Project number
16032
Organization
Honeywell Aerospace
Academic year
2016-2017
The project team analyzed the effects of free versus forced vortex flow in a jet engine. To conduct the analysis, cooling vanes and blades were integrated on the stationary and rotating discs of a mock jet turbine engine.
The blades and vanes were adjusted during the integration to achieve different aerodynamic properties that resulted in changes to internal cavity pressure and velocity. Data collected using airflow velocity anemometers and pressure transducers was analyzed to determine internal cavity behavior in a free or forced vortex relationship.
The relationship between the integrated blades and vanes and the vortex discovered during testing provides critical data for optimizing turbine main cavity pressure, and for maximizing overall engine efficiency and performance.
The blades and vanes were adjusted during the integration to achieve different aerodynamic properties that resulted in changes to internal cavity pressure and velocity. Data collected using airflow velocity anemometers and pressure transducers was analyzed to determine internal cavity behavior in a free or forced vortex relationship.
The relationship between the integrated blades and vanes and the vortex discovered during testing provides critical data for optimizing turbine main cavity pressure, and for maximizing overall engine efficiency and performance.