Measurements of fractional and chemical composition of non-volatil particles in emission products of aviation engine combustion chambers

2016 ◽  
Vol 29 (6) ◽  
Keyword(s):  
Chemical Composition ◽  
Combustion Chambers ◽  
Engine Combustion

Modelling of Spray–Swirl Interaction in Direct Injection Diesel Engine Combustion Chambers

1985 ◽  
Vol 199 (3) ◽  
pp. 187-198 ◽  
Author(s):  
P S Mehta ◽  
A K Gupta
Keyword(s):  
Diesel Engine ◽  
Fuel Injection ◽  
Direct Injection ◽  
Three Dimensional ◽  
Combustion Chambers ◽  
Direct Injection Diesel Engine ◽  
Wide Range ◽  
Engine Combustion ◽  
Computation Scheme ◽  
Good Agreement

A mathematical model for predicting spray–swirl interaction in a direct injection diesel engine combustion chamber is developed using centre-line velocity vector/continuum approach. The model has three-dimensional features in fuel spray motion. The present model responds to the various air swirl, fuel injection and cylinder charge conditions. The predicted results are compared with the analytical and experimental data available from various sources in the two-dimensional case. Very good agreement is achieved over a wide range of data. The three-dimensional predictions are directly possible without any alteration in the computation scheme.

Predicting the Performance of Diesel Engine Combustion Chambers

1969 ◽  
Vol 184 (10) ◽  
pp. 241-299 ◽  
Author(s):  
D. B. Spalding
Keyword(s):  
Heat Transfer ◽  
Diesel Engine ◽  
Numerical Analysis ◽  
Finite Difference ◽  
Fluid Dynamic ◽  
Combustion Chambers ◽  
Piston Motion ◽  
Engine Combustion ◽  
Growth Of Knowledge ◽  
Dynamic Heat Transfer

The availability of large digital computers, the recent development of adequate techniques of numerical analysis, and the growth of knowledge about the laws of turbulence, have combined to make possible the development of a comprehensive prediction procedure for the fluid-dynamic, heat transfer and combustion phenomena which take place in diesel engine combustion chambers. The difficulties, and means of surmounting them, are discussed in the lecture; it is argued that a very useful first stage would be a procedure applicable to axisymmetrical chambers; this could be constructed by extending already established techniques and knowledge. The procedure would be of the finite difference variety, and would employ a grid which expanded and contracted to accord with the piston motion.

An Ionization Probe Study of Small Engine Combustion Chambers

1976 ◽  
Author(s):  
Steven A. Johnson ◽  
David B. Kittelson ◽  
Thomas E. Murphy
Keyword(s):  
Combustion Chambers ◽  
Engine Combustion ◽  
Ionization Probe

Generic Geometry Definition of the Aircraft Engine Combustion Chamber

2004 ◽  
Author(s):  
Savad A. Shakariyants ◽  
Jos P. van Buijtenen ◽  
Wilfried P. J. Visser
Keyword(s):  
Combustion Chamber ◽  
Aircraft Engine ◽  
Working Environment ◽  
Combustion Chambers ◽  
Turbofan Engine ◽  
Empirical Relations ◽  
Size Constraints ◽  
Engine Combustion ◽  
Definition Of ◽  
Aircraft Application

The type and layout of a particular gas turbine combustion chamber are largely determined by engine specifications and, peculiarly for the aircraft application, by the effort to use the available space as effectively as possible. Therefore, large commercial turbofan engine combustors exhibit a great degree of commonality. This commonality is a result of the similarity in working environment, size constraints and also safety, performance, and weight requirements. The objective of the present work is to propose generic relations between combustor overall performance and geometry, in order to develop accurate models for combustion quality and emission studies. Therefore, an algorithm has been developed to produce a generic combustion chamber layout. The algorithm is based on a set of empirical relations, semi-analytical methods, statistical figures and design philosophy. Results have been validated in a case study, showing accurate correspondence with modern turbofan engine combustors. An alternate application of the models may be preliminary sizing or design of aero-engine combustion chambers.

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