In a gas turbine engine testing facility, the engine draws air in from the surrounding environment through a large inlet. This process entrains additional flow beyond that which goes through the engine. Downstream of the engine, the engine exhaust and this entrained flow both enter a long cylindrical flow channel during which the two streams partially mix. Further downstream the flow diffuses and impinges on a conical flow redirection device (cone) before exiting into an exhaust stack via a perforated cylinder. This project aims to develop solutions and new insight related to reducing undesired large amplitude, low frequency pressure fluctuations in the exhaust stream of a gas turbine engine testing facility. The analysis will be carried out using high fidelity numerical simulations of unstead fluid flow such as a large eddy simulation. Solutions will be investigated by identifying how best to model the unsteady pressure fluctuations numberically and then determining how changes to the geometry of existing facility components can best reduce the pressure fluctations. Simultaneously, the phsyical mechanisms driving the pressure fluctuations will be firmly established and solutions based on reducing the ultimate source of the unsteadiness will be proposed. Thse may be more substantial than simply changing existing facility component geometry and thus will serve as backup solutions if the fluctuations cannot be adequately reduced via simple component geometry changes.

Industry Partner(s):MDS Aero Support Corp.

Academic Institution:University of Windsor

Academic Researcher: Jeff Defoe

Focus Areas: Advanced Manufacturing

Platforms: Parallel CPU