A correlation method has been developed for predicting the temperature field produced by a single row of closely-spaced jets penetrating into a hot confined crossflow. The correlation procedure predicts the temperature field as a function of the distance downstream of the jet injection plane and pertinent geometric and flow variables. Predicted results are compared with measured data. The tests are selected to represent combinations of geometries or flow variables which give strong verification of the correlations and which are pertinent to gas turbine engine combustor design.

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Causes of exit temperature nonuniformity in the primary combustion system of the F100 augmented turbofan engine have been identified and investigated in a comprehensive test program. This test program involved a combination of instrumented full engine, annular combustor rig, and subscale component rig tests. Modifications to the fuel nozzle, which provide significant improvements in combustor exit temperature uniformity, are now being incorporated into the production version of the engine. Modifications to the combustor configuration are being incorporated into growth versions of the engine.

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