Analyses and Measurements of Gas Turbine Blade Heat Transfer Under Unsteady High Free-Stream Turbulence Conditions

建议编号：CTS 9903972主要调查者：F.Ladeinde和J-C Han从燃气轮机获得一流的性能和理想的热力和推进负荷，必然导致使用更高的进口温度。然而，不幸的是，这一行业趋势带来了一个严重的问题，即涡轮部件的热负荷增加，从而导致叶片热损坏。拟议的工作的目标是通过综合努力来解决这个问题，该努力结合了纽约州立大学石溪分校相关方程的高性能直接数值模拟(DNS)和德克萨斯A&A&M的涡轮换热实验室验证数值模型的实验研究。拟议的DNS研究将在圣地亚哥超级计算中心NSF支持的NPACI计划的IBM SP/2超级计算机上进行，以利用其大规模并行化。要研究的各种参数的范围都在与实际发动机相关的范围内。二维和三维模拟都是为了回答与传热有关的基本问题，这些问题涉及过渡测量、现有过渡模型的可靠性、自由流湍流强度、长度尺度、换热、雷诺数和马赫数的关键影响。将确定导致换热的精确机制，并将评估和改进当前的涡轮叶片湍流热流和雷诺应力模型或将其丢弃。燃气轮机行业是航空航天技术、发电和运输的核心，成功的研究有望带来效率的提高和排放的减少。能源部先进涡轮系统计划(ATS)和能源部集成高性能涡轮发动机技术计划(IHPTET)都将从这项拟议的工作中受益。

ABSTRACTProposal Number: CTS 9903972Principal Investigator: F. Ladeinde and J-C HanObtaining first-rate performance and desirable thermodynamic and propulsive duty from gas turbine engines has invariably led to the use of higher inlet temperatures. Unfortunately, however, a severe problem is created by this industry trend, which are the increased heat load to the turbine components and the consequent thermal damage to the blades. The proposed work has the objective of addressing this issue using an integrated effort that combines high performance direct numerical simulation (DNS) of the relevant equations at SUNY Stony Brook, and experimental studies to validate the numerical models at the Turbine Heat Transfer Laboratory of Texas A & M. The proposed DNS study will be carried out on the IBM SP/2 supercomputer at the NSF-supported NPACI program at the San Diego Supercomputing Center, to take advantage of its massive parallelization. The ranges of the various parameters to be investigated are within those which are relevant to realistic engines. Both two-dimensional and three-dimensional simulations are planned to answer fundamental heat transfer-related questions concerning the measure of transition, the reliability of existing transition models, the crucial effects of free-stream turbulence intensity, length scale, heat transfer, Reynolds number, and Mach number. The precise mechanisms responsible for heat transfer will be identified and current turbine blade turbulence heat flux and Reynolds stress models will be evaluated and improved or discarded. The gas turbine industry is at the core of aerospace technology, power generation, and transportation and successful research is expected to lead to improvements in efficiency and reduction in emissions. Both the DOE advanced turbine system program (ATS) and the DOD integrated high performance turbine engine technology program (IHPTET), will benefit from this proposed work.