Apu eductor plenum flow stability splitter

An aircraft in part comprising:

• an auxiliary power unit (APU) having a gas turbine engine and a load compressor, said APU mounted in a compartment having an intake duct for ambient air, the intake duct connected to provide the ambient air to the load compressor, the gas turbine engine as combustion air and an oil cooler for the gas turbine engine as cooling air, and an exhaust duct;
• an eductor assembly having an eductor housing and the oil cooler is mounted to an cooling airflow inlet of the eductor housing to receive flow of cooling air from the oil cooler, said eductor housing further having a turbine exhaust inlet opening receiving exhaust gases from the gas turbine engine, the cooling airflow inlet and the turbine exhaust inlet opening fluidly connected through a primary plenum to an outlet opening in the eductor housing, the outlet opening connected to the exhaust duct;
• and,
• a splitter plate positioned in the primary plenum fixing a stagnation point with respect to a wall of the primary plenum.

A method stabilizing a stagnation point in an eductor housing and enhancing mixing of gas turbine exhaust gases, oil cooler cooling air and surge bleed flow, the method comprising:

• receiving a flow of exhaust gases from a gas turbine engine of an APU through an exhaust gas inlet opening in an eductor housing;
• receiving cooling air from an oil cooler for the gas turbine engine through a cooling airflow inlet in the eductor housing, the cooling airflow inlet parallel to a first diametric plane of an annular volume of a primary plenum, the annular volume and exhaust gas inlet opening concentric about a longitudinal axis in the eductor housing;
• and
• inducing a stagnation point in air flow in the primary plenum with a splitter plate located on a wall of the primary plenum in a second diametric plane of the annular volume.