improved by making the curvature distribution of an aerofoil continuous and smooth [14,15]. The idea came originally from high-efficiency turbomachinery blade design, in which the distribution of surface curvature is an important factor [16,17].…”

Section: Introductionmentioning

confidence: 99%

Surface curvature effects on the tonal noise performance of a low Reynolds number aerofoil

et al. 2017

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This paper presents wind tunnel experiments to illustrate the effects of surface curvature on the aeroacoustic performance of airfoil E387. For the first time, surface curvature effects are considered in an investigation of the airfoil's self-noise. To distinguish the effects of surface curvature, the CIRCLE method is applied to the airfoil E387 to remove slope-of-curvature discontinuities and the redesigned airfoil is denoted A7. Anechoic wind tunnel tests were performed with E387 and A7 at three low Reynolds numbers to investigate aeroacoustic performance by measuring airfoil self-noise at different angles of attack (AoA) and spatial positions. At 2 • and 4 • AoA, A7 presents a tone with a reduced amplitude compared with E387 due to its improved slope-of-curvature distribution. It is concluded that improving surface curvature distribution improves airfoil aeroacoustic performance.

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Section: Introductionmentioning

confidence: 99%

Surface curvature effects on the tonal noise performance of a low Reynolds number aerofoil

et al. 2017

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“…The blades were divided into three sections (hub, tip and the mean effective diameter) and the velocity triangles were used to find the inlet angle and the twist on each section. The design procedure was developed as a MATLAB code that generates three-dimensional (3D) coordinates of the blade sections9–13.The profile and isometric view of a representative impeller with 2 blades and a 20° outlet angle is shown in Figure 1.…”

Section: Methodsmentioning

confidence: 99%

Optimization of Axial Pump Characteristic Dimensions and Induced Hemolysis for Mechanical Circulatory Support Devices

et al. 2018

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The application of axial pumps as ventricular assist devices (VADs) requires significant modifications to the size and characteristics of industrial pumps due to the difference in flow fields of industrial and medical pumps. Industrial pumps operate in the region of Reynolds number Re = 10, whereas axial blood pumps operate in Re < 10. The common pump design technique is to rely on the performance of previously designed pumps using the concept of fluid dynamic similarity. Such data are available for industrial pumps as specific speed-specific diameter (ns-ds) graphs. The difference between the flow fields of industrial and medical pumps makes the industrial ns-ds graphs unsuitable for medical pumps and consequently several clinically available axial blood pumps operate with low efficiencies. In this article, numerical and experimental techniques were used to design 62 axial pump impellers with different design characteristics suitable for VADs and mechanical circulatory support devices (MCSDs). The impellers were manufactured and experimentally tested in various operating conditions of flow, pressure, and rotational speed. The hemocompatibility of the impellers was numerically investigated by modeling shear stress and hemolysis. The highest efficiency of each pump impeller was plotted on an ns-ds diagram. The nondimensional results presented in this article enable preliminary design of efficient and hemocompatible axial flow pumps for VADs and MCSDs.

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“…The leading-edge separation bubble can influence the boundary layer development over the rest of the blade. Some specific studies have been directed at smoothening this geometric discontinuity [31,32]. In the present paper we ensured tangency continuity between the leading edge and the main blade profile.…”

Section: Variation Of Scaling Parameter and Heat Transfer With Leadinmentioning

confidence: 96%

Effect of leading-edge geometry on the aerodynamics and heat transfer in the stagnation region of uncooled turbine blades

Fenil

Sivapragasam

2018

Sādhanā

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The flow in the leading-edge stagnation region of uncooled turbine aerofoils is studied. The stagnation region is modelled based on the Hiemenz flow solution, following Holley and Langston (J. Turbomach. 130: 021001, 2008). These results are applied to the JT9D turbine blade and confirmed by computations. It is also shown that the heat transfer at the stagnation point is bounded by the Hiemenz flow and plane stagnation-point potential flow heat transfer solutions. The computations are further extended for a range of Reynolds numbers and freestream turbulence intensities. It is seen that for a wide range of these parameters considered in the present study and data collected from published literature, a majority of the data points are within these bounds. The leading-edge geometry of the JT9D turbine blade is modified with elliptical geometries. Blunter-leading-edge geometries have lower values of heat transfer at the stagnation region; however, their blade profile loss coefficients are higher. The off-design performance characteristics of the turbine blades are also computed. The results presented in this paper will be useful in designing leading-edge geometries for reduced heat transfer in the stagnation region of uncooled turbine blades.

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Aerodynamic performance effects of leading-edge geometry in gas-turbine blades

Cited by 48 publications

References 31 publications

Surface curvature effects on the tonal noise performance of a low Reynolds number aerofoil

Surface curvature effects on the tonal noise performance of a low Reynolds number aerofoil

Optimization of Axial Pump Characteristic Dimensions and Induced Hemolysis for Mechanical Circulatory Support Devices

Effect of leading-edge geometry on the aerodynamics and heat transfer in the stagnation region of uncooled turbine blades

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