Application of a three-dimensional viscous transonic inverse method to NASA rotor 67

Abstract

The development and application of a three-dimensional inverse methodology in which the blade geometry is computed on the basis of the speci cation of static pressure loading distribution is presented. The methodology is based on the intensive use of computational uid dynamics (CFD) to account for three-dimensional subsonic and transonic viscous ows. In the design computation, the necessary blade changes are determined directly by the discrepancies between the target and initial values, and the calculation converges to give the nal blade geometry and the corresponding steady state ow solution. The application of the method is explored using a transonic test case, NASA rotor 67. Based on observations, it is conclusive that the shock formation and its intensity in such a high-speed turbomachinery ow are well de ned on the loading distributions. Pressure loading is therefore as effective a design parameter as conventional inverse design quantities such as static pressure. Hence, from an understanding of the dynamics of the ow 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. A qualitative improvement in performance is achieved in the redesigned fan. The nal ow eld result is con rmed by a well-established commercial CFD package.

Aerodynamic Inverse Design of Transonic Compressor Cascades with Stabilizing Elastic Surface Algorithm

“…In addition, Tiow et al [43] redesigned the NASA rotor 67 transonic fan using a threedimensional inverse design method and applied the average swirling velocity distribution of the flow as a target function. They focused on the near-blade shock, the interaction of shock and boundary layer, and the tip leakage, and applied a three-dimensional viscous CFD solver based on the finite volume method.…”

Implementation of Three-Dimensional Inverse Design and Its Application to Improve the Compressor Performance

“…It further helped to understand more details of the internal flow in turbomachinery. Dang, Isgro, Damle, and Qiu and Tiow and Zangeneh developed inverse design methods based on permeable or transpiring models [5][6][7]. In their inverse design methods, the blade surfaces were regarded to be permeable and flexible where the normal velocity was allowed to exist during the inverse design process.…”

Picard–Newton iterative algorithm to solve the potential flow equation for different turbomachinery flow regimes

“…These methods are based on the flow properties and dynamics, and other aspects like mechanical properties of the blades are not included; hence, the final blade shapes can sometimes be unphysical or impractical in reality. Different approaches are already developed by several researchers [4][5][6][7][8]. Determining the isentropic velocity field consists the first step of the inverse design of turbomachinery blade profiles.…”