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Experimental Studies of a High-g Ultra-Compact Combustor at Elevated Pressures and Temperatures

机译:高克超紧凑型燃烧器在高温高压下的实验研究

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Volatile fuel costs have initiated a global sprint for technologies that will increase fuel efficiency in gas turbine engines, which continue to be a primary propulsion system for commercial and military aircraft The Ultra-Compact Combustor (UCC) is an advanced gas turbine combustor which integrates the high pressure turbine inlet guide vanes into the combustor. In comparison to conventional combustor systems, the UCC has the potential to shorten engine length, decrease engine weight, and reduce pressure losses entering the high pressure turbine rotor, all of which contribute subtantially to improving engine efficiency. The UCC has been studied in two forms in the literature - the Trapped-Vortex concept (TV) and the High-g concept (HG); the current study focuses on the latter. The HG-UCC utilizes a rectangular cavity wrapped around the outside circumference of the combustor where fuel and air are injected in a manner that generates a highly swirling flow within the circumferential cavity. The flow within the cavity experiences a centripetal acceleration ("g-load") which varies with tangential velocity and radius from the combustor axis. This "high-g" effect has the potential to increase flame speeds and volumetric heating rates, as well as enhance fuel air mixing and spreading providing the potential to reduce fuel injector count without compromising performance. Experiments were performed on the HG-UCC combustor at higher operating pressures, temperatures, and equivalence ratios than previous high-g experiments conducted in a similar uncooled inter-turbine burner (ITB). Results show that the HG-UCC has high combustion efficiencies for the entire range of data considered. The effects of pressure and temperature, cavity driver angle, centripetal acceleration (g-load), and equivalence ratio are studied for their impacts on combustion efficiency and nitrogen oxide (NO_x) emissions. An important result of this work is the construction of NO_x correlations for the HG-UCC. Test data performance results and correlations are compared to previous trapped vortex and high-g UCC experiments.
机译:波动的燃料成本已启动了一项旨在提高燃气涡轮发动机燃油效率的技术全球冲刺,而燃气涡轮发动机仍将继续作为商用飞机和军用飞机的主要推进系统。高压涡轮进口导叶进入燃烧室。与传统的燃烧器系统相比,UCC可以缩短发动机长度,降低发动机重量并减少进入高压涡轮机转子的压力损失,所有这些都将极大地提高发动机效率。对UCC的研究有两种形式:陷涡概念(TV)和高g概念(HG)。当前的研究集中在后者。 HG-UCC利用包裹在燃烧器外圆周上的矩形腔,以在圆周腔内产生高涡流的方式喷射燃料和空气。腔体内的流动经历向心加速度(“ g载荷”),该加速度随切向速度和距燃烧器轴线的半径而变化。这种“高克”效应有可能提高火焰速度和体积加热速率,并增强燃料空气的混合和扩散,从而有可能在不影响性能的情况下减少燃料喷射器的数量。在HG-UCC燃烧器上进行的实验比以前在类似的未冷却涡轮机间燃烧器(ITB)中进行的高g实验具有更高的工作压力,温度和当量比。结果表明,HG-UCC在所考虑的整个数据范围内具有较高的燃烧效率。研究了压力和温度,腔体驱动角,向心加速度(g负载)和当量比对燃烧效率和氮氧化物(NO_x)排放的影响。这项工作的重要成果是构建了HG-UCC的NO_x相关性。将测试数据的性能结果和相关性与以前的涡旋和高g UCC实验进行了比较。

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