sign. The annular combustion chamber permits building an engine of a
small and compact design. Instead of individual combustion chambers,
the primary compressed air is introduced into an annular space formed
by a chamber liner around the turbine assembly. A space is left
between the outer liner wall and the combustion chamber housing to
permit the flow of secondary cooling air from the compressor.
Primary air is mixed with the fuel for combustion. Secondary
(cooling) air reduces the temperature of the hot gases entering the
turbine to the proper level by forming a blanket of cool air around
these hot gases.
The annular combustion chamber offers the advantages of a
larger combustion volume per unit of exposed area and material
weight, a smaller exposed area resulting in lower pressure losses
through the unit, and less weight and complete pressure equalization.
b. The
cantype
combustion chamber is one made up
of individual combustion
chambers.
This type of
combustion chamber is so arranged
that air from the compressor
enters each individual chamber
through the adapter. Each
individual chamber is composed of
two cylindrical tubes, the
combustion chamber liner and the
outer combustion chamber, shown
in figure 1.19. Combustion takes
place within the liner. Airflow
into the combustion area is
controlled by small louvers
located in the inner dome, and by
round holes and elongated louvers
along the length of the liner.
Airflow into the combustion area
is controlled by small louvers
located in the inner dome, and by
Figure 1.19. Cantype Combustion
round holes elongated louvers
Chamber (Cutaway).
along the length of the liner.
Through these openings flows the air that is used in combustion and
cooling. This air also prevents carbon deposits from forming on the
inside of the liner. This is important, because carbon deposits can
block critical air passages and disrupt airflow along the liner walls
causing high metal temperatures and short burner life.
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