Conjugate heat transfer investigation on the cooling performance of air cooled turbine blade with thermal barrier coating

Ji, Yongbin; Ma, Chao; Ge, Bing; Zang, Shusheng

doi:10.1007/s11630-016-0867-6

Cited by 13 publications

(8 citation statements)

References 11 publications

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“…The kv-SST turbulence model, which is widely used and verified in the field of the turbo machinery, was adopted. 14,15 In this model, the mainstream inlet has mass flow rate and temperature boundary conditions, and the outlet is set to area averaged static pressure. The coolant inlet also sets mass flow rate and temperature boundary.…”

Section: Numerical Modelmentioning

confidence: 99%

Effect of jet flow on cooling performance and thermal stress of a radial turbine back disc

Zhu

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part D:

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In view of the development status of high-reliability and low-cost cooling technology for radial turbine of micro-gas turbine or vehicle turbocharger, the impingement cooling technology of the radial turbine back disc was proposed, and the improvement of the cooling efficiency and thermal stress of the turbine back disc was numerically simulated. The results show that the impingement cooling technology can greatly improve the cooling efficiency of the turbine back disc and reduce the stress level. When the relative cooling flow is 1.0%–3.0%, the average cooling efficiency of the lower part of the turbine back disc is increased by 258%–486% compared with no cooling, which can reduce the thermal stress at the fillet of the back disc by 140–216 MPa. Both the average cooling efficiency and the fillet stress of the back disc increase slightly as the relative position of the jet hole moves outward. When the relative cooling flow is controlled within 2.0%, the effect of this cooling technology on the performance of the turbine can be ignored.

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Section: Numerical Modelmentioning

confidence: 99%

Effect of jet flow on cooling performance and thermal stress of a radial turbine back disc

Zhu

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part D:

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“…CFX ® 16.0 was applied to solve Reynolds-averaged Navier–Stokes equations and shear-stress transport (SST) two-equation turbulence model which has been extensively used in the studies of turbomachinery. 15,19,20 The computational model of the turbine included turbine housing, the full 360° channel of the rotor, and the backdisc cavity and solid regions of the turbine. Frozen-rotor method was employed at the rotor–stator (housing) interface.…”

Section: Numerical Model and Verificationmentioning

confidence: 99%

Conjugate heat transfer study of backdisc cooling of a radial turbine

Lü

Wenjiao³

2020

Proceedings of the Institution of Mechanical Engineers, Part D:

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Radial turbines used in turbochargers and micro-turbines are subjected to high inlet temperature. This creates high thermal stress in the turbines, and possible creep of turbine inducer blades, and can reduce turbines’ reliability. With the ever-stringent engine emission regulations and the continuous drive for engine power density, turbine inlet temperature is significantly increased recently and the risk of thermo-mechanical failure of turbine rotor is heightened. To solve this problem, an innovative turbine cooling method is proposed by injecting a small amount of compressor or intercooler discharge air onto the upper backdisc region of turbine rotor to cool the disc and the inducer blades. A conjugate heat transfer simulation was carried out to investigate the effects of this cooling method with a turbocharger turbine. Flow conditions and geometric configurations were investigated for their influences on the cooling effectiveness of the method. The results show that using the compressor discharger air after intercooler with only 0.5–2.0% of turbine mass flow, the averaged cooling efficiency of the turbine backdisc is promoted by 23–43%; only four to six jets may be needed to cool the entire backdisc; and turbine efficiency is reduced by less than 1% point.

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“…ANSYS-CFX 16.0 was used to solve the full three-dimensional N-S equations. An SST-kω two-equation turbulence model, which has been widely tested and verified for use with turbines, was selected for the turbulence model [10,16,17]. A frozen-rotor method was used to process the data transfer between the turbine channel domain and the turbo wheel channel domain.…”

Section: Numerical Modelmentioning

confidence: 99%

The influence of a radial turbine volute on back-disk impingement cooling performance

Lü

Wenjiao³

2020

J Braz. Soc. Mech. Sci. Eng.

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Due to the restricted size of micro-gas turbines, the difficulty of cooling their radial turbines and raising their inlet temperature has been an ongoing focus in their research. In this paper, a back-disk impingement cooling technology for radial turbines is proposed. The study focuses on the influence of the non-uniform circumferential flow field generated by radial turbine volutes on the back-disk's cooling characteristics. The study was carried out by using a conjugated heat transfer numerical simulation method. The results showed that the circumferential non-uniform distribution of the flow field caused by the volute can significantly impact the relative distribution of cooling efficiency across the surface of the back-disk and can decrease the average cooling efficiency of the back-disk surface by 1.8-6.0% in comparison with when the flow field is uniform. Back-disk jet cooling reduces the efficiency of a turbine and, if the volute is generating a non-uniform flow field, this further decreases the turbine's efficiency. It was found, however, that the influence of back-disk jet cooling on the expansion ratio of the turbine can be ignored.

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Conjugate heat transfer investigation on the cooling performance of air cooled turbine blade with thermal barrier coating

Cited by 13 publications

References 11 publications

Effect of jet flow on cooling performance and thermal stress of a radial turbine back disc

Effect of jet flow on cooling performance and thermal stress of a radial turbine back disc

Conjugate heat transfer study of backdisc cooling of a radial turbine

The influence of a radial turbine volute on back-disk impingement cooling performance

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