When designing fans, it is essential to take intoaccount all specific features of their operationin real conditions. Determination of bypassratio influence on local flow parameters andintegral fan performance is a painstakingproblem. Presented is a method of calculatingsteady flow parameters, as well as turboenginefans performances.Design, computational and experimentalstudy of bypass scaled down stage model -prototype of a bypass-flow gearless fanincluding 3-4 booster stages for an advancedcivil aircraft engine has been performed.The calculations show perfect agreementvia comparison of numerical results withexperimental values at high efficiency levelwithin all operation range. Fan model (scaleddown version) meets its design goal ofperformance, flow capacity and surge margin inits first build. On test results, a decision wasaccepted to manufacture a full-size fan rotor inthe form of scaled model rotor.The work is organized with the aim ofcreating a scientific and technological potentialfor optimal designing and mathematicalmodeling physical processes, as well asexperimental investigations of aerodynamic andacoustic feature of new fans at special test rigs.Calculations of flow parameters and fanperformance were carried out for the reason ofmaking a choice of optimal versions atdesigning as well as expert examination ofmodel stages proposed for manufacturing andtesting. All experimental data are obtained at testing the fan model in the anechoic chamberof C-3A CIAM acoustic test facility.
展开▼
