Simulation and Design Tool for ORC Axial Turbine Stage

Talluri, Lorenzo; Lombardi, Giacomo

doi:10.1016/j.egypro.2017.09.154

Cited by 15 publications

(7 citation statements)

References 10 publications

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“…Macchi and Perdichizzi [3] Axial flow Fixed recovery a Lozza et al [5] Axial flow Fixed recovery a Da Lio et al [6] Axial flow Fixed recovery b Astolfi and Macchi [7] Axial flow Fixed recovery b Da Lio et al [8] Axial flow Fixed recovery b Al Jubori et al [9] Axial flow Not considered Talluri and Lombardi [10] Axial flow Not considered Tournier and El-Genk [11] Axial flow Not considered Meroni et al [12] Axial flow Not considered Meroni et al [13] Axial flow Not considered Meroni et al [14] Axial flow Fixed recovery b Perdichizzi and Lozza [15] Radial inflow Fixed recovery a Uusitalo et al [16] Radial inflow Not considered Rahbar et al [17] Radial inflow Not considered Da Lio et al [18] Radial inflow Not considered Pini et al [19] Radial outflow Fixed recovery a Casati et al [20] Radial outflow Fixed recovery a Bahamonde et al [4] Axial flow Radial inflow Radial outflow Not considered a Fixed recovery of the total kinetic energy. b Fixed recovery of the meridional kinetic energy.…”

Section: Reference Turbine Type Diffuser Modelingmentioning

confidence: 99%

One-Dimensional Annular Diffuser Model for Preliminary Turbomachinery Design

Agromayor

Müller

Nord

2019

IJTPP

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Annular diffusers are frequently used in turbomachinery applications to recover the discharge kinetic energy and increase the total-to-static isentropic efficiency. Despite its strong influence on turbomachinery performance, the diffuser is often neglected during the preliminary design. In this context, a one-dimensional flow model for annular diffusers that accounts for the impact of this component on turbomachinery performance was developed. The model allows use of arbitrary equations of state and to account for the effects of area change, heat transfer, and friction. The mathematical problem is formulated as an implicit system of ordinary differential equations that can be solved when the Mach number in the meridional direction is different than one. The model was verified against a reference case to assess that: (1) the stagnation enthalpy is conserved and (2) the entropy computation is consistent and it was found that the error of the numerical solution was always smaller than the prescribed integration tolerance. In addition, the model was validated against experimental data from the literature, finding that deviation between the predicted and measured pressure recovery coefficients was less than 2% when the best-fit skin friction coefficient is used. Finally, a sensitivity analysis was performed to investigate the influence of several input parameters on diffuser performance, concluding that: (1) the area ratio is not a suitable optimization variable because the pressure recovery coefficient increases asymptotically when this variable tends to infinity, (2) the diffuser should be designed with a positive mean wall cant angle to recover the tangential fraction of kinetic energy, (3) the mean wall cant angle is a critical design variable when the maximum axial length of the diffuser is constrained, and (4) the performance of the diffuser declines when the outlet hub-to-tip ratio of axial turbomachines is increased because the channel height is reduced.

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Section: Reference Turbine Type Diffuser Modelingmentioning

confidence: 99%

One-Dimensional Annular Diffuser Model for Preliminary Turbomachinery Design

Agromayor

Müller

Nord

2019

IJTPP

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“…The mean span wise velocity field is observed to be much more related to cross flow turbine's wake recovery. Guide lines for the design optimization of efficient high supersonic passages were also derived [18][19][20].…”

Section: Numerical Analysis Of Axial Flow Turbinementioning

confidence: 99%

The Numerical Simulation and Evaluation of Aircraft Engine Axial Flow Turbine using Numerical Techniques

al.¹

2019

IJMPERD

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This research aims to improve the efficiency of an axial flow turbine by improving the boundary conditions. In the baseline paper, Sherwood number, Nusselts number for a given flow were determined. The pressure ratio was not considered in the paper. Research has been done to improve the values by considering the pressure difference which was neglected in the base line paper. Axial flow turbines expand the flow passing through it. Losses like tip losses, efficiency losses and loss on blades due to heat are high and needs to be looked after. A comprehensive literature study was carried out for the better understanding of axial flow turbines, recent developments and to analyze the control of loses.

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“…Therefore, the selection and the design of the expander are of paramount importance. Axial turbines are widespread used for plants with power production between 500 kW and few MWs [16], while radial turbines are better suited for the lower power ranges (50-500 kW), due to their low degree of reaction and therefore their capability of dealing with large enthalpy drops at low peripheral speeds, allowing the adopting a single stage design [17][18][19]. Finally, for very small and micro power range applications (hW to about 50 kW), volumetric expanders, like scrolls or screws, are usually utilized, although their efficiency is limited by leakages, friction and heat transfer losses [20][21][22].…”

Section: Small Power Generationmentioning

confidence: 99%