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Author: Mohammed Aref Al-Hemyari
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 58
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Book Description
"Cooling gas turbine blades is a crucial technique to allow higher turbine inlet temperatures. A higher turbine inlet temperature allows boosting gas turbine efficiency, which reduces fuel consumption. One of the main cooling techniques of the turbine blades is film cooling where a relatively low air temperature is used to form a blanket of cool air around the blade to shield it from high temperature gases. Many complex interrelated geometry and flow parameters affect the effectiveness of the film cooling. The complex interrelations between these parameters are considered the main challenge in properly understanding the effect of these parameters on film cooling. Testing such cooling techniques under actual engine conditions is even more challenging due to difficulty of installing proper instrumentations. Numerical techniques are viable analysis techniques that are used to better understand film cooling techniques. In this study, a simplified 2D film cooling jet blown from the slot jet is investigated under multiple variable parameters, mainly, the blowing ratio, jet angle, density ratio and centrifugal force. The performance of the film cooling is reported using local and average adiabatic film effectiveness. The main contribution of this study is exploring the effect of the centrifugal force and wall material selection using conjugate heat transfer on film cooling effectiveness. The centrifugal force reduces the overall adiabatic film effectiveness. A correlation between the blowing ratio, density ratio and injection angle is developed in this work. The highest film cooling performance was founded at a blowing ratio of 0.8, an injection angle of 30° and density ratio of 1.2."--Abstract.
Author: Mohammed Aref Al-Hemyari
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 58
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Book Description
"Cooling gas turbine blades is a crucial technique to allow higher turbine inlet temperatures. A higher turbine inlet temperature allows boosting gas turbine efficiency, which reduces fuel consumption. One of the main cooling techniques of the turbine blades is film cooling where a relatively low air temperature is used to form a blanket of cool air around the blade to shield it from high temperature gases. Many complex interrelated geometry and flow parameters affect the effectiveness of the film cooling. The complex interrelations between these parameters are considered the main challenge in properly understanding the effect of these parameters on film cooling. Testing such cooling techniques under actual engine conditions is even more challenging due to difficulty of installing proper instrumentations. Numerical techniques are viable analysis techniques that are used to better understand film cooling techniques. In this study, a simplified 2D film cooling jet blown from the slot jet is investigated under multiple variable parameters, mainly, the blowing ratio, jet angle, density ratio and centrifugal force. The performance of the film cooling is reported using local and average adiabatic film effectiveness. The main contribution of this study is exploring the effect of the centrifugal force and wall material selection using conjugate heat transfer on film cooling effectiveness. The centrifugal force reduces the overall adiabatic film effectiveness. A correlation between the blowing ratio, density ratio and injection angle is developed in this work. The highest film cooling performance was founded at a blowing ratio of 0.8, an injection angle of 30° and density ratio of 1.2."--Abstract.
Author: Lamyaa El-Gabry
Publisher: BiblioGov
ISBN: 9781289236779
Category :
Languages : en
Pages : 40
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Book Description
Computational Fluid Dynamics is used in the analysis of a film cooling jet in crossflow. Predictions of film effectiveness are compared with experimental results for a circular jet at blowing ratios ranging from 0.5 to 2.0. Film effectiveness is a surface quantity which alone is insufficient in understanding the source and finding a remedy for shortcomings of the numerical model. Therefore, in addition, comparisons are made to flow field measurements of temperature along the jet centerline. These comparisons show that the CFD model is accurately predicting the extent and trajectory of the film cooling jet; however, there is a lack of agreement in the near-wall region downstream of the film hole. The effects of main stream turbulence conditions, boundary layer thickness, turbulence modeling, and numerical artificial dissipation are evaluated and found to have an insufficient impact in the wake region of separated films (i.e. cannot account for the discrepancy between measured and predicted centerline fluid temperatures). Analyses of low and moderate blowing ratio cases are carried out and results are in good agreement with data.
Author: Xuezhi Zhang
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
This work presents the performance of a louver film-cooling scheme under different operating conditions. The louver cooling scheme consists of a bend by which the coolant going through the flow passage is redirected from vertical to horizontal direction before being injected into the mainstream through an expanded exit. Not only is the momentum of the coolant converted to the mainstream direction, but it is also reduced by the expanded exit before injection. The impingement of the coolant on the blade surface inside the bend also enables further cooling on the targeted surface. The louver cooling scheme was tested under a variety of conditions, from a flat plate to airfoils, from low speed incompressible flows to transonic flows, from a stationary airfoil to a rotating airfoil, and from the leading edge to the middle of an airfoil. Unsteady analysis using a DES (Detached Eddy Simulation) model was also carried out to evaluate its ability to accurately simulate film cooling by comparing with steady state analysis. In general, the louver cooling scheme has been proved to provide enhanced cooling protection to the targeted surface in comparison with other cooling schemes in all conditions tested. At low speed incompressible flow conditions, a higher blowing ratio led to a higher cooling effectiveness. At transonic flow conditions, a moderately higher blowing ratio also proved helpful with a higher cooling effectiveness. Very high blowing ratios, however, proved to be detrimental to the cooling performance since strong detached shock wave structures due to high blowing ratios caused boundary layer separation, rendering the coolant virtually ineffective. The rotation of blade was found to have a significant impact on the level of cooling effectiveness at the leading edge of an airfoil. With regard to the cooling performance, blowing ratio was the dominant factor at low rotational speeds and the rotational speed was the dominant factor at high blowing ratios for circular holes. For the louver scheme as jet liftoff was avoided, effectiveness increased with rotating speed. Results also showed that, unsteady analysis was not significantly more accurate than steady analysis. The unsteady analysis did capture the coolant lateral spreading better, with a high cost of computing, however. Results in this work show that shock waves encountered on transonic airfoils had a significant impact on film cooling effectiveness on any shaped holes. Therefore, experimental data obtained under low speed test should be used with great caution in real design of turbine blade cooling. There are fundamental differences in film cooling between at the leading edge and elsewhere on an airfoil in that a slight incidence shifting due to turbine rotating speed may cause a sudden decrease in cooling effectiveness level at high blowing ratios for circular hole. This could lead to a catastrophic failure if the blade is already in a weak and stressed state. Using of shaped holes with expanded exits may prevent this from happening.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 14
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Book Description
Author: Shahin Salimi
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 140
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Book Description
Author: Cuong Quoc Nguyen
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 149
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Book Description
Film cooling is investigated on a flat plate both numerically and experimentally. Conical shaped film hole are investigated extensively and contribute to the current literature data, which is extremely rare in the open public domain. Both configuration of the cylindrical film holes, with and without a trench, are investigated in detail. Design of experiment technique was performed to find an optimum combination of both geometrical and fluid parameters to achieve the best film cooling performance. From this part of the study, it shows that film cooling performance can be enhanced up to 250% with the trenched film cooling versus non-trenched case provided the same amount of coolant. Since most of the relevant open literature is about film cooling on flat plate endwall cascade with linear extrusion airfoil, the purpose of the second part of this study is to examine the interaction of the secondary flow inside a 3D cascade and the injected film cooling jets. This is employed on the first stage of the aircraft gas turbine engine to protect the curvilinear (annular) endwall platform. The current study investigates the interaction between injected film jets and the secondary flow both experimentally and numerically at high Mach number (M=0.7). Validation shows good agreement between obtained data with the open literature. In general, it can be concluded that with an appropriate film coolant to mainstream blowing ratio, one can not only achieve the best film cooling effectiveness (FCE or [eta]) on the downstream endwall but also maintain almost the same aerodynamic loss as in the un-cooled baseline case. Film performance acts nonlinearly with respect to blowing ratios as with film cooling on flat plate, in the other hand, with a right blowing ratio, film cooling performance is not affect much by secondary flow. In turn, film cooling jets do not increase pressure loss at the downstream wake area of the blades.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 994
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Book Description
Author: Mulugeta K. Berhe
Publisher:
ISBN:
Category :
Languages : en
Pages : 314
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Book Description
Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 540
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Book Description
Author: R.S. Amano
Publisher: WIT Press
ISBN: 1845649060
Category : Science
Languages : en
Pages : 253
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Book Description
Due to the requirement for enhanced cooling technologies on modern gas turbine engines, advanced research and development has had to take place in field of thermal engineering. Among the gas turbine cooling technologies, impingement jet cooling is one of the most effective in terms of cooling effectiveness, manufacturability and cost. The chapters contained in this book describe research on state-of-the-art and advanced cooling technologies that have been developed, or that are being researched, with a variety of approaches from theoretical, experimental, and CFD studies. The authors of the chapters have been selected from some of the most active researchers and scientists on the subject. This is the first to book published on the topics of gas turbines and heat transfer to focus on impingement cooling alone.
