Lire la première partie

Felix Jaegle

Description

Niveau: Supérieur, Doctorat, Bac+8
Lire la première partie de la thèse

• transparent view


• reacting test bench


• fuel injection


• main stage bowl


• counter-rotating relative


• swirler


• pilot bowl


• swirler can


• swirler channels

Sujets

• Combustión
• Snecma
• Fuel injection

Informations

• Publié par: profil-zyak-2012
• Nombre de lectures: 26
• Langue: English
• Poids de l'ouvrage: 5 Mo

Extrait

Lire
la première partie
de la thèsePart IV
Application to an aeronautical
multipoint injector
181Chapter 9
Description of the TLC configuration
Contents
9.1 Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183
9.2 The SNECMA staged premixing swirler . . . . . . . . . . . . . . . . 183
9.2.1 Geometry . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 183
9.2.2 Injection of liquid fuel . . . . . . . . . . . . . . . . . . . . . . . . . . . . 185
9.3 The ONERA non-reacting test bench . . . . . . . . . . . . . . . . . . 185
9.3.1 Measurement methods . . . . . . . . . . . . . . . . . . . . . . . . . . . . 186
9.4 The numerical setup. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 187
9.4.1 Modifications of the original geometry . . . . . . . . . . . . . . . . . . . 187
9.4.2 The computational grid . . . . . . . . . . . . . . . . . . . . . . . . . . . 188
9.1 Introduction
Thefinalapplicationofthisthesisisanaeronauticalpremixingswirlerwithmultipointinjection.
ThisdeviceisaprototypemanufacturedbySNECMAmoteurs,andhasbeensubjecttoseveral
experimental and numerical studies in the TLC (for “Towards Lean Combustion”) project of
the 6th framework programme of the European Union. The configuration is therefore referred
to as “TLC configuration”throughout this manuscript.
9.2 The SNECMA staged premixing swirler
9.2.1 Geometry
An isolated, cut-away view of the premixing swirler is shown in figure 9.1. It represents one of
around 20 injectors that are typically mounted on the upstream wall of an annular combustion
chamber of an aero-engine. It is a staged design with the objective to divide fuel injection and
premixing in two separatly controllable zones, in order to allow the optimization of the system
for different operating points (see chapter 1 for a detailed explanation). The device is thus
composed of two stages, that can be identified by two conical “bowls”, where the central, pilot
bowl is nested inside the main stage bowl.
183184 CHAPTER 9. DESCRIPTION OF THE TLC CONFIGURATION
24 multipoint
injectors! Pilot injector!
Fuel
admission!
Pilot stage bowl!
Main stage bowl!
Figure 9.1: Staged premixing swirler, cut-away view.
Theairtraversestheconfigurationfromtheplenumthroughaseriesofswirlers,anarrangement
of channels, divided by guide vanes, that are inclined relative to the main axis and impose
a swirling motion to the flow. Figure 9.2 presents a transparent view, highlighting the three
swirler stages. Two are of radial type and lead into the pilot bowl. While the innermost swirler
dischargesintothepilotbowlatitsupstreamend,theflowfromthesecondoneentersthebowl
troughacircularslotinthesidewalljustbeforethepilotflowexitsintothechamber. Thethird
swirler can be considered to be of radial type, although it is slightly inclined, leading the flow
into the main stage bowl with a non-zero axial velocity component. All three swirler stages are
counter-rotatingrelativetoeachone’sneighbour,whichpromotesturbulentmixingintheareas
where the flows meet.
Counter-rotating
pilot stage !
swirler channels!
Main stage!
swirler channels!
Figure 9.2: Staged premixing swirler, transparent view with highlighted swirler channels.
The bulk of the airflow (approx. 90 %) passes through the main swirler stage. The remaining
10 % is divided between the innermost pilot swirler (3 %) and the outer pilot swirler (7%).9.3. THE ONERA NON-REACTING TEST BENCH 185
9.2.2 Injection of liquid fuel
Liquid fuel is fed into the injector via two separate circuits, which are well visible in figure
9.1. One is connected to the pilot injector, which creates a hollow-cone spray. The pilot fuel
atomizer is of the so-called piezo type, featuring a ring of very small orifices on a cone-shaped
injector head. The second circuit leads to the multi-point injection system of the main stage,
a series of 24 holes located on the inner wall of the main stage, each placed just downstream
of a swirler channel’s exit. At each point, liquid fuel is injected perpendicularly to the surface
through orifices of 0.5mm in diameter.
The partition of fuel mass fluxes between the pilot stage an the swirler stage can be used as
a tool to optimize local equivalence ratio values for different phases of flight. Throughout the
present work, the pilot stage will be completely deactivated in order to study the phenomena
related to multipoint injection in an isolated way. This, of course, is not a realistic operation
condition and only used in the framework of an academical study.
9.3 The ONERA non-reacting test bench
For measurement purposes, the inector described in the preceding section was mounted on var-
ious test benches. These include a completely open setup (with the inejctor directly exiting
into the atmosphere) that has been studied experimentally at ONERA DMAE in Toulouse
and numerically by Lavedrine [81]. A configuration adapted to reactive experiments has been
studied experimentally at ONERA DMPH in Palaiseau [105]. Numerical simulations have been
performedbyLavedrine[81]innon-reactingconditionsandbyBertier[14]inreactingconditions.
Figure 9.3: Photography of the installation at the ONERA Fauga-Mauzac center.
In the present work, a third configuration is considered. It was mounted at the ONERA center
at Fauga-Mauzac and allows a detailed study of the non-reacting, two-phase flow [82]. The
test bench, pictured in figure 9.3 allows to pressurize and pre-heat the chamber, which is of a
simple rectangular shape with a square cross-section, where large observation windows provide
optical access for measurements. Air enters through an admission duct that expands into a186 CHAPTER 9. DESCRIPTION OF THE TLC CONFIGURATION
Staged premixing swirler!
Plenum!
Chamber!
Outlet nozzle!
Figure 9.4: TLC configuration ONERA Fauga-Mauzac
plenum. The injector is mounted on the dividing wall between this plenum and the chamber.
Additionally, this divider is perforated to feed air into cooling films exiting into the chamber at
about half the distance between the injector outer diameter and the lateral chamber walls (see
figure 9.5). It has to be noted that this film serves no real purpose in the present configuration.
It is a remnant of the reacting test bench, where these films are located in direct proximity of
thelateralwallsandserveasacoolinglayertoprotecttheopticalaccesswindows. Thechamber
exit is formed by a nozzle that reaches supersonic flow at the throat, leading to an acoustically
non-reflecting outflow.
Figure 9.5: TLC configuration ONERA Fauga-Mauzac - view from the plenum
9.3.1 Measurement methods
The test bench was equipped for different measurement techniques briefly described in the
following. The goal of these measurements was to obtain data on:
• The gaseous phase velocity, using a LDA technique9.4. THE NUMERICAL SETUP 187
• The droplet velocity and diameter, using a PDA technique
• The local droplet size distribution, using laser diffraction spectroscopy
• The spatial distribution liquid volume flux, using a patternator technique
The LDA (for Laser Doppler Anemometry) measurement method uses a pair of coherent laser
beams that are crossed at the location where velocity data is measured. At this location, the
beams form interference fringes, which illuminate particles that cross the pattern periodically.
The frequency of this light signal can be detected and translated into a velocity. This value
corresponds to the velocity component perpendicular to the fringes and the measurement has
to be repeated to obtain other velocity components. The gaseous flow is seeded with particles
of a very low Stokes number in order to minimize errors due to droplet inertia and to exclude
two-way coupling effects.
ThePDA(forPhaseDopplerAnemometry)isanextensionoftheLDAtechnique,firstproposed
by Durst et al. [40], that uses two detectors for the light scattered by the particles, arranged
at different locations in space. The resulting phase shift between both doppler signals can be
translated into a diameter information of the recorded particle.
The laser diffraction spectroscopy uses a laser beam to illuminate the spray. For a single
droplet, in close forward direction, diffraction patterns are observed that can be related to the
size of a spherical particle using Mie theory [95]. For a polydisperse spray, a complex light
intensity distribution is recorded, which can be translated into a droplet size distribution using
methodsdescribedbyHirleman[62]. Theadvantageofthistechniqueisthatthedistributionis
obtained instantaneously, from the post-processing of a single image.
Thepatternator technique is based on the verysimple principle of placingan array of recip-
ients in the direction of spray movement. The spatial distribution of liquid volume flux can be
reconstructed by the amount of liquid that is present in each of the recipients.
For additional information, the reader is referred to the TLC report [82] and for theoretical
background to the book of Frohn and Roth [47].
9.4 The numerical setup
9.4.1 Modifications of the original geometry
Modifications are made relative to the original geometry in order to make it suitable for com-
putations. These modifications comprise:
• The air exits the chamber through a supersonic nozzle. In order to render the supersonic
boundary condition more stable, the narrowest section is followed by a short, gentl