Variable Stator Vane (VSV)
This test case has two objectives:
The first objective of this test case is to find new mechanisms for the VSV system. The main
goal of the design is to obtain good orientations of the blades during a
mission, using a minimum number of components (or minimising mass) and having
good mechanical behaviour.
The second objective deals with the advanced
3D modelling of the VSV. Once the general architecture is chosen, it is important to
validate the detailed design using 3D modelling. Indeed, it is important
to be able to provide 3D models which take into account all physical aspects
(contacts, friction, aerodynamic loads, etc.) We hope that the SYNCOMECS
project will improve our calculation process (“Multi stage” modelling, friction
on all kinematic elements, contact management, a wider variety of function
types to define the transient loads, performance, etc.)
Blade
Cooling Process
The objective is to
determine the initial shape of turbine blades: Rotor blades have shapes
which are functions of the rotation speed (e.g. rest, take off, cruise )
due to loads resulting
from: thermal fields, aerodynamic loads and centrifugal effects.
As blades are designed under
aerodynamics specifications
in cruise flight
(such as: compression ratio and yield).
The work of the mechanical engineer consists of finding the blade to be
manufactured, termed a “cold blade” (while the engine is not running).
This is an inverse finite
element problem.
At
this time some heuristic iterative methods exist, but they are quite
time expensive.
As a consequence, the
SYNCOMECS projects aims to develop an inverse finite element tool.
Examples of Pressure distribution
