FIELD: guide vane assembly; gas turbine engine.
SUBSTANCE: invention relates to a guide vane assembly (1) for a fan module of a gas turbine engine, wherein the guide vane assembly (1) comprises a number of blades (2) distributed around the axis of rotation of the guide vane assembly, each blade (2) being made of a composite material and has a feather (21) and a leg (22) intended for connection with the shell (4) of the gas turbine engine. The assembly (1) contains platform (3) for centering and mounting on a gas turbine engine, designed for mounting, on the one hand, on the shell (4) in a certain azimuth position and, on the other hand, on the leg (22) of the blade (2), with in this case, the platform (3) is made with the possibility of its fastening on the shell (4) using screws (51a), longitudinal relative to the axis of rotation of the assembly (1), and fastening on the leg (22) using screws (52), radial relative to the axis of rotation of the guide vane assembly (1). The use of the platform as an element of alignment and fastening, separate from the blade and shell, makes it possible to simplify the installation of the straightener unit. The dual function of the platform eliminates complex solutions such as dovetails. The platform is attached to the blade, then accurately positioned on the shell. Since the position of the platform as well as its geometry is precisely known, the mounting of the blade on the platform ensures accurate positioning of the blade. In addition, fastening the platform on the shell with longitudinal screws and fastening the platform on the leg with radial screws ensures good transfer of mechanical forces from the shell to the blade, this fastening helps to prevent certain stress concentrations in the platform and, therefore, allows to increase its service life.
EFFECT: invention provides a guide vane assembly in which the fixing and positioning of the guide vane is simple and reliable.
10 cl, 10 dwg
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Authors
Dates
2023-04-11—Published
2019-11-08—Filed