Cooling the Tip of a Turbine Blade Using Pressure Side Holes—Part I:
                    Adiabatic Effectiveness Measurements

Christophel, J. R.; Thole, Karen A.; Cunha, F. J.

doi:10.1115/1.1812320

Cited by 37 publications

(7 citation statements)

References 10 publications

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“…Quite a few high-pressure turbines have cooling holes on the near-tip region of the pressure side. Christophel et al [13,14] studied the cooling effectiveness, the heat-transfer coefficient, and the NHFR for this configuration. The coolant ejected from the dust holes near the leading edge of the blade tip effectively improved the thermal performance near the leading edge of the tip.…”

mentioning

confidence: 99%

Thermal Performance of Different Cooled Tips in A High-Pressure Turbine Cascade

Zhou

Hodson

Lock

2012

Journal of Propulsion and Power

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The thermal performance of the three turbine tips was investigated. The results are presented in terms of heattransfer coefficient (h), cooling effectiveness (), net heat-flux reduction (NHFR), and heat load. The calculations were performed using a cooled flat tip, a cooled cavity tip, and a cooled suction-side squealer tip in a cascade at a tip gap of 1.6%C. The results were validated using experimental data where possible. For an uncooled flat tip, the fluid dynamics are dominated by flow separation at the pressure-side edge. A significant benefit of ejecting coolant inside this separation bubble is shown. At the coolant mass-flow ratio M c 0:52%, both the cooled flat tip and the cooled cavity tip are well-protected by the coolant. For the cooled suction-side squealer tip, the coolant lifts off from the tip floor and leads to not only low cooling effectiveness, but also to high heat-transfer coefficients. The effects of the coolant mass-flow ratio on the thermal performance of the tip were presented. The effects of end-wall motion on the thermal performance of the blade tip are found to be small in the current study.

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mentioning

confidence: 99%

Thermal Performance of Different Cooled Tips in A High-Pressure Turbine Cascade

Zhou

Hodson

Lock

2012

Journal of Propulsion and Power

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“…The way to provide acceptable cooling of the blade tips is to extract some cooling air from various coolant passages, to protect the tip surface from the hot leakage gas [10]. The performance of cooling holes placed along the pressure side tip was good for a small tip gap when compared to a large tip gap [11]. An overall benefit to the tip obtained by releasing coolant from the pressure side holes [12].…”

Section: Problem Statement and Methodologymentioning

confidence: 99%

Heat Transfer Analysis of Gas Turbine Blade by Varying Number of Cooling Holes and at Suitable Coolant Speeds Using CFD

Basavaraju¹,

Kaleru²,

Chintireddy³

2021

IJHT

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In the present work, heat transfer analysis of a gas turbine blade consisting of 5, 7, and 10 holes, coolant flowing with suitable velocities 40 m/s, 75 m/s, and 110 m/s. From the results of several investigations, the suitable velocity ranges of coolant fluid have been taken. The coolant fluid used in this work is air, as it is suitable for aircraft engines working on open cycle gas turbines, and of course, it is cheaply available, and the blade material used is Inconel 718. Simulations are carried out using Computational Fluid Dynamics (CFD) software, ANSYS FLUENT 14.5. An analysis is being done on how the temperature is varying in blade with different configurations. Temperature distribution in the blade is studied and variation of different parameters like velocity, Nusselt number, heat transfer coefficient is observed. It is found that the blade cooling is maximum in the case of a blade with 10 holes and coolant inlet velocity 110 m/s. The average Nusselt number with the coolant inlet velocity of 40 m/s, 75 m/s, and 110 m/s is around 11, 19, and 21, respectively. The lowest temperature attained by the blade on the coolant inlet surface is 1152 K and the coolant exit surface is 1334 K. These two temperatures are observed when the blade has 10 cooling holes and coolant inlet velocity is 110 m/s.

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“…More recently, Kwak and Han (2003a,b) and Christophel et al (2005) used thermal imaging techniques (Liquid crystal and IR thermography respectively) to measure detailed film cooling effectiveness contours on the tip with holes on the tip region of the pressure side and on the tip. The effect squealer tips (used to inhibit tip leakage) on film cooling was also studied.…”

Section: Blade Tip Film Coolingmentioning

confidence: 99%

Turbine Blade Film Cooling Using PSP Technique

Han¹,

Rallabandi²

2010

Frontiers in Heat and Mass Transfer

191

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Film cooling is widely used to protect modern gas turbine blades and vanes from the ever increasing inlet temperatures. Film cooling involves a very complex turbulent flow-field, the characterization of which is necessary for reliable and economical design. Several experimental studies have focused on gas turbine blade, vane and end-wall film cooling over the past few decades. Measurements of heat transfer coefficients, film cooling effectiveness values and heat flux ratios using several different experimental methods have been reported. The emphasis of this current review is on the Pressure Sensitive Paint (PSP) mass transfer analogy to determine the film cooling effectiveness. The theoretical basis of the method is presented in detail. Important results in the open literature obtained using the PSP method are presented, discussing parametric effects of blowing ratio, momentum ratio, density ratio, hole shape, surface geometry, free-stream turbulence on flat plates, turbine blades, vanes and end-walls. The PSP method provides very high resolution contours of film cooling effectiveness, without being subject to the conduction error in high thermal gradient regions near the hole.

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Cooling the Tip of a Turbine Blade Using Pressure Side Holes—Part I: Adiabatic Effectiveness Measurements

Cited by 37 publications

References 10 publications

Thermal Performance of Different Cooled Tips in A High-Pressure Turbine Cascade

Thermal Performance of Different Cooled Tips in A High-Pressure Turbine Cascade

Heat Transfer Analysis of Gas Turbine Blade by Varying Number of Cooling Holes and at Suitable Coolant Speeds Using CFD

Turbine Blade Film Cooling Using PSP Technique

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