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Flow Analysis of a Gas Turbine Low-Pressure Subsystem
This project coordinated by NASA Lewis Research Centre, numerically simulates aerodynamic flow in the complete low-pressure (LPS) of a gas turbine engine. The numerical model solves the three-dimensional Navier-Stokes flow equations through all components within the LPS as well as the external flow around the engine nacelle.
Low-pressure subsystem computational mesh.
This engine includes a low pressure system and a high-pressure system. An inlet, a fan, a booster stage, a bypass duct, a lobed mixer, a low-pressure turbine, and a jet nozzle comprise the low-pressure subsystem within this engine. The tightly coupled flow analysis evaluates aerodynamic interactions between all components of the LPS. The high-pressure core engine of this engine is simulated with one-dimensional thermodynamic cycle code in order to provide boundary conditions to the detailed LPS model. This core engine consists of a high pressure compressor, a combustor, and a high-pressure turbine.
The three-dimensional LPS flow model is coupled to a one-dimensional core engine model to provide a "hybrid" flow model of the complete gas turbine Energy Efficient Engine.
cut away view of the Energy Efficient Engine showing the fan and low-pressure turbine. The three-dimensional flow solution is superimposed onto the turbomachinery blades of the low-pressure subsystem and compared with test data.
The Navier-Stokes modeling of the large, low-pressure subsystem provides detailed knowledge of the between its components. These interactions effects can be critical to engine performance.
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