Design Parameters for an Aircraft Engine Exit Plane Particle Sampling System

被引:16
|
作者
Wong, Hsi-Wu [1 ]
Yu, Zhenhong [1 ]
Timko, Michael T. [1 ]
Herndon, Scott C. [1 ]
Blanco, Elena de la Rosa [1 ]
Miake-Lye, Richard C. [1 ]
Howard, Robert P. [2 ]
机构
[1] Aerodyne Res Inc, Billerica, MA 01821 USA
[2] Aerosp Testing Alliance, Arnold AFB, TN 37389 USA
关键词
AEROSOL MASS-SPECTROMETER; THERMOPHORETIC DEPOSITION; HOMOGENEOUS NUCLEATION; HYDROCARBON EMISSIONS; H2SO4-H2O; SULFUR; MODEL; SIZE; SOOT; FLOW;
D O I
10.1115/1.4001979
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
The experimental data and numerical modeling were utilized to investigate the effects of exhaust sampling parameters on the measurements of particulate matter ( PM) emitted at the exit plane of gas-turbine engines. The results provide guidance for sampling system design and operation. Engine power level is the most critical factor that influences the size and quantity of black carbon soot particles emitted from gas-turbine engines and must be considered in sampling system design. The results of this investigation indicate that the available soot surface area significantly affects the amount of volatile gases that can condense onto soot particles. During exhaust particle measurements, a dilution gas is typically added to the sampled exhaust stream to suppress volatile particle formation in the sampling line. Modeling results indicate that the dilution gas should be introduced upstream before a critical location in the sampling line that corresponds to the onset of particle formation microphysics. Also, the dilution gas should be dry for maximum nucleation suppression. In most aircraft PM emissions measurements, the probe-rake systems are water cooled and the sampling line may be heated. Modeling results suggest that the water cooling of the probe tip should be limited to avoid overcooling the sampling line wall temperature and, thus, minimize additional particle formation in the sampling line. The experimental data show that heating the sampling lines will decrease black carbon and sulfate PM mass and increase organic PM mass reaching the instruments. Sampling line transmission losses may prevent some of the particles emitted at the engine exit plane from reaching the instruments, especially particles that are smaller in size. Modeling results suggest that homogeneous nucleation can occur in the engine exit plane sampling line. If newly nucleated particles, typically smaller than 10 nm, are indeed formed in the sampling line, sampling line particle losses provide a possible explanation, in addition to the application of dry diluent, that they are generally not observed in the PM emissions measurements. [DOI: 10.1115/1.4001979]
引用
收藏
页数:15
相关论文
共 50 条
  • [31] AUTOMATED DESIGN OF THE LANGUAGE OF AIRCRAFT ENGINE TESTS
    KOZHEVNIKOV, YV
    ZALYAEV, IA
    IZVESTIYA VYSSHIKH UCHEBNYKH ZAVEDENII AVIATSIONAYA TEKHNIKA, 1991, (03): : 64 - 68
  • [32] Design Space Reduction using Clustering in Aircraft Engine Design
    Karagoz, Esma
    Sarojini, Darshan
    Tai, Jimmy
    Mavris, Dimitri
    2019 IEEE AEROSPACE CONFERENCE, 2019,
  • [33] Design of the Power Management System for Electrical Power Systems in More Electric Engine / Aircraft
    Zhang, Yicheng
    Peng, Gabriel Ooi Heo
    Dasgupta, Souvik
    Husband, Mark
    Su, Rong
    Wen, Changyun
    2018 IEEE INTERNATIONAL CONFERENCE ON ELECTRICAL SYSTEMS FOR AIRCRAFT, RAILWAY, SHIP PROPULSION AND ROAD VEHICLES & INTERNATIONAL TRANSPORTATION ELECTRIFICATION CONFERENCE (ESARS-ITEC), 2018,
  • [34] NUMERICAL ANALYSIS OF PARTICLE DEPOSITION IN AN AIRCRAFT ENGINE COMPRESSOR CASCADE
    Casari, Nicola
    Altmeppen, Johannes
    Koch, Christian
    Pinelli, Michele
    Staudacher, Stephan
    Suman, Alessio
    Vulpio, Alessandro
    PROCEEDINGS OF THE ASME TURBO EXPO 2020: TURBOMACHINERY TECHNICAL CONFERENCE AND EXPOSITION, VOL 2E, PT I, 2020,
  • [35] Fault prediction of aircraft engine based on adaptive hybrid sampling and BiLSTM
    Junying Hu
    Xu Jiang
    Huan Xu
    Ke Zhang
    Scientific Reports, 15 (1)
  • [36] SUBISOKINETIC SAMPLING ERRORS FOR AIRCRAFT TURBINE-ENGINE SMOKE PROBES
    MARTONE, JA
    JOURNAL OF THE AIR POLLUTION CONTROL ASSOCIATION, 1978, 28 (06): : 607 - 609
  • [37] Analysis on Important Parameters Design of Aircraft
    Shang, Yongfeng
    CONSTRUCTION AND URBAN PLANNING, PTS 1-4, 2013, 671-674 : 2961 - 2964
  • [38] Coolant Injection System for Aircraft Engine Compressor
    Tudosie, Alexandru-Nicolae
    2019 20TH INTERNATIONAL CARPATHIAN CONTROL CONFERENCE (ICCC), 2019, : 169 - 174
  • [39] The engine mission simulation system: coupled simulation of aircraft and engine in the mission
    Remiger J.
    Stößel M.
    Kožulović D.
    Niehuis R.
    Krummenauer M.
    CEAS Aeronautical Journal, 2024, 15 (02) : 227 - 238
  • [40] Identification of linear model parameters and uncertainties for an aircraft turbofan engine
    Leibov, R
    JOURNAL OF GUIDANCE CONTROL AND DYNAMICS, 1997, 20 (06) : 1274 - 1275