Patent ID: 8696306
Filing Date: 2014-04-15
Classification: F01D,F02K,F04D,F05D

Abstract:
1. A bypass duct of a turbofan engine comprising: a guide blade ring including a plurality of guide stator vanes arranged at regular intervals in a circumferential direction around a circumference of the bypass duct for altering a direction of airflow generated by a fan of the turbofan engine, the plurality of stator vanes including a plurality of regular guide stator vanes, a plurality of guide stator vane support struts and a plurality of modified guide stator vanes; the guide stator vane support struts having a larger thickness and chord length than the regular guide stator vanes and an aerodynamic shape adapted thereto; the modified guide stator vanes positioned adjacent respective suction sides of the guide stator vane support struts and having a different geometry as compared to the regular guide stator vanes to form expanding flow channels between pressure sides of the modified guide stator vanes and the adjacent respective suction sides of the guide stator vane support struts, the expanding flow channels for reducing pressure peaks of a circumferential pressure field building up on an upstream side of the guide blade ring, the different geometry configured in accordance with a configuration of the regular guide stator vane support struts.