Numerical simulation on film cooling with compound angle of blade leading edge model for gas turbine

Gao, Wenjing; Yue, Zhufeng; Li, Lei; Zhao, Zhenan; Tong, Fujuan

doi:10.1016/j.ijheatmasstransfer.2017.07.105

Cited by 39 publications

(3 citation statements)

References 30 publications

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“…The commercial software ANSYS ICEM CFD v.14 has been used to generate the mesh of computational domains. The schematic of geometry shows that the computational models are complex, so the unstructured grids have been generated (Acharya and Moreaux, 2014;Gao et al, 2017;Yang et al 2002). The prism elements are meshed near the interfaces between the fluid and solid domains (e.g.…”

Section: Grid Independence Studymentioning

confidence: 99%

“…They found that the cavity squealer tip can weaken the TLV effectively, and the mutation of mass-averaged aerodynamic loss of the cavity squealer tip is smaller than that of the plane tip with the increment of height-to-chord ratio. Tong et al (2015Tong et al ( , 2018 and Gao et al (2017) also concluded that the groove depth of squealer tip can influence the TLF. The optimum value of groove depth is about 2.5 percent of the blade span, and the larger or smaller value is not good for the blade tip flow.…”

Section: Introductionmentioning

confidence: 97%

“…Tong et al . (2015, 2018) and Gao et al . (2017) also concluded that the groove depth of squealer tip can influence the TLF.…”

Section: Introductionmentioning

confidence: 98%

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Numerical investigation of high pressure turbine blade tip-shaping effects on the aerothermal and dynamic performance

Tong¹,

Gou²,

Li³

et al. 2019

MMMS

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Purpose In order to improve the engine reliability and efficiency, an effective way is to reform the turbine blade tip conformation. The paper aims to discuss this issue. Design/methodology/approach The present research provides several novel tip-shaping structures, which are considered to control the blade tip loss. Four different tip geometries have been studied: flat tip, squealer tip, flat tip with streamwise ribs and squealer tip with streamwise ribs. The tip heat transfer and leakage flow are both analyzed in detail, for example the tip heat transfer coefficient, tip flow and local pressure distributions. Findings The results show that the squealer seal and streamwise rib can reduce the tip heat transfer and leakage loss, especially for the squealer tip with streamwise ribs. The tip and near-tip flow patterns at the different locations of axial chord reflect that both the squealer seal and streamwise rib structure can control the tip leakage flow loss. In addition, the analysis of the aerodynamic parameters (the static pressure and turbine efficiency) also indicates that the squealer tip with streamwise ribs obtains the highest adiabatic efficiency with an increase of 2.34 percent, compared with that of the flat tip case. Originality/value The analysis of aerothermal and dynamic performance can provide a reference for the blade tip design and treatment.

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Section: Grid Independence Studymentioning

confidence: 99%