Navier-Stokes analysis of radial turbine rotor performance

Larosiliere, Louis M.

doi:10.2514/6.1993-2555

Cited by 2 publications

(2 citation statements)

References 11 publications

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“…In the present study, the supercritical air is employed to reduce site area and increase the energy density of CAES system, 16 so the compressed air in the multistage radial turbine expands from supercritical to atmospheric conditions to obtain higher output power, which differs from the ordinary operating condition of radial turbines (Figure 1). [16][17][18][19][20][21][22][23] In addition, radial turbines, which are shrouded and unshrouded rotors with different blade profile, are all included in the multistage radial inflow turbine to meet the requirement of operation condition, thus it is difficult for the engineers to determine the stage that has higher flow loss to conduct performance improvement. Although some studies 24 has been conducted on the aerodynamic performance and internal flow patterns of multistage radial inflow turbine, the effects of supercritical condition and geometric parameters on the aerodynamic performance and flow characteristic of multistage radial turbine in CAES system is also still not revealed.…”

Section: Introductionmentioning

confidence: 99%

Flow characteristic of a multistage radial turbine for supercritical compressed air energy storage system

Wang

Zhang

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part A:

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Compressed air in supercritical compressed air energy storage system expand from supercritical to atmospheric conditions at lower inlet temperature (<500 K) to generate MW scale power. Therefore, a new multistage radial turbine is adopted and the flow characteristic is investigated by numerical simulation. Effects of ideal gas model and tip clearance on the performance and flow field of the multistage turbine are revealed. Results show that ideal gas model can reveal flow pattern under supercritical condition correctly while leading to obvious deviation of isentropic enthalpy drop, entropy, and inlet-to-exit total temperature ratio. Relative differences for mass flow and efficiency are less than 2%, while the relative differences for output power reaches to 9.36%. For shrouded rotor, mixing of working fluid near hub, blade suction surface, and shroud is the main influencing factor of the flow loss in the rotor. For unshrouded rotor, leakage vortex promote mixture of the fluid deriving from the hub, shroud, and suction surface, and causes much higher flow loss in the channel of rotor. The rotors, which have higher blade height variation rate, present higher efficiency reduction when the tip clearance height is increased, which is because the proportion of tip clearance in blade inlet height increases with the increase of average aspect ratio, resulting in the increase of leakage flow at the leading edge of rotor blade. The pressure fluctuation near the tip clearance and efficiency reduction is also increased. The present study provides a reference for further design and optimization of the multistage radial turbines in compressed air energy storage.

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Section: Introductionmentioning

confidence: 99%

Flow characteristic of a multistage radial turbine for supercritical compressed air energy storage system

Wang

Zhang

et al. 2017

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…A similar conclusion was also drawn by Tirres 8 when he predicted the performance of the solid version of a cooled radial rotor, and it was shown that the backface clearance loss for the rotor accounted for 79% of the total clearance losses. Larosiliere 9 simulated the backface clearance flow in a deeply scalloped radial turbine. The author presented entropy contours and velocity vectors at different quasi-normal planes, and showed the backface clearance leakage vortex.…”

Section: Introductionmentioning

confidence: 99%

Investigation of clearance flows in deeply scalloped radial turbines

Sun

Zhang

et al. 2012

Proceedings of the Institution of Mechanical Engineers, Part A:

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The tip clearance, backface clearance, and backface cavity clearance flows in deeply scalloped radial turbines are numerically investigated in this article. The secondary flow structures in the rotor passage with the three clearance flows are shown and their influences on the distribution of aerodynamic parameters at the rotor outlet are analyzed. It is found that the migration of the tip clearance flow is constrained near the tip corner, and the region influenced by the tip clearance flow is mainly located at the upper span. With the largest mass flow rate, the tip clearance flow has the greatest impact on the outlet parameters among the three clearance flows. The backface clearance flow enters the mainstream from the blade backface and migrates toward the blade tip due to the centrifugal force. And it mainly affects the distribution of outlet parameters at the mid-span. The backface cavity clearance flow is injected into the mainstream from the disc rim. It moves toward the blade tip and stays close to the suction surface. With the smallest mass flow rate, the impact of the backface cavity clearance flow on the outlet parameters is the lowest.

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Navier-Stokes analysis of radial turbine rotor performance

Cited by 2 publications

References 11 publications

Flow characteristic of a multistage radial turbine for supercritical compressed air energy storage system

Flow characteristic of a multistage radial turbine for supercritical compressed air energy storage system

Investigation of clearance flows in deeply scalloped radial turbines

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