Investigation on heat transfer of a rotor blade tip with various film cooling holes arrangements and groove depths

Tong, Fujuan; Gou, Wenxuan; Li, Lei; Liu, Qingchang; Yue, Zhufeng; Xie, Gongnan

doi:10.1177/1687814014568499

Cited by 10 publications

(8 citation statements)

References 44 publications

(37 reference statements)

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“…Wang et al 10 concluded that increasing squealer width can reduce the velocity of leakage flow and the size of separation vortex, then reduce overall heat transfer processes. The research work of Tong et al 11 also showed that tip averaged HTC decreased with the increase of the squealer height. Bunker et al 12 tested and analyzed the influence of the squealer height on tip heat transfer processes.…”

Section: Introductionmentioning

confidence: 86%

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Aerothermal and aerodynamic performance of turbine blade squealer tip under the influence of guide vane passing wake

Zhang

Qiang

2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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In this paper, the performance of the turbine blade squealer tip has been studied detailed aimed to highlight the impact of the upstream guide vane passing wake. The first stage of GE-E3 high-pressure turbine has been employed to perform the three-dimensional simulation and the computational domain has been scaled based on the domain scaling method. Boundary conditions are consistent with operating conditions of the annular cascade testing. Circumferential averaged and realistic non-uniform interface conditions have been used to obtain steady and unsteady characteristics respectively. The validation of the turbulent model and mesh independent test has been conducted detailed in previous work. Three squealer tips, including two widths and heights, have been designed and investigated to understand its influence. Results show that the aerothermal performance of the squealer tip is remarkably influenced by the upstream passing wake. Although steady and time-averaged results have a good agreement, the variation of instantaneous heat transfer coefficient (HTC) would be over 30%, especially on the Cavity Floor region. Changing the geometry of the squealer also has different impacts on both steady and unsteady performance. The unsteady aerodynamic has relatively small fluctuation within 10%, and the distribution of steady and time-averaged leakage flow as well as total pressure loss coefficient still have a satisfactory agreement.

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Section: Introductionmentioning

confidence: 86%

“…The research work of Tong et al. 11 also showed that tip averaged HTC decreased with the increase of the squealer height. Bunker et al.…”

Section: Introductionmentioning

confidence: 86%

Aerothermal and aerodynamic performance of turbine blade squealer tip under the influence of guide vane passing wake

Zhang

Qiang

2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…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%

Section: Introductionmentioning

confidence: 99%

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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“…Film cooling is typically applied to turbine engines, 1 where cooling air is exhausted through small holes drilled into the blade, 2,3 which can have a higher turbine inlet temperature to improve the turbine performance. Moreover, in rocket engines, 4 film cooling can be used alone or in combination with regenerative cooling to protect the thruster wall.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of supersonic film cooling in a rearward-facing slot

Chen

Shen

2017

Advances in Mechanical Engineering

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Supersonic film cooling tangentially ejected through a half Laval nozzle set in a backward-facing slot was numerically simulated to investigate the structures of flowfield and the mechanisms of heat transfer after the slot. In particular, changes in flowfield near the turning point in the cooling effectiveness curve were studied. The turning point is defined by extrapolation of the cooling effectiveness curve using a power-law relationship. The point corresponds to the streamwise position where the hot mainstream is reaching the wall protected by the film coolant and to the disappearance of the unsmooth transition points in streamwise velocity profiles, where the growth rate of velocity in wall normal direction changes gradually from one state to another. The transition of velocity becomes smooth downstream of the turning point. The unsmooth transition point also exists in other profiles of flow parameters, such as the mole fraction of film gas and the total temperature of the fluid, which are indicators of the mixing extent between the mainstream and film coolants. Moreover, the unsmooth transition point is more evident in the film coolant of nitrogen than that of helium due to the slower drop rate of effectiveness in the current configuration of the supersonic film cooling.

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Investigation on heat transfer of a rotor blade tip with various film cooling holes arrangements and groove depths

Cited by 10 publications

References 44 publications

Aerothermal and aerodynamic performance of turbine blade squealer tip under the influence of guide vane passing wake

Aerothermal and aerodynamic performance of turbine blade squealer tip under the influence of guide vane passing wake

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

Numerical simulation of supersonic film cooling in a rearward-facing slot

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