Experimental investigation of a supersonic micro turbine running with hexamethyldisiloxane

Andreas, P Weiß; Hauer, Josef; Popp, Tobias; Preißinger, Markus

doi:10.1063/1.5004384

Cited by 4 publications

(2 citation statements)

References 1 publication

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“…It should be noted that the one-dimensional calculations showed that the total-to-static efficiency of the axial-flow turbine was 68%, whereas it was 73.4% in three-dimensional CFD calculations and this latter value was consistent with the experimental results. 13 In Weiß et al, 14 the authors presented the experimental and numerical research results of a 6 kWe (49 000 rpm) single-stage axial-flow impulse turbine with a permanent magnet generator. They state that compared with reaction radial-flow turbines, this turbine can operate with unlimited pressure ratio coefficients with a lower nominal rotational speed and can be designed as a partial admission turbine (with no pressure drop on the rotor blades)-such a solution can be implemented in virtually every small turbine.…”

Section: Introductionmentioning

confidence: 99%

Design and investigation of a partial admission radial 2.5‐kW organic Rankine cycle micro‐turbine

et al. 2020

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In recent years, organic Rankine cycle (ORC) micro-turbine distributed energy systems have become increasingly popular. Design methods for this type of fluid-flow machinery are still being developed. In this paper, a 2.5-kW radialflow four-stage ORC micro-turbine with HFE7100 is experimentally and numerically analysed. CFX ANSYS was used for the numerical analysis as well as a computational fluid dynamics (CFD) in-house code based on finite volume discretisation with Godunov-type upwind differencing, a high-resolution essentially non-oscillatory (ENO) scheme and a turbulence model with twoequation shear stress transport (SST). The experimental stand and measurements are described. The numerical results are compared with experimental ones and prove to be satisfactory. The developed micro-turbine does not require the use of any traditional lubricant (oil-free technology) because the bearings are lubricated with the vapour of the low-boiling HFE7100. The developed micro-turbine is an innovative solution providing maintenance-free operation and high durability with low friction losses. The experimental studies have also confirmed a considerable reduction in noise and vibration levels.

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Section: Introductionmentioning

confidence: 99%

Design and investigation of a partial admission radial 2.5‐kW organic Rankine cycle micro‐turbine

et al. 2020

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“…Small-scaled turbines are usually applied for the propulsion drive in these cases. Smallscaled turbines of interest usually have single stage supersonic impulse design (see, e.g., Kunte and Seume (2013), Weiß et al (2017)) thanks to its simplicity and low cost. However, pressure shocks appearance, unexpected flow separation regions, high leakages due to high Mach numbers (see fig.1a) and high relative clearances lead to comparably low efficiency of such turbines.…”

Section: Introductionmentioning

confidence: 99%

Effects of hub endwall geometry and rotor leading edge shape on performance of supersonic axial impulse turbine. Part II: Method validation and final results.

Sebelev

Smirnov

Боровков

et al. 2019

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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The present paper continues the investigation started in Part I. The basic turbine stage remains the same as in Part I (an axial turbine stage with axisymmetric nozzles and mean diameter 103.5 mm). The numerical simulation method used in Part I was corrected by adding analytical correlation for disc friction losses. This approach was validated on the base of the experimental data for a geometrically close turbine. Variation of the radial velocity component at the rotor inlet was proposed as a new modification compared with Part I. The mathematical formulations of the rotor blade sweep and radial velocity component at the rotor inlet were proposed. The new modifications of the baseline were provided to establish the effects of the rotor blade sweep, velocity radial component at the rotor inlet and hub endwall contouring separately. The using of backward swept rotor blades together with the positive cinematic lean provided efficiency increasing up to 2.9% at the design conditions. It was also established that absence of a velocity radial component at the rotor inlet in the model with backward swept blades leads decreasing of the turbine performance. Axisymmetric hub contouring provided up to 1.9% efficiency growth at the part-load operation.

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Experimental characterization and comparison of an axial and a cantilever micro-turbine for small-scale Organic Rankine Cycle

Weiß¹,

Popp²,

Müller³

et al. 2018

Applied Thermal Engineering

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Experimental investigation of a supersonic micro turbine running with hexamethyldisiloxane

Cited by 4 publications

References 1 publication

Design and investigation of a partial admission radial 2.5‐kW organic Rankine cycle micro‐turbine

Design and investigation of a partial admission radial 2.5‐kW organic Rankine cycle micro‐turbine

Effects of hub endwall geometry and rotor leading edge shape on performance of supersonic axial impulse turbine. Part II: Method validation and final results.

Experimental characterization and comparison of an axial and a cantilever micro-turbine for small-scale Organic Rankine Cycle

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