摘要：

The multi-stage simulations of the GE90 turbofan primary flowpath components havebeen performed. The multistage CFD code, APNASA, has been used to analyze the fan,fan OGV and booster, the 10-stage high-pressure compressor and the entire turbinesystem of the GE90 turbofan engine. The code has two levels of parallel, and for the 18blade row full turbine simulation has 87.3% parallel efficiency with 121 processors on anSGI ORIGIN. Grid generation is accomplished with the multistage Average PassageGrid Generator, APG. Results for each component are shown which compare favorablywith test data.OrganizationThis document is a collection of several presentations, modified presentations (toeliminate GE proprietary information) and papers which have been written or presentedin support of this task order. They are arranged in the appendices which follow. Theyare: lip Appendix A: Parallel 3D Multi-Stage Simulation of a Turbofan Engine,presented at the 1998 NASA HPCCP/CAS workshop, August 25-27,1998 at the NASA Ames Research Center. Appendix B: Application of Multi-Stage Viscous Flow CFD Methods forAdvanced Gas Turbine Engine Design and Development, also presentedat the 1998 NASA HPCCP/CAS workshop, August 25-27, 1998 at theNASA Ames Research Center. Appendix C: GE90 Simulation which has been slightly modified fromthe presentation given at NASA Lewis Research Center on October 16,1998. Appendix D: "Multistage Simulations of the GE90 Turbine" paper whichwill be presented at the 1999 ASME IGTI conference. Appendix E: Excerpts from the 1999 IGTI scholar lecture paper by JohnJ. Adamczyk "Aerodynamic Analysis of Multistage TurbomachineryFlows in Support of Aerodynamic Design." Appendix F: Combustor Analysis description for the efforts to model thecombustor in APNASA with source terms. This approach was laterreplaced by a simple boundary condition treatment for representingcombustor profiles.

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