The editors have assembled a world-class group of contributors who address the questions the combustion diagnostic community faces. They are chemists who identify the species to be measured and the interfering substances that may be present; physicists, who push the limits of laser spectroscopy and laser devices and who conceive suitable measuremen

Applied Combustion Diagnostics

Experimental investigation of the ignition process in a separated dual-swirl spray flame

Simple-jet mode electrosprays with water. Description, characterization and application in a single effect evaporation chamber

Measurement of the vapor-phase and liquid-phase fuel distributions downstream of an integrated flameholder in heated stream

Ignition, efficiency and emissions of RP-3 kerosene in a three-staged multi-injection combustor

This paper has focused on the droplets behavior of kerosene RP-3 spray produced by a pressure swirl atomizers in terms of spray pattern, droplet size spatial distribution, mean droplet size, and distribution index with variations of pressure differential. The analyses have been carried out experimentally with the aid of optical diagnostic methods. The spray pattern, such as spray cone angle and fuel spatial distribution, has been measured by the technique of planar laser induced fluorescence of kerosene. A method for correction of fuel distribution measurement error induced by laser attenuation in spray is proposed and validated. The droplet size spatial distribution in central axis plane of the spray has been measured by a planar droplet sizing method which combining laser induced fluorescence and Mie scattering. The spray pattern in axial center plane and cross-sectional plane perpendicular to axis of the atomizer indicate that the droplets in spray concentrate around the outer periphery and in a narrow annular zone at the near-field of fuel injector exit, and then disperse to produce a solid spray at downstream of the spray. The analyses of droplet size spatial distribution, Sauter mean diameter, and distribution index with pressure differential clearly show the presence of droplets collision and its adverse effects on droplet size uniformity. The spray outline, droplet mass spatial distribution, and droplet size spatial distribution, droplets dispersion and collision in the process of atomization provide a great insight into the processes of atomization and spray development, which are key information for fuel injector design and quality control. The visualizations of spray pattern and droplet size spatial distribution with variations of pressure differential for pressure swirl atomizer are key issues in swirl cup or internally staged airblast fuel injectors because pressure swirl atomizer provides primary atomization or pilot spray which affects the quality of air/fuel mixing in lean-burn combustion. Moreover, a well-defined and complete database regarding the isothermal hollow cone spray is provided for validation of spray model.

Experimental investigations of spray generated by a pressure swirl atomizer

Experimental Investigation of Spray and Combustion Performances of a Fuel-Staged Low Emission Combustor: Part I — Effects of Main Swirl Angle

This work focuses on optimizing the flame stability by matching the primary spray with swirling air streams in swirl cup which is used as pilot stage of a lean-burn fuel injector. Two configures of...

Improvement on ignition and lean blowout performances of a piloted lean-burn combustor:

An effect of the swirling flow on the combustion performance is studied by the computational fluid dynamics (CFD) in a micro-gas turbine with a centrifugal compressor, dump diffuser and forward-flow combustor. The distributions of air mass and the Temperature Pattern Factor (as: Overall Temperature Distribution Factor -OTDF) in outlet are investigated with two different swirling angles of compressed air as 0° and 15° in three combustors. The results show that the influences of swirling flow on the air distribution and OTDF cannot be neglected. Compared with no-swirling flow, the air through outer liner is more, and the air through the inner liner is less, and the pressure loss is bigger under the swirling condition in the same combustor. The Temperature Pattern Factor changes under the different swirling conditions.

Numerical study of effect of compressor swirling flow on combustor design in a MTE

The invention discloses a missile turbojet engine fast starting control device and method. Based on an evaporating pipe combustor, a swirl atomizer ignition oil way is added to an engine, the successive starting order of a plurality of accessories and the oil supply quantity of an oil pump are controlled, the oil supply law is given, and thus under low-temperature low-pressure environmental conditions in which the evaporating pipe type combustor is difficult to ignite, the engine can enter a high-rotation-speed stable operation state in a short time. The missile turbojet engine with the evaporating pipe type combustor reaches high rotation speed of 95% or above within 10 s. Through the missile turbojet engine fast starting control device and method, a reliable guarantee can be provided forstarting of the engine within a wide envelope range, the effect of fast starting of the missile turbojet engine is achieved, and significant engineering application value is achieved.

Chunyan Hu

Papers

Experimental investigations of spray generated by a pressure swirl atomizer

Experimental Investigation of Spray and Combustion Performances of a Fuel-Staged Low Emission Combustor: Part I — Effects of Main Swirl Angle

Improvement on ignition and lean blowout performances of a piloted lean-burn combustor:

Numerical study of effect of compressor swirling flow on combustor design in a MTE

Missile turbojet engine fast starting control device and method