Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine: Part 1 — Experimental Results

Bunker, Ronald S.; Bailey, Jeremy C.; Ameri, Ali

doi:10.1115/99-gt-169

Cited by 144 publications

(46 citation statements)

References 26 publications

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“…Bunker et al [2] presented detailed tip heat transfer measurements. They observed that reduced tip clearances can reduce heat transfer and located areas of high heat transfer.…”

mentioning

confidence: 99%

Aerothermal Performance of Shroudless Turbine Blade Tips with Relative Casing Movement Effects

Virdi¹,

Zhang²,

He³

et al. 2015

Journal of Propulsion and Power

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“…Bunker et al [2] presented detailed tip heat transfer measurements. They observed that reduced tip clearances can reduce heat transfer and located areas of high heat transfer.…”

mentioning

confidence: 99%

Aerothermal Performance of Shroudless Turbine Blade Tips with Relative Casing Movement Effects

Virdi¹,

Zhang²,

He³

et al. 2015

Journal of Propulsion and Power

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“…The experimental setup and conditions are similar to those described in [3]. In that paper the pressure distribution and tip heat transfer for both a sharp edge tip and radiused edge tip of the present blade geometry were presented.…”

Section: The Experimental Setupmentioning

confidence: 91%

“…This has spurred experimental work on measuring tip heat transfer for various blade tip treatments on stationary cascades and has provided data for numerical simulations. In a previous numerical study [2] the predicted tip heat transfer for a sharp edge tip and a radiused tip (blade tip with a rounded edge around the perimeter of the blade tip) was compared with the measured experimental data of Bunker et al [3]. The data was, at the time, the only set of liquid crystal measurements of tip heat transfer.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped With a Mean-Camberline Strip

Ameri¹

2001

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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Experimental and computational studies have been performed to investigate the detailed distribution of convective heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines(>100MW). In a previous work the numerical heat transfer results for a sharp edge blade tip and a radiused blade tip were presented. More recently several other tip treatments have been considered for which the tip heat transfer has been measured and documented. This paper is concerned with the numerical prediction of the tip surface heat transfer for radiused blade tip equipped with mean-camberline strip (or “squealer” as it is often called). The heat transfer results are compared with the experimental results and discussed. The effectiveness of the mean-camberline strip in reducing the tip leakage and the tip heat transfer as compared to a radiused edge tip and sharp edge tip was studied. The calculations show that the sharp edge tip works best (among the cases considered) in reducing the tip leakage flow and the tip heat transfer.

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“…This so-called "sweet spot" has been observed by Bunker et al [22], whose study was conducted at flow conditions of exit Mach 0.75 with varying turbulent intensities of five and nine percent. In the present study, the "sweet spot" region is larger for the lower tip gap cases of 0.9%.…”

Section: Flow Visualizationmentioning

confidence: 93%

Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer

Anto

Xue

et al. 2013

Volume 3C: Heat Transfer

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It is important to be able to accurately predict the heat transfer distribution over a component when designing the turbine section of an engine. The gas temperature exiting the combustor in many gas turbine engines is above the melting temperature of turbine components. These high gas temperatures can quickly degrade components and cause failure. A detailed heat transfer study on these turbine components is an important input when developing ways to cool them. One such important component is the gas turbine blade, which primarily extracts the energy from the hot combustion gases. To allow for rotation of the blades, a gap exists between the stationary casing and the rotating blades. Unfortunately, leakage flow from the blade pressure side to the suction side dramatically increases the heat load on and around the blade tip surfaces.The objective of this work is to present the heat transfer distribution on the tip and neartip region of a turbine blade under transonic conditions. Tests were performed at a high inlet freestream turbulence level (Tu = 12%). This work seeks to investigate the effects of tip clearance gap and Mach number on heat transfer on and near the blade tip. Thin film heat flux gages that allow for high frequency measurements are used to obtain the heat transfer distribution on the near tip pressure and suction sides. An infrared thermography technique is used to obtain the heat transfer distribution on the blade tip surface.iii PrefaceIn order to get more energy from gas turbine engines, the temperature of the combustion products is continually being increased by designers. These high temperatures will lead to increased degradation of turbine blades unless effective cooling schemes are developed to help protect the blades. A thorough understanding of the heat transfer distribution on the gas turbine blades is essential before sound cooling techniques can be implemented. An especially fragile part of the turbine blade exposed to high heat transfer is the blade tip. The tip gap, between the casing and the blade tip, is where leakage flow escapes from the blade pressure side to the suction side. This leakage flow has been shown to significantly increase the heat load on the blade tip. Designers need to understand the heat transfer distribution, especially on the blade tip, and then subsequently devise the appropriate cooling mechanisms. This study examines the effects of tip clearance gap and exit Reynolds number on the heat transfer distribution on a turbine blade tip and near-tip region.This thesis is organized into two sections that include one research paper that concisely documents the central thrust of this study. The author was primarily responsible for most aspects of the research project from initial test section design to analyzing data. A colleague, Xue Song, was responsible for the post processing of some of the blade tip heat transfer results. The title of the research paper coincides with the title of this thesis. A series of appendices then follow which provide additional in...

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Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine: Part 1 — Experimental Results

Cited by 144 publications

References 26 publications

Aerothermal Performance of Shroudless Turbine Blade Tips with Relative Casing Movement Effects

Aerothermal Performance of Shroudless Turbine Blade Tips with Relative Casing Movement Effects

Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped With a Mean-Camberline Strip

Effects of Tip Clearance Gap and Exit Mach Number on Turbine Blade Tip and Near-Tip Heat Transfer

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