Abstract
Flow characteristics in the outer annulus and its effects on the flow splits through different liner holes have been established by conducting experiments on a full annulus prototype reverse-flow gas turbine combustor for different intensities of swirl imposed on the inlet flow. Measurements have been taken with a direction-sensitive pressure probe and a standard hot wire probe. It is seen that imposition of swirl improves the uniformity of outlet flow in θ-plane. It is observed that the flow split through the turn-section cooling holes and primary holes remains nearly constant up to S=0.55, while the split through the dilution holes decreases. With increase in the swirl intensity (S=0.84) the flow split through the turn-section and dilution holes increases while flow split through the primary holes reduces. The turbulence intensity level at the outlet is not affected by the imposed inlet swirl.
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