Effects of Tip Clearance on Miniature Gas Turbines Compressor Performance: A Numerical Approach

Xiang, Junting; Schlüter, Jörg; Duan, Fei

doi:10.2514/6.2015-2412

Cited by 3 publications

(3 citation statements)

References 12 publications

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“…Tip clearance is not considered currently to simplify our analysis. Although previous study indicates tip clearance flow leads to performance loss, especially for MGT, 39 the current study does not count in this effect to simplify our benchmark investigation. Further examination regarding this particular issue will be proposed and addressed in our follow-up study.…”

Section: Numerical Approach Setupmentioning

confidence: 99%

Study of KJ-66 micro gas turbine compressor: Steady and unsteady Reynolds-averaged Navier–Stokes approach

Xiang

Schlüter

Duan

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Numerical study on the compressor stage of a KJ-66 micro gas turbine was conducted in this paper through both steady and unsteady Reynolds-averaged Navier-Stokes. The study was conducted for the numerical prediction of micro gas turbine compressor performance at various operation conditions, with special attention given to the transient flow behaviors during compressor operation. The numerical results showed reasonable agreements with experimental data while providing predictions for the charting of compressor performance map at various operation speeds. The simulation results indicated that the increase of operation speed from 80 k r/min to 117 k r/min would leads to an increased peak total pressure ratio from 1.54 to 1.96, while decreasing the peak adiabatic efficiency from 0.73 to 0.55. This paper also provided discussion on details of transient flow field within the compressor stage as well as demonstrated the smooth flow transition through rotor-stator interactions.

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Section: Numerical Approach Setupmentioning

confidence: 99%

Study of KJ-66 micro gas turbine compressor: Steady and unsteady Reynolds-averaged Navier–Stokes approach

Xiang

Schlüter

Duan

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

Self Cite

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“…Kim et al 3 found that a blade is subjected to centrifugal force, resulting in a reduction in tip clearance, which increases the efficiency of the compressor. Xiang et al 4 showed that compressor performance deteriorates with the existence of tip clearance and the performance loss increases with a large tip clearance. Mao and Liu 5 studied the TLV in a dual-stage counter-rotating axial compressor and found that the variation clearance size of a Rotor 2 tip had almost no influence on the performance of Rotor 1, while the variation of Rotor 1 tip clearance affected the performance of Rotor 2.…”

Section: Introductionmentioning

confidence: 99%

Effect of circumferential static pressure nonuniformity caused by volute on tip leakage flow in a centrifugal compressor

Yang

Bao

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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For a centrifugal compressor with volute, the flow field is circumferentially nonuniform because of the volute asymmetrical structure and leads to a circumferential difference in the tip leakage flow. In this work, the compressor performance and the casing wall static pressure distribution are measured, and the results are compared with the time-averaged results of the unsteady calculation to verify the reliability of the simulation. The results show a relationship between the tip leakage vortex trajectory and the high static pressure region in the diffuser, based on which a prediction model is established for the reverse propagation of pressure waves caused by a volute tongue. Influenced by the volute asymmetric structure, the trajectory, shape, and strength of the tip leakage vortex at different circumferential positions differs significantly. The tip leakage vortex trajectory affected by the high static pressure is more inclined to a circumferential direction because the tip leakage flow velocity flowing out of the suction surface is reduced, and the tip leakage flow with low velocity is subjected to the high-pressure gradient in a passage. Moreover, the tip leakage vortex breakdown in different passages differs significantly. A tip leakage vortex core more inclined towards the streamwise direction is more likely to break down than a tip leakage vortex core inclined towards the circumferential direction because of the larger reverse pressure gradient.

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“…This is caused by the strong change in direction which the flow has to perform and the high pressure ratio per stage; this leads to a strong interaction between main flow and leakage flow in the tip gap region, with the creation of complex vortexes. For this reason, the study of tip gap influence on both performance and flow field is interesting and it has been widely analysed in literature by several works ([3] [4] [5]). This paper aims to relate performance and internal aerodynamics, investigating the machines flow fields to corroborate the global parameters variation (e.g.…”

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confidence: 99%

Design of a Centrifugal Compressor for Micro Gas Turbine: Investigation of Scaling and Tip Clearance Effects

Barsi¹,

Bottino²,

Perrone³

et al. 2019

OJFD

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The aim of this paper is to investigate the design in similarity of a centrifugal compressor for micro gas turbine and the related scaling effects on performance using CFD investigations. This work is part of a research project carried out by the Department DIME of the University of Genova, with the purpose of investigating the performance of a micro gas turbine in the change from 100 kW electrical output to 250 kW, while maintaining the compressor pressure ratio and geometry in similarity. The first part of the work focuses on the comparison between the original and the scaled machine, while the second part of the study deeply investigates the tip gap effect in the new configuration. The aim is to provide information about the performance of the compressor designed in geometrical similarity and to evaluate the tip gap height impact. From the efficiency point of view, the scaled-up machine has higher efficiency (up to 1.4% increment in design conditions) keeping the same technological limit for impeller manufacturing. However, the variation of tip gap height in the range 0 ÷ 1 mm strongly affects this parameter, leading to 10% alteration in design conditions between the ideal and worst case. The results, both in terms of overall performance and flow fields, are widely discussed in order to obtain simple yet reliable correlation for preliminary design.

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Effects of Tip Clearance on Miniature Gas Turbines Compressor Performance: A Numerical Approach

Cited by 3 publications

References 12 publications

Study of KJ-66 micro gas turbine compressor: Steady and unsteady Reynolds-averaged Navier–Stokes approach

Study of KJ-66 micro gas turbine compressor: Steady and unsteady Reynolds-averaged Navier–Stokes approach

Effect of circumferential static pressure nonuniformity caused by volute on tip leakage flow in a centrifugal compressor

Design of a Centrifugal Compressor for Micro Gas Turbine: Investigation of Scaling and Tip Clearance Effects

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