| タイトル | Calculation of Multistage Turbomachinery Using Steady Characteristic Boundary Conditions |
| 本文（外部サイト） | http://hdl.handle.net/2060/19980017287 |
| 著者（英） | Chima, Rodrick V. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1998-01-01
1998 |
| 言語 | eng |
| 内容記述 | A multiblock Navier-Stokes analysis code for turbomachinery has been modified to allow analysis of multistage turbomachines. A steady averaging-plane approach was used to pass information between blade rows. Characteristic boundary conditions written in terms of perturbations about the mean flow from the neighboring blade row were used to allow close spacing between the blade rows without forcing the flow to be axisymmetric. In this report the multiblock code is described briefly and the characteristic boundary conditions and the averaging-plane implementation are described in detail. Two approaches for averaging the flow properties are also described. A two-dimensional turbine stator case was used to compare the characteristic boundary conditions with standard axisymmetric boundary conditions. Differences were apparent but small in this low-speed case. The two-stage fuel turbine used on the space shuttle main engines was then analyzed using a three-dimensional averaging-plane approach. Computed surface pressure distributions on the stator blades and endwalls and computed distributions of blade surface heat transfer coefficient on three blades showed very good agreement with experimental data from two tests. |
| NASA分類 | Aircraft Propulsion and Power |
| レポートNO | NASA/TM-1998-206613
E-11033
NAS 1.15:206613
AIAA Paper 98-0968 |
| 権利 | No Copyright |
