Conjugate Heat Transfer Study of Combined Impingement and Showerhead Film Cooling Near NGV Leading Edge

Chandran, Dileep; Prasad, B. V. S. S. S.

doi:10.1155/2015/315036

Cited by 15 publications

(13 citation statements)

References 13 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The κ−ω SST model was adopted as the turbulence model in this study. The computational model was validated by comparing the spanwise averaged coefficient of pressure distribution on the vane obtained computationally with the experiment carried out by Chandran and Prasad [ 31 ]. Figure 5 indicates that a good correspondence exists between the experimental and computational results, thereby validating the computational methodology, including the mesh and the turbulence model adopted for the computations.…”

Section: Methodsmentioning

confidence: 99%

Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

Mei

Zou

et al. 2019

Entropy

View full text Add to dashboard Cite

Numerical calculation of conjugate heat transfer was carried out to study the effect of combined film and swirl cooling at the leading edge of a gas turbine vane with a cooling chamber inside. Two cooling chambers (C1 and C2 cases) were specially designed to generate swirl in the chamber, which could enhance overall cooling effectiveness at the leading edge. A simple cooling chamber (C0 case) was designed as a baseline. The effects of different cooling chambers were studied. Compared with the C0 case, the cooling chamber in the C1 case consists of a front cavity and a back cavity and two cavities are connected by a passage on the pressure side to improve the overall cooling effectiveness of the vane. The area-averaged overall cooling effectiveness of the leading edge () was improved by approximately 57%. Based on the C1 case, the passage along the vane was divided into nine segments in the C2 case to enhance the cooling effectiveness at the leading edge, and was enhanced by 75% compared with that in the C0 case. Additionally, the cooling efficiency on the pressure side was improved significantly by using swirl-cooling chambers. Pressure loss in the C2 and C1 cases was larger than that in the C0 case.

show abstract

Section: Methodsmentioning

confidence: 99%

Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

Mei

Zou

et al. 2019

Entropy

View full text Add to dashboard Cite

show abstract

“…Several authors have used multiple surface thermocouples to calibrate IR surface temperature measurements on filmed-cooled NGVs in the absence of airfoil endwall film cooling e.g. [2]- [4]. Multiple calibration thermocouples have also been used to improve temperature measurements on cooled endwall surfaces e.g.…”

Section: Past Studies and Present Contributionsmentioning

confidence: 99%

The Effects of Combustor Cooling Features on Nozzle Guide Vane Film Cooling Experiments

Holgate

Ireland

Romero

2018

Volume 5C: Heat Transfer

View full text Add to dashboard Cite

Recent advances in experimental methods have allowed researchers to study nozzle guide vane film cooling in the presence of combustor dilution ports and endwall films. The dilution injection creates nonuniformities in temperature, velocity, and turbulence, and an understanding of the vane film cooling performance is complicated by competing influences. In this study, dilution port temperature profiles have been measured in the absence of vane film cooling and compared to film effectiveness measurements in the presence of both films and dilution, illustrating the effects of the dilution port turbulence on film cooling performance. It is found that dilution port injection can create significant effectiveness benefits at the difficult-to-cool vane stagnation region, due to the more turbulent hot mainstream enhancing the mixing of film coolant jets that have left the airfoil surface. Also explored are the implications of endwall film cooling for infrared vane surface temperature measurements. The reduced endwall temperatures reduce the thermal emissions from this surface, so reducing the amount of extraneous radiation reflected from the vane surface where measurements are being made. The results of a detailed calibration show that the maximum local film effectiveness measurement error could be up to 0.05 if this effect were to go unaccounted for.

show abstract

“…The 1D model was validated by showing its accuracy to predict the temperature distributions of a NASA E3 blade with an uncertainty of less than +/-10%. As a result, 1D model was proposed as a novel, quicker, and more convenient way for the overall analysis and for a set of different boundary conditions with the same blade (NASA E3) Chandran and Prasad [16] carried out both the numerical and experimental studies on the leading edge region of a typical gas turbine NGV, cooled by a combination of impingement and showerhead film cooling. A detailed flow and conjugate heat transfer study revealed that the complex flow structure results owing to the coolant-mainstream interaction and the influence of vane material thermal conductivity.…”

Section: Rama Kumar and Prasadmentioning

confidence: 99%

“…Prasad [16] Although the values of pressure drop across these holes are much smaller, there is no danger of hot gas ingestion as they are all positive.The third hole of the SH1 row exhibits highest coolant pressure dop and hence corresponding high mass flow rate (refer Fig.9). This helps in the removal of more heat from the NGV surface and decreases the temperature of vane surface.…”

Section: Mass Flow Ate Distributionmentioning

confidence: 99%

Coupled flow network model and CFD analysis for a combined impingement and film cooled gas turbine nozzle guide vane

Kukutla¹,

Prasad²

2017

MMC_B

View full text Add to dashboard Cite

The nozzle guide vane (NGV) of a gas turbine engine possesses complex cooling passages, with inherent thermo-fluid dynamic interactions between the vane and the main stream. The present paper is an attempt to make use of the Computational Fluid Dynamics(CFD) tools as well as the flow network analysis tools, in combination, for analyzing typical cooled NGV flow passages. CFD results containing the static and total pressure contours are presented in the paper and are summarized as simple correlating relations; these in turn are used to generate the discharge coefficients as input to the flow network. The pressure conditions at different boundary nodes are further input to the flow network analysis. The mass flow rate and pressure drop values through the impingement and film holes are obtained as output from the flow network model. Comparison of the results from one-dimensional approach coupled with three-dimensional CFD analysis with the available literature by Jin et al. [7] shows a good agreement for the operating pressure ratio in the range of 1.2 to 1.5 at pressure surface rows of the film cooling holes in the leading edge region of the vane. The accuracy of the calculated total pressure ratio on the pressure surface rows of the leading edge circuit has been found satisfactory.The coolant from FIT and AIT are 25.5% and 74.5% respectively. The secondary fluid flows from FIT is 24.3% fed to the leading edge film holes, while 51.9% of coolant is fed to the mid-chord region through the film holes, 22.5% coolant flows out of the trailing edge film holes and the remaining 1.3% flows through trailing edge slot

show abstract

Conjugate Heat Transfer Study of Combined Impingement and Showerhead Film Cooling Near NGV Leading Edge

Cited by 15 publications

References 13 publications

Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane

The Effects of Combustor Cooling Features on Nozzle Guide Vane Film Cooling Experiments

Coupled flow network model and CFD analysis for a combined impingement and film cooled gas turbine nozzle guide vane

Contact Info

Product

Resources

About