Effects of rim location, rim height, and tip clearance on the tip and near tip region heat transfer of a gas turbine blade

Kwak, Jae Su; Ahn, Jae-Hyun; Han, Je-Chin

doi:10.1016/j.ijheatmasstransfer.2004.07.029

Cited by 66 publications

(20 citation statements)

References 32 publications

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“…The effects of squealer geometry on the thermal performance of the cavity tip have been investigated in several previous studies with a stationary endwall, e.g. Kwak [8]. Above study shows that the flow physics within the tip gap is quite different for a cavity tip with a moving endwall.…”

Section: Resultsmentioning

confidence: 84%

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Effects of endwall motion on thermal performance of cavity tips with different squealer width and height

Zhou

2015

International Journal of Heat and Mass Transfer

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Section: Resultsmentioning

confidence: 84%

“…Azad et al [7] studied the heat transfer and blade pressure in a linear cascade with a stationary endwall. In the same cascade, Kwak et al [8] studied the effects of the height of the squealer on the thermal performance of the cavity tip. In an engine, the casing endwall moves relative to the blade tips.…”

Section: Introductionmentioning

confidence: 99%

Effects of endwall motion on thermal performance of cavity tips with different squealer width and height

Zhou

2015

International Journal of Heat and Mass Transfer

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“…Papa et al [15] experimentally studied the average and local mass transfer coefficients on tip blade using the naphthalene sublimation technique. Kwak and Han [16] experimentally studied the effects of the rim height and the tip gap clearance on the tip heat transfer coefficients. They found that the higher rims reduce the heat transfer coefficients on the blade tip and shroud but had a weak influence on the reduction on the pressure and suction sides.…”

Section: Introductionmentioning

confidence: 99%

Influence of Different Rim Widths and Blowing Ratios on Film Cooling Characteristics for a Blade Tip

Wang

Sundén

Zeng³

et al. 2012

Journal of Heat Transfer

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Three-dimensional simulations of the squealer tip on the GE-E 3 blade with eight film cooling holes were carried out. The effect of the rim width and the blowing ratio on the blade tip flow and cooling performance were revealed. Numerical simulations were performed to predict the leakage flow and the tip heat transfer with the k-e model. For the squealer tip, the depth of the cavity is fixed but the rim width varies to form a wide cavity, which can decrease the coolant momentum and the tip leakage flow velocity. This cavity contributes to the improvement of the cooling effect in the tip zone. To investigate the influence on the tip heat transfer by the rim width, numerical simulations were performed as a two-part study: (1) unequal rim width study on the pressure side and the suction side and (2) equal rim width study with rim widths of 0.58%, 1.16%, and 1.74% of the axial chord (0.5 mm, 1 mm, and 1.5 mm, respectively) on both the pressure side rim and the suction side rim. With different rim widths, the effect of different global blowing ratios, i.e., M ¼ 0.5, 1.0 and 1.5, was investigated. It is found that the total heat transfer rate is increasing and the heat transfer rates on the rim surface (RS) rapidly ascend with increasing rim width.

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“…Distinct blade tip configurations -including full and partial, suction rim -were investigated in terms of heat transfer by Kwak et al [8]. The campaign continued in reference [9] with a more thorough analysis of the effects of rim height and tip clearance using the full and partial squealer geometries -similar to the one in the present contribution. According to this study, the suctionside squealer geometry yielded lower heat transfer rates on the blade tip and near tip regions, than the full squealer one.…”

Section: Literature Surveymentioning

confidence: 98%

Numerical investigation of high-pressure turbine blade tip flows: analysis of aerodynamics

Vass

Arts

2011

Proceedings of the Institution of Mechanical Engineers, Part A:

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The current contribution reports on the validation and analysis of three-dimensional computational results of the flow around four distinct high-pressure turbine blade tip geometries (TG1, 2, 3, and 4 hereinafter), taking into account the effect of the entire internal cooling setup inside the blade, at design exit Mach number: M ¼ 0.8, and high exit Reynolds number: Re C ¼ 900 000. Three of the four geometries represent different tip design solutions -TG1: full squealer rim; TG2: single squealer on the suction side; TG3: partial suction and pressure side squealer, and one (TG4) models TG1 in worn condition. This article provides a comparison between the different geometries from the aerodynamic point of view, analyses the losses, and evaluates the distinct design solutions. An assessment of the effect of the uneven rubbing of the blade tip was performed as well.TG1 was found to be the top performer followed by TG3 and TG2. According to the investigations, the effect of rubbing increased the kinetic loss coefficient by 10-15 per cent.

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Effects of rim location, rim height, and tip clearance on the tip and near tip region heat transfer of a gas turbine blade

Cited by 66 publications

References 32 publications

Effects of endwall motion on thermal performance of cavity tips with different squealer width and height

Effects of endwall motion on thermal performance of cavity tips with different squealer width and height

Influence of Different Rim Widths and Blowing Ratios on Film Cooling Characteristics for a Blade Tip

Numerical investigation of high-pressure turbine blade tip flows: analysis of aerodynamics

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