On the Formation of Nitrogen Oxides During the Combustion of ...

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C Design Details of Experiment Equipment An intrusive concept was chosen for the crucial steps of exhaust gas sampling during/after microgravity [293, 294, 296]. This gas sampling process was complemented by a gas analysis on the ground. The related exhaust gas sampling (EGS) setup is arranged in a compact manner on the fifth DCU platform (see Fig. 3.2, F). C.1 Key Data of Experimental Setup In addition to the general outline of the experiment, Table C.1 provides a systematic overview of weight and dimensions of the experimental setup broken down at the JCM and DCU levels. The DCU technically is the upper part of the “experiment deck”, which itself is the lowest circular baseplate [196, 208]. Table C.1: Weight and Dimensions of Experimental Setup. The overview shows the functional units hierarchically structured, as integrated in the TEXUS environment. The weight of the DCU is indicated including the “experiment deck” (i.e. common baseplate of JCM and DCU), which has a mass of 5kg itself. The inner diameter of the DCU vacuum protection is 377mm with a radial clearance of 2.5mm. Mass m Height h Diameter d in kg in mm in mm TEXUS-46 total payload 393.7 4979 438 TEXUS-46 scientific payload (all experiments) 291.0 3143 438 TEXUS nominal maximum scientific payload 270.0 3300 438 Japanese Combustion Module (JCM) 103.0 1290 403 Droplet Array Combustion Unit (DCU) 42.0 813 372 214
C.1 Key Data of Experimental Setup Depending on these figures and the rocket motor of the particular sounding rocket mission, the achievable apogee height is approximately 250 km with an available microgravity time of 6min. For the TEXUS-46 mission, launched on November, 22 nd , 2009, an apogee height of 252.3 km and a microgravity time of 388 s could be reached. Telemetry/Telecommand Parameters Table C.2 provides an overview of the telemetry/telecommand setup of the TEXUS-46 mission. The scan transmitter was used for self-configuration of the hook antennas that were mounted to the TEXUS service module. Table C.2: Overview of Telemetry/Telecommand System on TEXUS-46. Scan transmitter S-band 2295.0 MHz TV downlink S-band 2361.5 MHz Telemetry downlink S-band 2292.5 MHz Telemetry uplink 449.96 MHz 2 RS-232 9.6kBd 32 Analog channels 3×500 Hz (16bit), 29×5 Hz (16bit) 30 Digital channels 12 Discrete telecommands with JCM A special approach needed to be pursued for the video data of the cameras CCD1, CCD2, and CCD3 (see Chap. 3.2.3) with the sounding rocket setup. This was due to a limitation of TV downlink channels and in favor of redundancy. Figure C.1 shows the video/image flow scheme of the JCM. While all four camera images were channeled through umbilical cable during testing and flight preparation on the ground by switching the two RF relays (TVR1 and TVR2), only the signal of TVR1 was transmitted via TV downlink during sounding rocket flight. Therefore, a DV recorder documented the alternating video data of the cameras CCD3 and HSV directly on MiniDV tape. In the case of the HSV data, this was a backup solution, as the high-speed raw data was also kept in the volatile DRAM of the camera until payload recovery [196]. 215
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TECHNISCHE UNIVERSITÄT MÜNCHEN In
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Vorwort Die vorliegende Arbeit ents
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Kurzfassung Die vorliegende Arbeit
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Contents List of Figures List of Ta
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CONTENTS 5 Results 155 5.1 Droplets
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LIST OF FIGURES xiv 3.3 Droplet Arr
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LIST OF FIGURES 5.19 Progression of
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LIST OF TABLES C.2 Overview of Tele
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NOMENCLATURE g Gravitational force
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NOMENCLATURE σ S Surface tension N
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NOMENCLATURE () T Thermal, temperat
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NOMENCLATURE PAL PAN PDU PFA PFC PH
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1 Introduction In thermal engines t
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1 Introduction 1.3 Oxides of Nitrog
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1 Introduction residence time of th
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1 Introduction Chapter 3 describes
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2 Combustion Theory 2.1.1 Premixed
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2 Combustion Theory molecules by ea
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2 Combustion Theory four types. Out
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2 Combustion Theory ventional combu
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2 Combustion Theory of partial pre-
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2 Combustion Theory Formation of Fu
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2 Combustion Theory Moreover, exper
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2 Combustion Theory For the gas pha
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2 Combustion Theory combustion, ext
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2 Combustion Theory termed “natur
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2 Combustion Theory thin layer of u
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2 Combustion Theory nor generally c
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2 Combustion Theory is assumed to o
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2 Combustion Theory before it follo
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2 Combustion Theory position, which
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2 Combustion Theory 2.3 Kinetic Mod
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2 Combustion Theory 1.2 m s −1 La
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2 Combustion Theory Mole fraction o
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2 Combustion Theory Reburn Miller a
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2 Combustion Theory The results of
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2 Combustion Theory Temperature T 3
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2 Combustion Theory 0.0004 GRI 3.0
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2 Combustion Theory In conclusion,
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3 Experiments on Droplet Array Comb
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3.1 Droplet Combustion Facility and
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3.1 Droplet Combustion Facility C D
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3.1 Droplet Combustion Facility ous
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3.1 Droplet Combustion Facility for
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3.1 Droplet Combustion Facility par
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3.1 Droplet Combustion Facility The
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3.1 Droplet Combustion Facility a c
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3.1 Droplet Combustion Facility •
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3.1 Droplet Combustion Facility Tab
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3.1 Droplet Combustion Facility Fig
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3.2 Measurement Techniques and Data
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3.3 Numerical Study of the Fluid Dy
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4 Numerical Modeling and Simulation
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4.2 Basics for Numerical Modeling 4
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4.2 Basics for Numerical Modeling 4
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4.2 Basics for Numerical Modeling n
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4.2 Basics for Numerical Modeling P
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4.2 Basics for Numerical Modeling E
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4.3 Modeling of Ignition In the end
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4.3 Modeling of Ignition 10 W Time
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4.3 Modeling of Ignition Hence, the
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4.4 Modeling of Nitrogen Oxide Form
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4.5 Simulation of Single Droplets t
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4.5 Simulation of Single Droplets e
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4.6 Model Validation with index i
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4.6 Model Validation utilized model
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4.6 Model Validation Figure 4.7 dep
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4.6 Model Validation 340 K Ambient
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4.6 Model Validation Table 4.1: Val
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4.7 Scope and Limitations of Single
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4.7 Scope and Limitations of Single
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5 Results In total, it includes 99
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5 Results atmosphere of Figure 5.1
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5 Results 32 g kg −1 2400 K Emiss
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5 Results 4.0 g kg −1 Emission in
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Page 194 and 195: 5 Results Maximum temperature Tmax
Page 196 and 197: 5 Results Even though the parameter
Page 198 and 199: 5 Results Flame stand-off ratio ζ
Page 200 and 201: 5 Results 5.2.3 Comparison with Mic
Page 202 and 203: 5 Results 0.50 5000 ppm Emission in
Page 204 and 205: 5 Results Ψ = 0.1695 (t Ψ = 5 s):
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Page 210 and 211: 5 Results Flame stand-off ratio ζ
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Page 216 and 217: 5 Results A twofold trend was obser
Page 218 and 219: 5 Results 5.6 Recommendations and F
Page 221 and 222: 6 Summary and Conclusions In times
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Page 226 and 227: A Chemical Mechanisms The earliest
Page 228 and 229: A Chemical Mechanisms only deduced
Page 230 and 231: A Chemical Mechanisms Another, very
Page 232 and 233: A Chemical Mechanisms the reactions
Page 234 and 235: B Investigated Conditions There are
Page 236 and 237: B Investigated Conditions Table B.1
Page 238 and 239: B Investigated Conditions high mech
Page 242 and 243: C Design Details of Experiment Equi
Page 250 and 251: D Raw Data of Microgravity Experime
Page 256 and 257: SUPERVISED THESES Student Sebastian
Page 259 and 260: References [1] J.A. Aardenne van, G
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