نتایج جستجو برای: innovation in film cooling

تعداد نتایج: 17035755  

2002
J. H. Yoon R. F. Martinez-Botas

An experimental investigation of the local film cooling effectiveness and heat transfer coefficient downstream of a row of elongated holes in a simulated axial turbine blade tip is presented. Film cooling is needed to protect the turbine blade tip region from high heat transfer rates, especially when cooling by convection is insufficient to keep the temperature distribution of the blade within ...

2005
Daryoosh Vashaee James Christofferson Yan Zhang Ali Shakouri Gehong Zeng Chris LaBounty Xiaofeng Fan Joachim Piprek John E. Bowers Edward Croke

Modeling and optimization of bulk SiGe thin-film coolers are described. Thin-film coolers can provide large cooling power densities compared to commercial thermoelectrics. Thin-film SiGe coolers have been demonstrated with maximum cooling of 4◦C at room temperature and with cooling power density exceeding 500 W/cm2. Important parameters in the design of such coolers are investigated theoretical...

پایان نامه :وزارت علوم، تحقیقات و فناوری - دانشگاه علم و صنعت ایران 1378

طراحی محفظه احتراق از مهم ترین قسمتهای طراحی یک توربین گاز می باشد. وجود معادلات غیرخطی، پیچیده و گذرا، بررسی پارامترهای حاکم بر طراحی و بهینه نمودن آنها را بسیار مشکل می کند. یکی از نکات مهم در طراحی محفظه احتراق خنک کاری آن می باشد که بواسطه وجود دماهای بالای گاز در محفظه و محدودیت مواد قابل کاربرد از اهمیت ویژه ای برخوردار است . بمنظور خنک کاری محفظه احتراق از دو روش خنک کاری توسط مجرا (slot...

2016
Hyung Hee Cho

Abstract—There is a gap at combustor-turbine interface where leakage flow comes out to prevent hot gas ingestion into the gas turbine nozzle platform. The leakage flow protects the nozzle endwall surface from the hot gas coming from combustor exit. For controlling flow’s stream, the gap’s geometry is transformed by changing fillet radius size. During the operation, step configuration is occurre...

2015
Hossein Nadali Najafabadi

To achieve high thermal efficiency in modern gas turbines, the turbine-inlet temperature has to be increased. In response to such requisites and to prevent thermal failure of the components exposed to hot gas streams, the use of different cooling techniques, including film cooling, is essential. Finding an optimum film cooling design has become a challenge as it is influenced by a large number ...

2014
Wenwu Zhou Blake Johnson Hui Hu

An experimental study was performed to examine effects of compressibility on film cooling effectiveness for coolant flowing from cylindrical holes in a flat plate. The incoming flow Mach number was set at 0.07, 0.30, 0.50 and 0.70. The Pressure Sensitive Paint (PSP) technique, which is based on a mass transfer analogy, was used to map the adiabatic film cooling effectiveness distribution on the...

The objective of this work is to develop deep theoretical methods that are based on the solution of the integral boundary layer equations for investigating film cooling in liquid rocket engine. The integral model assumes that heat is transferred from hot free stream gas to the liquid film both by convection and radiation. The mass is transferred to the free srteam gas by the well-known blowing ...

2006
Xianchang Li Ting Wang

Effective cooling of gas turbine combustor liners, combustor transition pieces, turbine vanes (nozzles) and blades (buckets) is a critical task to protect these components from the flue gas at extremely high temperature. Air film cooling has been successfully used to cool these hot sections for the last half century. However, the net benefits from the traditional methods seem to be marginally i...

2011
Ting Wang Lei Zhao

In film cooling experimental studies, due to the difficulty in measuring the surface heat flux variation, a Heat Flux Ratio (HFR) equation originally derived by Mick and Mayle [1], has been widely employed to calculate the surface heat flux distribution using the measured adiabatic film effectiveness and surface temperature. A close examination of the derivation process and applications of the ...

2005
Xianchang Li Ting Wang

Cooling of gas turbine hot section components such as combustor liners, combustor transition pieces, turbine vanes (nozzles) and blades (buckets) is a critical task for improving the life and reliability of hotsection components. Conventional cooling techniques using air-film cooling, impingement jet cooling, and turbulators have significantly contributed to cooling enhancements in the past. Ho...

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