The Development of a Deviation Model for Radial and Mixed-Flow Turbines for Use in Throughflow Calculations

Cox, Graham D.; Roberts, Alex; Casey, Michael

doi:10.1115/gt2009-59921

Cited by 2 publications

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“…The OFC results were compared with the NASA TN D-8164 report and verified by computational fluid dynamics (CFD) simulation. Cox et al [6] used a quasi-three dimensional throughflow method to design a radial turbine. They studied the loss structure and the flow rule of vortex in radial and mixed-flow turbines by CFD.…”

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Design and numerical simulation on coupled flow field of radial turbine with air-inlet volute

Wang

Chen

2015

Trans. Tianjin Univ.

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Abstract：As one of the core components of turbocharger or micro-turbine, radial turbine has the features of small size and high rotation speed. In order to explore the design method and flow mechanism of the turbine with a volute, a centimeter-scale radial turbine with a vaneless air-inlet volute was designed and simulated numerically to investigate the characteristics of the coupled flow field. The results show that the wheel efficiency of single passage computation without the volute is 80.1%. After accounting for the factors of the loss caused by the volute and the interaction between each passage, the performance is more accurate according to the whole flow passage computation with the volute. High load region gathers at the mid-span and the efficiency declines to 76.6%. The performance of the volute whose structure angle of the trapezoid section is equal to 70 degree is better. Unlike uniform inlet condition in single passage, more appropriate inlet flow for the impeller is provided by the rectification effect of the volute in full passage calculation. Flow parameters are distributed more evenly along the blade span and are generally consistent between each passage at the outlet of the turbine. Keywords：radial turbine; aerodynamic design; whole flow passage; air-inlet volute Radial turbine is an important working component for micro-turbine engine, turbocharger and turbopump [1,2] . It is widely used in aircraft and power applications, due to its reliability, high ratio of work to weight, low fuel consumption, compact structure and high efficiency with low flow rate [3,4] . However, the aerodynamic design of a radial turbine with a compatible volute still poses a lot of challenges because of its high inlet temperature and rotation speed, which influence the rotor structure integrity [5] .In recent years, research on radial turbines has become a hotspot in engine field in universities and research institutes all over the world. Carrillo et al [5] designed the nozzle and the radial inflow rotor for a 600 kW simple cycle gas turbine engine using onedimensional computer FORTRAN code (OFC). The OFC results were compared with the NASA TN D-8164 report and verified by computational fluid dynamics (CFD) simulation. Cox et al [6] used a quasi-three dimensional throughflow method to design a radial turbine. They studied the loss structure and the flow rule of vortex in radial and mixed-flow turbines by CFD. Epstein [7] developed a radial turbine with a rotor diameter of 4 mm, which adopted the deep reactive ion etching (DRIE) and wafer bonding technology. Ebaid et al [8] described a unified method to design a radial turbine at 60 000 r/min with the maximum power of 60 kW electrical output. The micro-turbine developed at Stanford is a radial-axial turbine with a rotor diameter of 12 mm, and the silicon nitride rotor was produced by gel-casting technique [9] . A large deflection blade design method was introduced by Tan et al [10] , and it has been extended to 3D flows and applied to radial turbine design by Zangene...

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Design and numerical simulation on coupled flow field of radial turbine with air-inlet volute

Wang

Chen

2015

Trans. Tianjin Univ.

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“…The description of the radial turbines operating in steady flows has been widely presented in the literature [1,2], together with an extensive description of the flow pattern, even for off-design conditions (e.g., in [3]). Some design processes have also been presented to ensure the good performance of the energy-recovering process of the stage (see [4,5]).…”

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Dynamic Response in Transient Operation of a Variable Geometry Turbine Stage: Influence of the Aerodynamic Performance

Binder

Benitez

Carbonneau

2013

International Journal of Rotating Machinery

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The transient response of a radial turbine stage with a variable geometry system is evaluated. Mainly, the consequences of the variations of the aerodynamic performance of the stage on the response time are checked. A simple quasi-steady model is derived in order to formalize the expected dependences. Then an experimental campaign is conducted: a brutal step in the feeding conditions of the stage is imposed, and the response time in terms of rotational speed is measured. This has been reproduced on different declinations of the same stage, through the variation of the stator geometry, and correlated to the steady-state performance of the initial and final operating points of the transient phase. The matching between theoretical expectation and results is surprisingly good for some configurations, less for others. The most important factor identified is the mass-flow level during the transient phase. It increases the reactivity, even far above the theoretical expectation for some configurations. For those cases, it is demonstrated that the quasi-steady approach may not be sufficient to explain how the transient response is set.

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The Development of a Deviation Model for Radial and Mixed-Flow Turbines for Use in Throughflow Calculations

Cited by 2 publications

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Design and numerical simulation on coupled flow field of radial turbine with air-inlet volute

Design and numerical simulation on coupled flow field of radial turbine with air-inlet volute

Dynamic Response in Transient Operation of a Variable Geometry Turbine Stage: Influence of the Aerodynamic Performance

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