Influence of Geometrical Parameters on Aerodynamic Optimization of a Mixed-Flow Turbocharger Turbine

Khairuddin, Uswah; Costall, Aaron; Martinez-Botas, Ricardo

doi:10.1115/gt2015-42053

Cited by 11 publications

(10 citation statements)

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“…This chapter discusses 3D-CFD simulation and optimization methodology of interstage ducts (ISD) and high pressure turbine (HPT) wheels of a two-stage heavy duty off road 4.4 litre Caterpillar engine. Some of the paragraphs and figures in this chapter are taken from proceedings written by the author in Khairuddin et al (2015) and Khairuddin and Costall (2017).…”

Section: Simulation Methodologymentioning

confidence: 99%

“…The performance of MFTA was mapped during this testing and a CFD simulation was carried out for this wheel as well. Various turbine wheel geometry optimization was tested on MFTA and a conference paper was produced out of this work and presented at the 2015 ASME Turbo Expo (Khairuddin et al, 2015).…”

Section: Turbocharger Aerodynamic Optimizationmentioning

confidence: 99%

“…Some of the paragraphs and figures in this section are taken from a proceeding written by the author (Khairuddin et al, 2015) where Khairuddin is the main author and all of the work published is her research work.…”

Section: Optimization Of a Mixed Flow Turbine Wheelmentioning

confidence: 99%

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Aerodynamic Optimization of the High Pressure Turbine and Interstage Duct in a Two-Stage Air System for a Heavy-Duty Diesel Engine

Khairuddin

Costall

2017

Journal of Engineering for Gas Turbines and Power

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Turbochargers reduce fuel consumption and CO2 emissions from heavy-duty internal combustion engines by enabling downsizing and downspeeding through greater power density. This requires greater pressure ratios and thus air systems with multiple stages and interconnecting ducting, all subject to tight packaging constraints. This paper considers the aerodynamic optimization of the exhaust side of a two-stage air system for a Caterpillar 4.4 l heavy-duty diesel engine, focusing on the high pressure turbine (HPT) wheel and interstage duct (ISD). Using current production designs as a baseline, a genetic algorithm (GA)-based aerodynamic optimization process was carried out separately for the wheel and duct components to evaluate seven key operating points. While efficiency was a clear choice of cost function for turbine wheel optimization, different objectives were explored for ISD optimization to assess their impact. Optimized designs are influenced by the engine operating point, so each design was evaluated at every other engine operating point, to determine which should be carried forward. Prototypes of the best compromise high pressure turbine wheel and ISD designs were manufactured and tested against the baseline to validate computational fluid dynamics (CFD) predictions. The best performing high pressure turbine design was predicted to show an efficiency improvement of 2.15% points, for on-design operation. Meanwhile, the optimized ISD contributed a 0.2% and 0.5% point efficiency increase for the HPT and low pressure turbine (LPT), respectively.

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Section: Simulation Methodologymentioning

confidence: 99%

Section: Turbocharger Aerodynamic Optimizationmentioning

confidence: 99%

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Aerodynamic Optimization of the High Pressure Turbine and Interstage Duct in a Two-Stage Air System for a Heavy-Duty Diesel Engine

Khairuddin

Costall

2017

Journal of Engineering for Gas Turbines and Power

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“…To study the limitations of ORC performance, Robertson et al applied the genetic algorithm to the turboexpander of the ORC system, aiming to optimize the geometry specification (radii, areas, blade heights, and angles) to provide maximal time‐averaged power output. Khairuddin et al used genetic algorithms to adjust the main features of the blade geometry—he hub, shroud, camber line, leading, and trailing edge profiles—to significantly improve the efficiency of the turboexpander. According to some scholars' research on impeller blades, this paper proposes to study and analyze the parameters of outlet diameter, blade angle, and meridian width of impeller blades, to improve the flow expansion acceleration in the impeller and the distribution of flow field parameters at impeller outlet.…”

Section: Introductionmentioning

confidence: 99%

Analysis of impeller blade parameters and tip clearance of turboexpander in organic Rankine cycle system

Jia

Wang

Zhang

et al. 2019

Energy Science & Engineering

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The optimization of a turboexpander can significantly improve the performance of the organic Rankine cycle (ORC) system, which can use in low‐temperature geothermal energy for high‐efficiency power generation. Therefore, this paper studies and optimizes the expander in the ORC of low‐temperature geothermal energy around 90°C. Firstly, the influence of impeller parameters on the performance of the expander is analyzed. Then, the grid is divided by the turbine mesh, and numerical simulation is performed by CFX. The gas state equation selects the Peng–Robinson equation, and the turbulence equation selects the SST model. Finally, the effect of tip clearance on the performance of the expander was studied. Research on impeller blade parameters shows that with the increase in the outer diameter of the impeller blade outlet, the isentropic efficiency of the expander decreases, and the output power increases. As the increase in the angle between the direction of the impeller blade and the meridian plane, the outlet velocity of the blade increases, the temperature decreases, and the efficiency and control of the turboexpander will decrease. The meridional section width has few effects on the performance of the expander. The study of the tip clearance by numerical simulation shows that the existence of tip clearance will cause clearance flow between pressure surface and suction surface that interferes with the mainstream direction. When the tip clearance increases from 0 mm to 1.2 mm, the efficiency of the expander is reduced by 8.9%.

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“…N Karamanis et al [15] investigated the steady and unsteady performances of a mixed-flow turbocharger turbine with a constant blade inlet angle. Uswah et al [16] optimized the hub and the shroud in order to increase the mixed inflow turbine efficiency.…”

Section: Introductionmentioning

confidence: 99%

Effects of Cone Angle and Inlet Blade Angle on Mixed Inflow Turbine Performances

Chelabi

Hamidou

Hamel

2017

Period. Polytech. Mech. Eng.

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The development of the aerofoil-shaped turbomachine blades is of prime importance for achieving the appropriate deflection of a three dimensional flow through desired angles, to work at the same degree of incidence and thereby providing the required performances for the specific machine. The sensitivity of the rotor to incidence effects and tendency of the flow to separate from one or the other blade surface have given rise to considerations of the optimum incidence angle and cone angle for a mixed inflow turbine by a numerical investigation using the ANSYS-CFX code. In order to keep the rotor in the same casing some geometrical parameters have been hold constant and the Bezier polynomial is used to generate the new shape of the rotor blade when changing the cone angle magnitude.

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Influence of Geometrical Parameters on Aerodynamic Optimization of a Mixed-Flow Turbocharger Turbine

Cited by 11 publications

References 0 publications

Aerodynamic Optimization of the High Pressure Turbine and Interstage Duct in a Two-Stage Air System for a Heavy-Duty Diesel Engine

Aerodynamic Optimization of the High Pressure Turbine and Interstage Duct in a Two-Stage Air System for a Heavy-Duty Diesel Engine

Analysis of impeller blade parameters and tip clearance of turboexpander in organic Rankine cycle system

Effects of Cone Angle and Inlet Blade Angle on Mixed Inflow Turbine Performances

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