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首页> 外文会议>Congress of the International Council of the Aeronautical Sciences; 20060903-08; Hamburg(DE) >STAGNATION-POINT REVERSE-FLOW COMBUSTOR PERFORMANCE WITH LIQUID FUEL INJECTION
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STAGNATION-POINT REVERSE-FLOW COMBUSTOR PERFORMANCE WITH LIQUID FUEL INJECTION

机译：液体燃料喷射的停滞点逆流燃烧器性能

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This paper describes an investigation of the performance of the recently developed ultra low emissions, Stagnation-Point Reverse-Flow (SPRF) Combustor when burning liquid fuels (Jet-A and heptane). This study has been undertaken because of the need to burn liquid fuels with low emissions in gas turbines that are used, for example, in aircraft engines, land-based power generation, and marine applications. In contrast with state of the art combustors, in which the reactants and products enter and leave the combustor through opposite ends of the combustor, the reactants and products enter and leave the SPRF combustor through the same plane opposite a closed end. The design of the SPRF combustor allows mixing of reactants with hot combustion products and radicals within the combustor, prior to combustion. Thus, no external premixing of fuel and air is required. Additionally, since the air and fuel enter opposite the closed end of the combustor, they must stagnate near the closed end, thus establishing a region of low velocity just upstream of the closed end that helps stabilize the combustion process. This apparently produces a low-temperature, stable, distributed reaction zone. Previous studies with the SPRF combustor investigated its performance while burning natural gas. This paper presents the results of SPRF combustor studies using liquid fuels, both heptane and Jet-A. The performance of the combustor was investigated using an airblast fuel injector, which is suitable for the low fuel flow rates used in laboratory experiments. To reduce pressure losses across the injector, a diffuser was incorporated into an airblast injector. It was found that stable combustor operation was achieved burning Jet-A with emissions of less than 1 ppm NO_x and 5 ppm CO, pressure losses less than 5 percent, and a power density on the order of 10 MW/m~3 in atmospheric pressure. This power density would linearly scale to 300 MW/m~3 in a combustor at a pressure of 30 atmospheres.
机译：本文介绍了对最近开发的超低排放，停滞点逆流（SPRF）燃烧器在燃烧液体燃料（Jet-A和庚烷）时的性能的研究。由于需要在燃气轮机中燃烧低排放的液体燃料而进行了此项研究，这些燃气轮机用于飞机发动机，陆上发电和船舶应用。与其中反应物和产物通过燃烧器的相对端进入和离开燃烧器的现有技术燃烧器相反，反应物和产物通过与封闭端相对的同一平面进入和离开SPRF燃烧器。 SPRF燃烧器的设计允许在燃烧之前将反应物与燃烧器中的热燃烧产物和自由基混合。因此，不需要燃料和空气的外部预混合。另外，由于空气和燃料相对于燃烧器的封闭端进入，因此它们必须在封闭端附近停滞，从而在封闭端上游建立低速区域，这有助于稳定燃烧过程。这显然产生了一个低温，稳定的分布式反应区。 SPRF燃烧器的先前研究调查了其燃烧天然气时的性能。本文介绍了使用庚烷和Jet-A液体燃料的SPRF燃烧器研究的结果。使用鼓风喷油器对燃烧器的性能进行了研究，该喷油器适用于实验室实验中使用的低燃料流量。为了减少喷油器两端的压力损失，将扩压器结合到了空气喷射器中。发现在喷射压力小于1 ppm NO_x和5 ppm CO，压力损失小于5％，功率密度在大气压下约为10 MW / m〜3的条件下燃烧Jet-A可实现稳定的燃烧器运行。在30个大气压的压力下，该功率密度将在燃烧室中线性扩展至300 MW / m〜3。

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