Gas Turbine Combustor Liner Wall Heat Load Characterization for Different Gaseous Fuels

2019 ◽  
Author(s):  
Kishore Ranganath Ramakrishnan ◽  
Shoaib Ahmed ◽  
Benjamin Wahls ◽  
Prashant Singh ◽  
Maria A. Aleman ◽  
...  
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Heat Load ◽  
Recirculation Zone ◽  
Flame Temperature ◽  
Conduction Model ◽  
Steady State Condition ◽  
Gaseous Fuels ◽  
Peak Heat Flux ◽  
Combustor Liner

Abstract The knowledge of detailed distribution of heat load on swirl stabilized combustor liner wall is imperative in the development of liner-specific cooling arrangements, aimed towards maintaining uniform liner wall temperatures for reduced thermal stress levels. Heat transfer and fluid flow experiments have been conducted on a swirl stabilized lean premixed combustor to understand the behavior of Methane-, Propane-, and Butane-based flames. These fuels were compared at different equivalence ratios for a matching adiabatic flame temperature of Methane at 0.65 equivalence ratio. Above experiments were carried out a fixed Reynolds number (based on the combustor diameter) of 12000, where the pre-heated air temperature was approximately 373K. Combustor liner in this setup was made from 4 mm thick quartz tube. An infrared camera was used to record the inner and outer temperatures of liner wall, and two-dimensional heat conduction model was used to find the wall heat flux at a quasi-steady state condition. Flow field in the combustor was measured through Particle Image Velocimetry. The variation of peak heat flux on the liner wall, position of peak heat flux and heat transfer, and position of impingement of flame on the liner have been presented in this study. For all three gaseous fuels studied, the major swirl stabilized flame features such as corner recirculation zone, central recirculation zone and shear layers have been observed to be similar. Liner wall and exhaust temperature for Butane was highest among the fuel tested in this study which was expected as the heat released from combustion of Butane is higher than that of Methane and Propane.

On the Transiant Response of Convective Extended Surface Heat Transfer: A New Approach

2006 ◽  
Author(s):  
P. Razelos ◽  
G. Michalakeas
Keyword(s):  
Heat Transfer ◽  
Steady State ◽  
Transient Response ◽  
Surface Heat ◽  
Constant Thickness ◽  
Conduction Model ◽  
Steady State Condition ◽  
Surface Heat Transfer ◽  
Extended Surface ◽  
Extended Surfaces

This work is devoted to the study of the extended surfaces transient response. Although, the steady-state fin analysis has attracted considerable attention for a very long time, the interest in the transient response started in the last quarter of the past century. Several publications have appeared since, either analytical using the 1-D, conduction model, or experimental. Perusing the pertinent literature, however, we have observed that, in all previous published papers the authors treat the transient response of extended surfaces, or fins, like regular solids. However, fin endeavors rest on certain fundamental concepts, leading to some simplified assumptions, that we shall briefly discuss in the next section, which allows using the 1-D conduction model, and affect their steady-state operation. Therefore, the need for re-examining and revising the previously used methods becomes apparent. However, the authors are indebted to the pioneer workers on this topic that opened new avenues in the field of extended surface heat transfer. The aim of this work is to offer a different point of view to this problem, by introducing a new spatial coordinate system, and a new time scale. The solutions presented here, rest on the previously mentioned certain fundamental concepts developed recently. In the following we show step by step, how the existing pertinent equations and formulas of fins' transient response, are transformed to new simpler forms, expressed in terms of more appropriate dimensionless parameters, in accord with those appearing in recent publications. In the following, we confine to the analysis of constant thickness longitudinal and pin fins subject to specific1 boundary conditions. Each case is accompanied with an example that, for reasons of comparison are taken from the literature. We also discuss what is meant by "the time required for transient response to attain the steady-state condition."

scholarly journals Influence of the type of fuel on the heat transfer in internal combustion engine

2007 ◽  
Vol 128 (1) ◽  
pp. 59-63
Author(s):  
Leon BOGUSŁAWSKI ◽  
Janusz RABIEGA
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Internal Combustion Engine ◽  
Heat Load ◽  
Liquid Fuel ◽  
Combustion Engine ◽  
Internal Combustion ◽  
Gaseous Fuel ◽  
Significant Growth ◽  
Representative Points

Due to diminishing liquid fuel resources comparing with gaseous fuel as well as difference in their price one can observe a tendency to substitute liquid fuel with gaseous one. The reduction in the emission of toxic ingredients of fumes is also of extreme importance. However, together with the change of the fuel new problems have occurred. One of them is the increase in heat load that shortens the life of an engine. Therefore, studies on the chosen type of an engine were carried out. A heat flux in representative points of the engine’s head was measured. The engine was firstly fed with petrol, later with LPG. For both types of fuel the obtained power was similar. Studies showed a significant growth in heat load on the surface of the engine’s head after changing the fuel from petrol to LPG.

Impinging Jet Cooling Optimization for Obtaining Uniform Heat Flux

2010 ◽  
Author(s):  
Farshad Kowsary ◽  
Hamed Gholamian ◽  
Mehran Rajaeeian Hoonejani
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Transfer Problem ◽  
Jet Impingement ◽  
Separation Distance ◽  
Uniform Heat Flux ◽  
Target Plate ◽  
Steady State Condition ◽  
Uniform Heat ◽  
Impingement Heat Transfer

In this study obtaining a uniform heat flux over a target surface was investigated by means of using characteristics of jet impingement heat transfer. Conjugate Gradients Method (CGM) was utilized to minimize the objective function defined on the basis of the squared differences between the target heat flux and the calculated ones. Design variables were taken to be jets’ Reynolds numbers, separation distance between the exit plane of the jets and the target plate, as well as inter-jet spacing. Air single phase jets were used in this study. The problem was solved for the cases of 4 and 6 jets. Temperature difference between the jet exit and the target plate is 100°C, and a steady state condition was assumed. The Finite Volume Method and an unstructured mesh were used for direct solution of the jet impingement heat transfer problem for a laminar jets impingement to a flat plate with constant temperature.

Effect of Velocity on Heat Transfer to Boiling Freon-113

1980 ◽  
Vol 102 (1) ◽  
pp. 26-31 ◽  
Author(s):  
Salim Yilmaz ◽  
J. W. Westwater
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Atmospheric Pressure ◽  
Nucleate Boiling ◽  
High Heat ◽  
Heat Fluxes ◽  
Forced Flow ◽  
Film Boiling ◽  
Square Root ◽  
Peak Heat Flux

Measurements were made of the heat transfer to Freon-113 at near atmospheric pressure, boiling outside a 6.5 mm dia horizontal steam-heated copper tube. Tests included pool boiling and also forced flow vertically upward at uelocities of 2.4, 4.0 and 6.8 m/s. The metal-to-liquid ΔT ranged from 13 to 125° C, resulting in nucleate, transition, and film boiling. The boiling curves for different velocities did not intersect or overlap, contrary to some prior investigators. The peak heat flux was proportional to the square root of velocity, agreeing with the Vliet-Leppert correlation, but disagreeing with the Lienhard-Eichhorn prediction of an exponent of 0.33. The forced-flow nucleate boiling data were well correlated by Rohsenow’s equation, except at high heat fluxes. Heat fluxes in film boiling were proportional to velocity to the exponent 0.56, close to the 0.50 value given by Bromley, LeRoy, and Robbers. Transition boiling was very sensitive to velocity; at a ΔT of 55° C the heat flux was 900 percent higher for a velocity of 2.4 m/s than for zero velocity.

Comparison of Heat Transfer Measurement Techniques on a Transonic Turbine Blade Tip

2009 ◽  
Author(s):  
Devin O’Dowd ◽  
Qiang Zhang ◽  
Phil Ligrani ◽  
Li He ◽  
Stefan Friedrichs
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Turbine Blade ◽  
Transfer Coefficients ◽  
Adiabatic Wall ◽  
Steady State Condition ◽  
Heat Transfer Coefficients ◽  
Measure Surface Temperature ◽  
Blade Tip ◽  
Processing Techniques

The present study considers spatially-resolved surface heat transfer coefficients and adiabatic wall temperatures on a turbine blade tip in a linear cascade under transonic conditions. Six different measurement and processing techniques are considered and compared, including transient infrared thermography and thin-film heat flux gauges. Three methods use the same experimental setup, using a heater mesh to provide a near-instantaneous step-change in mainstream temperature, employing an infrared camera to measure surface temperature. The three methods use the same data but different processing techniques to determine the heat transfer coefficients and adiabatic wall temperatures. Two methods use different processing techniques to reconstruct heat flux from the temperature time trace measured. A plot of the heat flux versus temperature is used to determine the heat transfer coefficients and adiabatic wall temperatures. The third uses the classical solution to the 1-D non-steady Fourier equation to determine heat transfer coefficients and adiabatic wall temperatures. A fourth method uses regression analysis to calculate detailed heat transfer coefficients for a quasi-steady state condition using a thin-foil heater on the tip surface. The fifth method uses the infrared camera to measure the adiabatic wall temperature surface distribution of a blade tip after a quasi-steady state condition is present. Finally, the sixth method employs thin-film gauges to measure surface temperature histories at four discreet blade tip locations. With this approach, heat flux reconstruction is used to calculate the transient heat transfer coefficients and adiabatic wall temperatures. Overall, the present study shows that the infrared thermography technique with heat flux reconstruction using the Impulse method, is the most accurate and reliable method to obtain detailed, spatially-resolved heat transfer coefficients and adiabatic wall temperatures on a turbine blade tip in a linear cascade.

Flow Film Boiling From a Sphere to Subcooled Freon-11

1986 ◽  
Vol 108 (4) ◽  
pp. 934-938 ◽  
Author(s):  
J. A. Orozco ◽  
L. C. Witte
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Liquid Velocity ◽  
Flow Boiling ◽  
Empirical Correlation ◽  
The Other ◽  
Film Boiling ◽  
Vapor Film ◽  
Peak Heat Flux ◽  
Semi Empirical

The boiling curves for flow boiling of freon-11 from a fluid-heated 3.81-cm-dia copper sphere showed dual maxima. One maximum corresponded to the nucleate peak heat flux while the other was caused by transitory behavior of the wake behind the sphere. Film boiling data were predicted well by the theory of Witte and Orozco. A semi-empirical correlation of the film boiling data accounting for both liquid velocity and subcooling predicted the heat transfer to within +/− 20 percent. The conditions at which the vapor film became unstable were also determined for various sub-coolings and velocities.

Comparison of Heat Transfer Measurement Techniques on a Transonic Turbine Blade Tip

2010 ◽  
Vol 133 (2) ◽  
Author(s):  
D. O. O’Dowd ◽  
Q. Zhang ◽  
L. He ◽  
P. M. Ligrani ◽  
S. Friedrichs
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Turbine Blade ◽  
Infrared Camera ◽  
Transfer Coefficients ◽  
Adiabatic Wall ◽  
Steady State Condition ◽  
Heat Transfer Coefficients ◽  
Blade Tip ◽  
Processing Techniques

The present study considers spatially resolved surface heat transfer coefficients and adiabatic wall temperatures on a turbine blade tip in a linear cascade under transonic conditions. Five different measurement and processing techniques using infrared thermography are considered and compared. Three transient methods use the same experimental setup, using a heater mesh to provide a near-instantaneous step-change in mainstream temperature, employing an infrared camera to measure surface temperature. These three methods use the same data but different processing techniques to determine the heat transfer coefficients and adiabatic wall temperatures. Two of these methods use different processing techniques to reconstruct heat flux from the temperature time trace measured. A plot of the heat flux versus temperature is used to determine the heat transfer coefficients and adiabatic wall temperatures. The third uses the classical solution to the 1D nonsteady Fourier equation to determine heat transfer coefficients and adiabatic wall temperatures. The fourth method uses regression analysis to calculate detailed heat transfer coefficients for a quasi-steady-state condition using a thin-foil heater on the tip surface. Finally, the fifth method uses the infrared camera to measure the adiabatic wall temperature surface distribution of a blade tip after a quasi-steady-state condition is present. Overall, the present study shows that the infrared thermography technique with heat flux reconstruction using the impulse method is the most accurate, computationally efficient, and reliable method to obtain detailed, spatially resolved heat transfer coefficients and adiabatic wall temperatures on a transonic turbine blade tip in a linear cascade.

scholarly journals Three-dimensional computational fluid dynamics modeling of TiO2/R134a nanorefrigerant

2017 ◽  
Vol 21 (1 Part A) ◽  
pp. 175-186 ◽  
Author(s):  
Kamil Arslan
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Laminar Flow ◽  
Convective Heat Transfer ◽  
Convective Heat ◽  
Volume Fraction ◽  
Reynolds Numbers ◽  
Nanoparticle Volume Fraction ◽  
Steady State Condition ◽  
Volume Fractions

In this study, numerical investigations were carried out for R134a based TiO2 nanorefrigerants. Forced laminar flow and heat transfer of nanorefrigerants in a horizontal smooth circular cross-sectioned duct were investigated under steady-state condition. The nanorefrigerants consist of TiO2 nanoparticles suspended in R134a as a base fluid with four particle volume fractions of 0.8, 2.0 and 4.0%. Numerical studies were performed under laminar flow conditions where Reynolds numbers range from 8?102 to 2.2?103. Flow is flowing in the duct with hydrodynamically and thermally developing (simultaneously developing flow) condition. The uniform surface heat flux with uniform peripheral wall heat flux (H2) boundary condition was applied on the duct wall. Commercial CFD software, Ansys Fluent 14.5, was used to carry out the numerical study. Effect of nanoparticle volume fraction on the average convective heat transfer coefficient and average Darcy friction factor were analyzed. It is obtained in this study that increasing nanoparticle volume fraction of nanorefrigerant increases the convective heat transfer in the duct; however, increasing nanoparticle volume fraction does not influence the pressure drop in the duct. The velocity and temperature distribution in the duct for different Reynolds numbers and nanoparticle volume fractions were presented.

Effects of Hot Streak and Airfoil Clocking on Heat Transfer and Aerodynamic Characteristics in Gas Turbine

2015 ◽  
Vol 138 (2) ◽  
Author(s):  
Zhenping Feng ◽  
Zhaofang Liu ◽  
Yan Shi ◽  
Zhiduo Wang
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Gas Turbine ◽  
Heat Load ◽  
Aerodynamic Characteristics ◽  
High Heat ◽  
Inlet Temperature ◽  
Blade Surface ◽  
Heat Transfer Characteristics ◽  
Hot Streak

The effects of the hot streak and airfoil clocking on the heat transfer and aerodynamic characteristics in a high pressure (HP) gas turbine have been investigated in this paper. The blade geometry is taken from the first 1.5 stage turbine of GE-E3 engine. To study the effect of hot streak clocking, three cases under nonuniform and uniform inlet temperature boundary conditions were simulated first. Subsequently, four clocking positions (CPs) of S2 (second stator) were arranged in these three cases to study the combined effect of hot streak and airfoil clocking. By solving the unsteady compressible Reynolds-averaged Navier–Stokes (RANS) equations, time-dependent solutions for the flow and heat transfer characteristics of the 1.5 stage turbine were obtained. The results indicate that impinged by different inlet temperature profiles, the heat flux distribution on S1 (first stator) blade varies significantly. Due to the separation of hot and cold fluid, more hot fluid flows toward pressure side (PS) of R1 (first rotor) and worsens the heat transfer environment there. The high heat flux on the R1 blade surface is controlled not only by the high heat transfer coefficient but also by the large temperature difference. By adjusting the CPs of S2, the hot streak fragments from the upstream could be guided to different places in S2 passage, to reduce the heat load on S2 blade surface. In view of the influence of the heat transfer characteristics, the nonadiabatic efficiency is calculated. The combined effects of the hot streak and airfoil clocking have been discussed, and the proper matching position for the two kinds of clocking could be selected for a higher nonadiabatic efficiency and lower heat load on S2 blade and end walls.

Modeling of Temperature Distributions in the Workpiece During Abrasive Waterjet Machining

1993 ◽  
Vol 115 (2) ◽  
pp. 446-452 ◽  
Author(s):  
M. M. Ohadi ◽  
K. L. Cheng
Keyword(s):  
Heat Flux ◽  
Heat Conduction ◽  
Abrasive Waterjet ◽  
Block Type ◽  
Analysis Tool ◽  
Operational Parameters ◽  
Conduction Model ◽  
Steady State Condition ◽  
Temperature Distributions ◽  
Awj Cutting

Modeling of temperature distributions in a block-type workpiece during cutting with an abrasive waterjet (AWJ) was the subject of an analytical/experimental investigation in the present study. The experiments included measurement of detailed time-temperature distributions in the workpiece for selected AWJ/workpiece operational parameters. Mathematical modeling of the problem made use of a two-part process. In the first part, the measured experimental data were fed into an inverse heat conduction algorithm, which determined the corresponding heat flux in the workpiece. In the second part, this heat flux was fed into a two-dimensional transient heat conduction model that calculated the corresponding temperature distributions in the workpiece. It is demonstrated that the proposed model can serve as a useful thermal analysis tool for AWJ cutting processes so long as a quasi-steady-state condition can be established in the workpiece.

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