The purpose of combustion chamber is to
increase the thermal energy of the flowing gas
stream which is an exothermic chemical
reaction.
Reference : Air craft engine design by Mattingly
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This is project presentation for Physics course. Instructor and project supervisor was Prof. Alpana Vishvajit at Aliah University. It includes: Combustion, Chamber, Thermal, Energy, Exothermic, Chemical, Reaction, Annular, Can-annular
Typology: Slides
2011/2012
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The purpose of combustion chamber is to increase the thermal energy of the flowing gas stream which is an exothermic chemical reaction.
Reference : Air craft engine design by Mattingly
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Three types Annular type Can type Can annular
Reference : Gas turbine theory by Rogers
Can type combustion chamber
This type of chamber consists of
individual combustion chambers
arranged in such a way that the air from
the compressor enters each individual
chamber.
Each individual chamber consists
of two cylindrical tubes.
Combustion chamber liner
Outer combustion chamber
Reference : Gas turbine theory by Rogers
Inflowing air enters the main burner at station 3.1. The air flow is diffused at station 3.2. A snout stabilizes the diffusing airstream and divides it for distribution to liner and annulus. The central part of the divided airstream flows through an air swirler into the primary zone.
Reference : Air craft engine design by Mattingly
It mixes with fuel. The remaining air flows into the inner and outer annulus. Then flows into the liner through various holes and cooling slots. From primary zone the mixture of partially mixed and incomplete gases flows downstream into secondary zone.
Reference : Air craft engine design by Mattingly
Dilution zone is that any remaining annulus flow be dumped through dilution holes into liner hot gas stream.
Also to avoid hot spots.
Reference : Air craft engine design by Mattingly
About 15-20 per cent of the air is introduce around the jet of fuel in primary zone to provide necessary high temperature for rapid combustion.
Some 30 per cent of total air is then introduced through holes in secondary zone to complete combustion.
Complete combustion Low pressure loss Proper temperature distribution at exit Short length and cross section Stability of combustion process
Reference : Element of gas turbine by Mattingly
Diffuser
Primary zone
Secondary zone
Dilution zone
Reference : Thesis by Zaid Rahim
Diffuser To reduce velocity of air exiting the compressor.
Snout Divides air into two streams primary air and secondary air.
Reference : Element of gas turbine by Mattingly
Liner The liner contains the combustion process and introduced the various airflows (intermediate, dilution, and cooling air ) into the combustion zone.