【文章內(nèi)容簡介】 ge,and Thermal Barrier Coating Spakkation on Vane Endwall Film of ,129:599607.[3]戴萍,24(5)：560565.[4]劉存良,－,23(4):598604.[5]李廣超,25(6):581585.[6]Baheri S, Alavi Tabrizi S P, Jubran B A. Film cooling effectiveness from trenched shaped and pound holes. Heat Mass Transfer, 2008, 44: 989998.[7]Lu Y P, Dhungel A, Ekkad S V, et al. Effect of trench width and depth on film cooling from cylindrical holes embedded in trenches. Journal of Turbomachinery, 2009, 13(11):0313.[8]章大海,23(4):2732.[9]戴萍,24(1):16[10]鄧宏武,(7):4549.[11]李少華, ,29(8):5559.[12], of Surface Depositon,Hole Blockage,and Thermal Barrier Coating Spallation on Vane Endwall Film of ,129:599607[13]：（工學(xué)碩士學(xué)位論文）.哈爾濱:哈爾濱工程大學(xué),2008. [14]李保岐,3:3334.[15]陳偉,29(34).[16]李瓏，,25:306311.[17] Jovanovic180。,. de Lange et of hole imperfection on jet cross flow inter Journal of Heat and Fluid :4253致 謝本篇論文在導(dǎo)師楊曉軍老師精心指導(dǎo)和嚴(yán)格要求下完成。導(dǎo)師淵博的知識，嚴(yán)謹(jǐn)?shù)目蒲凶黠L(fēng)都深深的影響著我。值此論文完成之際，再次衷心地感謝畢業(yè)設(shè)計導(dǎo)師楊曉軍老師。感謝080141H班王志平、肖庭文同學(xué)在CAD建模方面的指導(dǎo)與建議。感謝默默信任我、支持我的家人，你們給了我前進(jìn)的信心。53附錄：外文翻譯資料Heat Transfer Distributions on a Cylinder with Simulated Thermal Barrier Coating SpallationSrinath and JeChin of thermophysics and heat ,13(1):7681.IntroductionHigher inlet temperatures in modern gasturbine engines provide higher power output and higher thermal efficiency. Hightemperature gases have a damaging effect on hot gas path ponents in the engine. Thermal barrier coatings (TBC) are used to protect engine ponent metal surfaces from these hightemperature gases. The TBC coating is a heatresistant ceramic layer sprayed onto the hot gas side of the turbine airfoil. The TBC application process is either done by air plasma spraying (APS) or the plasma vapor deposition (PVD) technique. The TBCs consist of two layers and involve a base bond coat layer applied onto the metal surface and a ceramic top layer applied on top of the base bond. The TBC forms an insulating layer between the hot gases and the airfoil metal surface, reducing the heat input to the airfoil. In land based gasturbine engines, the TBC surface undergoes more severe erosion as a result of the use of coalderived fuels for bustion. When the TBC surface gets damaged, the bond will disassociate and a spallation is formed exposing the inner metal surface to the hot gases. Typically, the heat transfer coefficient around the exposed metal surface area will be enhanced because of tripping of the boundary layer. The enhanced heat transfer coefficients increase heat loads around the spallation, which may be detrimental to the life of the ponent. The increased heat load will cause further degradation of the spalled region and, hence, will lead to early failure of the turbine ponent. The present study focuses on the effect of simulated TBC spallation on the leadingedge region of a turbine blade. Watt et and Abuaf et provide a detailed description of the TBC application process. Watt et al. focused on the boundarylayer characteristics and losses caused by the TBC layer, and Abuaf et al. studied the stagnation heat transfer on cylindrical leadingedge models coated with real TBC. The leadingedge region of the turbine airfoil has been the focus of several heat transfer studies. O39。Brien and Van Fossen3 and Morehouse and Simoneau4 studied the effects of freestream turbulence on the forward half of a circular cylinder. Ota and Kon,539。6 Bellows and Mayle,7 and Mehendale et studied heat transfer on a simulated semicircular leading edge with a flat after body. They reported that an increase in freestream turbulence intensity increases leadingedge heat transfer significantly. All of the preceding studies were for a surface without roughness or coating. Seban,9 Yamamoto et al.,10 Chyu and Goldstein,11 and Metzger et studied heat transfer for flow over rectangular cavities on a flat surface. However, the preceding studies were not intended to simulate spallations on turbine ponents. Ekkad and Han13 studied the effect of cavity shape, size, and depth on heat transfer enhancement over a flat surface. The study intended to simulate various spallation geometries to correlate the effects on heat transfer. They presented detailed heat transfer enhancement distributions for various spallation geometries using a transient liquidcrystal technique. They reported that increases in cavity size and depth increases heat transfer enhancement because of spallation. They also reported that cavities with longer axial length produced higher heat transfer enhancement on the flat surface. The present study simulates the effect of TBC spallation on a cylindrical leadingedge model. The spallation sizes were based on scaling from real engine spalls and TBC thicknesses from landbased gasturbine engines. Heat transfer tests were conducted at three freestream turbulence levels for four spallation locations on the leading edge. Detailed heat transfer enhancement distributions are presented within and around the spallation. A transient liquidcrystal technique was used to obtain the detailed heat transfer distributions on the leadingedge surface. Two different spallation depths were studied at each spallation location to understand the effect of spallation depth. The highresolution results help identify local high and lowheat transfer regions caused by flow reattachment and separation, respectively.Test Apparatus and InstrumentationA schematic of the wind tunnel is shown in Fig. 1. The suctiontype wind tunnel was designed to avoid uncontrolled turbulence at the inlet of the test section. A flow straightener is followed by a contraction inlet nozzle. The nozzle has a contraction ratio of 3:1. The test tunnel is cm X cm in cross section and 183 cm long with the cylindrical model placed cm downstream of the nozzle exit. A tailboard was placed at the rear of the cylinder to reduce the downstream wake effects on upstream heat transfer. A grid is placed at the nozzle exit for the generat