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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.1; 20060506-11; Barcelona(ES) >NONINTRUSIVE FLOWFIELD, TEMPERATURE AND SPECIES MEASUREMENTS ON A GENERIC AEROENGINE COMBUSTOR AT ELEVATED PRESSURES
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NONINTRUSIVE FLOWFIELD, TEMPERATURE AND SPECIES MEASUREMENTS ON A GENERIC AEROENGINE COMBUSTOR AT ELEVATED PRESSURES

机译：通用压力下通用航空发动机燃烧室的非侵入式流场，温度和物种测量

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摘要

A generic combustor was built, that gives wide optical access at higher pressure and shares typical features with aero engine combustors. A comprehensive data set for validation of RANS and LES codes was generated at isothermal as well as combusting conditions at 2 and 10 bars with 650 K preheat using natural gas as fuel. The velocity field was measured using LDA (Laser Doppler Anemometry) and DGV (Doppler Global Velocimetry) as well as PIV (Particle Image Velocimetry). Temperature data were acquired using CARS (Coherent Anti stokes Raman Scattering) and SRS (Spontaneous Raman Scattering). Major species concentrations as well as the mixture fraction in the primary zone of the combustor were also measured using SRS. Mean and RMS values of the temperature measured by CARS in the secondary zone illustrate the influence of the jet impingement on the unsteady mixing of the jets with the swirling primary air.
机译：建造了通用燃烧器，该燃烧器可在较高压力下提供宽广的光学通道，并与航空发动机燃烧器具有典型特征。在以天然气为燃料的650 K预热下，在2 bar和10 bar等温以及燃烧条件下，生成了用于验证RANS和LES代码的综合数据集。使用LDA（激光多普勒风速仪）和DGV（多普勒全局测速仪）以及PIV（颗粒图像测速仪）测量速度场。使用CARS（相干反斯托克斯拉曼散射）和SRS（自发拉曼散射）获取温度数据。还使用SRS测量了燃烧室主要区域中的主要物种浓度以及混合物分数。通过CARS在次级区域中测得的温度的平均值和RMS值说明了射流撞击对射流与涡旋初级空气不稳定混合的影响。

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