In order to balance the low emission and wide stabilization for lean premixed prevaporized (LPP) combustion, the centrally staged layout is preferred in advanced aero-engine combustors. However, compared with the conventional combustor, it is more difficult for the centrally staged combustor to light up as the main stage air layer will prevent the pilot fuel droplets arriving at igniter tip. The goal of the present paper is to study the effect of the main stage air on the ignition of the centrally staged combustor. Two cases of the main swirler vane angle of the TeLESS-II combustor, 20 deg and 30 deg are researched. The ignition results at room inlet temperature and pressure show that the ignition performance of the 30 deg vane angle case is better than that of the 20 deg vane angle case. High-speed camera, planar laser induced fluorescence (PLIF), and computational fluids dynamics (CFD) are used to better understand the ignition results. The high-speed camera has recorded the ignition process, indicated that an initial kernel forms just adjacent the liner wall after the igniter is turned on, the kernel propagates along the radial direction to the combustor center and begins to grow into a big flame, and then it spreads to the exit of the pilot stage, and eventually stabilizes the flame. CFD of the cold flow field coupled with spray field is conducted. A verification of the CFD method has been applied with PLIF measurement, and the simulation results can qualitatively represent the experimental data in terms of fuel distribution. The CFD results show that the radial dimensions of the primary recirculation zone of the two cases are very similar, and the dominant cause of the different ignition results is the vapor distribution of the fuel. The concentration of kerosene vapor of the 30 deg vane angle case is much larger than that of the 20 deg vane angle case close to the igniter tip and along the propagation route of the kernel, therefore, the 30 deg vane angle case has a better ignition performance. For the consideration of the ignition performance, a larger main swirler vane angle of 30 deg is suggested for the better fuel distribution when designing a centrally staged combustor.

References

References
1.
Mongia
,
H. C.
, and
Dodds
,
W.
,
2004
, “
Low Emissions Propulsion Engine Combustor Technology Evolution Past, Present and Future
,” 24th Congress of International Council of the Aeronautical Sciences, Yokohama, Japan, Aug. 29-Sept. 3, Paper No.
ICAS
2004-609.
2.
Mongia
,
H. C.
,
2003
, “
TAPS-A 4th Generation Propulsion Combustor Technology for Low Emissions
,”
AIAA
Paper No. 2003-2657.
3.
Lazik
,
W.
,
Doerr
,
T.
, and
Bake
,
S.
,
2007
, “
Low NOx Combustor Development for the Engine 3E Core Engine Demonstrator
,” XVIII International Symposium on Air Breathing Engines (ISABE), Beijing, China, Sept. 2–7, Paper No. 2007-1190.
4.
A.
Horikawa
, and
Kinoshita
,
Y.
,
2011
, “
Improvement on Ignition Performance for a Lean Staged Low NOx Combustor
,”
ASME
Paper No. GT2011-46187.
5.
Fu
,
Z. B.
, and
Lin
,
Y. Z.
,
2011
, “
Experimental Investigation on Ignition Performance of Less Combustor
,”
ASME
Paper No. GT2011-45786.
6.
Lefebvre
,
A. H.
,
2010
,
Gas Turbine Combustion
,
CRC Press, Taylor & Francis
,
New York
.
7.
Ballal
,
D. R.
, and
Lefebvre
,
A. H.
,
1981
, “
General Model of Spark Ignition for Gaseous and Liquid Fuel/Air Mixtures
,”
Symp. (Int.) Combust.
,
18
(1), pp.
1737
1746
.
8.
Dhanuka
,
S. K.
,
Driscoll
,
J. F.
, and
Mongia
,
H. C.
,
2008
, “
Instantaneous Flow Structures in a Reacting Gas Turbine Combustor
,”
AIAA
Paper No. 2008-4683.
9.
Dhanuka
,
S. K.
,
Temme
,
J. E.
,
Driscoll
,
J. F.
,
Foust
,
M. J.
, and
Lyle
,
K. H.
,
2010
, “
Unsteady Aspects of Lean Premixed-Prevaporized (LPP) Gas Turbine Combustor: Flame–Flame Interactions
,”
AIAA
Paper No. 2010-1148.
10.
Lazik
,
W.
,
Doerr
,
T.
,
Bake
,
S.
,
Bank
,
R. V. D.
, and
Rackwitz
,
L.
,
2008
, “
Development of Lean-Burn Low-NOx Combustion Technology at Rolls-Royce Deutschland
,”
ASME
Paper No. GT2008-51115.
11.
Yamamoto
,
T.
,
Shimodaira
,
K.
,
Urosawa
,
Y.
,
Mastuura
,
K.
,
Iino
,
J.
, and
Yoshida
,
S.
,
2009
, “
Research and Development of Staging Fuel Nozzle for Aeroengine
,”
ASME
Paper No. GT2009-59852.
12.
Ahmed
,
S. F.
,
2014
, “
The Probabilistic Nature of Ignition of Turbulent Highly-Strained Lean Premixed Methane-Air Flames for Low-Emission Engines
,”
Fuel
,
134
, pp.
97
106
.
13.
Wang
,
X. F.
, and
Lin
,
Y. Z.
,
2014
, “
Effect of Swirl Cup's Venturi Shape on Spray Structure and Ignition Process
,”
ASME
Paper No. GT2014-25216.
14.
Soworka
,
T.
,
2014
, “
Numerical Investigation of Ignition Performance of a Lean Burn Combustor at Sub-Atmospheric Conditions
,”
ASME
Paper No. GT2014-25644.
15.
Myers
,
G. D.
, and
Lefebvre
,
A. H.
,
1986
, “
Flame Propagation in Heterogeneous Mixtures of Fuel Drops and Air
,”
Combust. Flame
,
66
(
2
), pp.
193
210
.
16.
Baranger
,
P.
,
Orain
,
M.
, and
Grisch
,
F.
,
2005
, “
Fluorescence Spectroscopy of Kerosene Vapour: Application to Gas Turbines
,”
AIAA
Paper No. 2005-828.
17.
Mongia
,
H. C.
,
2008
, “
Recent Progress in Comprehensive Modeling of Gas Turbine Combustion
,”
AIAA
Paper No. 2008-1445.
You do not currently have access to this content.