Patent ID: 8523517
Filing Date: 2013-09-03
Classification: F01D,F05D,Y02T

Abstract:
1. An aerodynamically shaped, symmetrical cross-sectional profile for at least one chosen from a strut, a fairing of a strut and a service line positioned in at least one chosen from a bypass duct and a core-flow duct of a turbofan engine, wherein the profile is defined by a course of a local thickness (T) and a position (PMT) of maximum thickness (MT) on both sides over a central chord (C) extending from a leading edge (LE) to a trailing edge (TE) of the at least one chosen from the strut, the fairing of a strut and the service line, wherein, in order to avoid flow separations, the course of the local thickness (T) between the position of maximum thickness (PMT) and a certain trailing-edge position (PTE) has a first turning point (WP the profile including: