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A numerical analysis of 3-D inviscid stator/rotor interactions using non-reflecting boundary conditions

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Show simple item record Saxer, André P. (André Pierre) en_US
dc.contributor.other Massachusetts Institute of Technology. Gas Turbine Laboratory en_US 2016-10-06T21:22:33Z 2016-10-06T21:22:33Z 1992 en_US
dc.description March 1992 en_US
dc.description Includes bibliographical references (pages 230-239) en_US
dc.description.abstract This dissertation presents a method for the computation of three-dimensional inviscid, transonic steady and unsteady flows, primarily in axial flow turbines. The work is divided into two major contributions. The first is an algorithm for the solution of the 3-D Euler equations which incorporates a second-order accurate numerical smoothing for non-uniform grids and steady-state non-reflecting boundary conditions. Fourier analysis applied to the linearized Euler equations is used to develop novel quasi-3-D non-reflecting boundary conditions at the inflow/outflow and at the stator/rotor interface. The accuracy, effectiveness and robustness of the boundary condition formulation is demonstrated through several subsonic and transonic test cases and through comparison with the standard 1-D formulation. The second contribution consists in the study of three specific flow phenomena occurring in an axial flow turbine. en_US
dc.description.abstract First, the steady-state effects of an inlet spanwise stagnation temperature gradient in a transonic stage are analyzed. The mechanism for the migration of the temperature as well as the extent of the non-uniformity are assessed. Then, the secondary flow produced by a combined thermal and vortical inlet distortion on a downstream moving rotor is studied. The extent of the radial mixing for steady and unsteady flow is assessed as a function of the strength of the inlet disturbance. The third case is an analysis of the steady, unsteady and time-averaged flow fields in a highly loaded industrial transonic turbine stage. In particular, the unsteady shock interaction due to the impact of the stator trailing edge shock wave off the downstream rotor is studied. From the last two cases it is concluded that in many aspects the time-averaged results are extremely close to the steady-state values, even with strong unsteady shock interaction. en_US
dc.description.abstract For each case the mechanisms for the creation of the secondary flow and deviations from a steady, uniform inlet conditions flow field are presented and analyzed. en_US
dc.format.extent 303 pages en_US
dc.publisher Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1992] en_US
dc.relation.ispartofseries GTL-209 en_US
dc.relation.ispartofseries GTL report #209 en_US
dc.subject.lcc QA911 .S29 1992 en_US
dc.subject.lcc TJ778.M41 G24 no.209 en_US
dc.subject.lcsh Lagrange equations -- Numerical solutions en_US
dc.subject.lcsh Gas-turbines -- Fluid dynamics -- Mathematical models en_US
dc.title A numerical analysis of 3-D inviscid stator/rotor interactions using non-reflecting boundary conditions en_US
dc.type Technical Report en_US
dc.identifier.oclc 26759376 en_US
dc.identifier.oclc 60285299 en_US

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