OPTIMIZATION DESIGN OF THE INTEGRATED SEALING DISK-BAFFLE FOR THE HIGH-PRESSURE TURBINE OF AN AEROENGINE

The integrated sealing disk-baffle is widely used in modern advanced aeroengines. Under the harsh and variable load conditions of high temperature, high pressure, and high rotational speed, it must not only possess sufficient structural strength, but also ensure that the sealing disk-baffle remains tightly pressed against the turbine disk to maintain the sealing of the cooling air. Existing studies mostly focus on strength optimization, while few have addressed the optimization of the sealing surface’s contact pressure. The sealing disk-baffle relies on pre-deformation during assembly to maintain tight contact at the sealing surface. However, due to the Poisson effect, centrifugal loads can cause axial shortening of the part, which may offset part or all of the pre-deformation. If the applied preload is too large, although tight contact can be ensured, strength issues may arise; conversely, if the preload is too small, it can lead to cooling air leakage. In addition, due to the complex geometry and multiple constraints of the sealing disk-baffle, its deformation behavior under variable operating conditions is complex, and optimization based solely on assembly parameters is insufficient to solve the aforementioned problems. This study focuses on optimizing the configuration of the integrated sealing disk-baffle with the goal of improving the contact pressure at the sealing surface. While keeping the mass essentially unchanged, the robustness of the sealing surface contact state is enhanced. The results provide a basis and reference for the structural design and engineering application of the integrated sealing disk-baffle.