CFD Validation and Analysis of a Single-Stage Axial Compressor

Xiang, Junting; Schlüter, Jörg; Duan, Fei

doi:10.4028/www.scientific.net/amm.629.109

Cited by 5 publications

(5 citation statements)

References 9 publications

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“…These settings are identical with previous validation study. 40 The adiabatic wall condition is applied throughout this MGT study. The operation speed is defined as 80 k, 100 k, and 117 k r/min, with varying mass flow rate ( M fr ) applied.…”

Section: Steady Rans Simulationmentioning

confidence: 99%

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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: Steady Rans Simulationmentioning

confidence: 99%

“…Boundary conditions are specified referring to the previous case study, 40 with adjustment made according to the KJ-66 MGT compressor design parameters. Figure 5 shows the specification of boundary conditions and each boundary type is highlighted in different colors.…”

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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“…Researchers from ETH Zurich have also tried to develop MGT as a portable power device [11]. The mini-jet group in NTU Singapore has investigated the performance of MGT for UAV application [12][13][14][15].…”

Section: Chapter 1 Introductionmentioning

confidence: 99%

“…14 shows the distribution of turbulent viscosity ῦ(kg/m•s) based on the primary surface, to quantify the intensity of turbulence at 5% span and 20% span from R ss , respectively. At 5% span, the turbulent viscosity remains zero during the first 40% chord length, indicating the flow is laminar in this region.…”

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confidence: 99%

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Miniature gas turbines : numerical study of the effects of miniaturization on the performance of compressor

Xiang¹

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Micro Gas Turbines (MGT) are an attractive choice for Unmanned Aerial Vehicles (UAV) and small-scale power generation. Compared with other propulsion systems, MGT have several advantages including high power-toweight ratio, availability for various fuels, endurance and others. However, the direct miniaturization of conventional gas turbines designed at large scales may induce performance loss. Therefore, the effects of miniaturization on gas turbines need to be investigated. In this research, an axial compressor in a gas turbine is studied, to understand the effects of the miniaturizing process. Using a numerical approach, parameter studies are conducted on three of the most important parameters during the miniaturizing process: the Reynolds number effect, the increased heat transfer and the tip clearance. The NASA Stage35 compressor is selected as the configuration in this study. Firstly, a thorough validation of the computational tools and methods is conducted, suggesting the suitability of the numerical methods for follow-up study. Then, the effect of Reynolds number is investigated, in the range of Re 2.14×10 5 to Re 8.54×10 5. Our results indicate a drop of performance with the decrease of Reynolds number, due to the increased viscous effect in boundary layer when compressor is miniaturized. Thereafter, the effect of heat transfer is investigated due to thermal conduction; adiabatic wall conditions, constant heat transfer coefficient conditions and isothermal conditions are applied, respectively. The results indicate that the increased heat transfer from internal flow to the ambient air will actually benefit compressor performance, but the heat transfer from the downstream combustor to the compressor has an adverse effect on compressor overall performance. Subsequently, the effect of tip clearance (TC) is investigated, with varying TC value and varying Reynolds number. Our results indicate that the existence of TC has an adverse effect on compressor performance, and the loss of performance amplifies during the miniaturization process.

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Numerical Investigations of Stall Development in a Transonic Axial Compressor Stage

et al. 2019

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CFD Validation and Analysis of a Single-Stage Axial Compressor

Cited by 5 publications

References 9 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

Miniature gas turbines : numerical study of the effects of miniaturization on the performance of compressor

Numerical Investigations of Stall Development in a Transonic Axial Compressor Stage

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