A fully three-dimensional compressible inverse design method for the design of radial and mixed flow turbomachines in described in this paper. Two approaches are presented for solving the compressible flow problem: approximate and exact approaches.
In this paper, the potential of a 3D inverse design method, in which the blade geometry is computed for a specified circulation distribution (directly related to blade loading), as a means of using the flow information obtained from CFD predictions and detailed measurements to effect systematic improvements in turbomachinery design has been explored.
To compare the performance of inducers with different blade loadings, a three-dimensional inverse design method was applied to control the blade loading distribution of inducers. This paper has been presented during the ASME 2002 Fluid Engineering Division Summer Meeting.
The application of the method is explored using a transonic test case, NASA rotor 67. From an understanding of the dynamics of the flow in the fan in relation to its pressure loading distributions,simple guidelines can be developed for the inverse method in
order to weaken the shock formation.
This paper presents the redesign of an electrically driven mixed flow transonic compressor by using a 3D Inverse Design methodology. The compressor will be used for an active high-lift system application that aims to delay the onset of stall.
The design of transonic multistage axial turbines and compressors of the type used in aero-engines and industrial gas turbines poses difficult and challenging problems to turbomachinery designers. In aero-engines, there is an increasing trend to reduce engine weight, which is only possible by increasing stage loading coefficient and reducing the axial spacing between the stages.