Aero-engine mounting edge structure with radial deformation coordination function
By using a combined mounting edge structure, double radial clearance and precision positioning holes, the problem of radial thermal expansion difference of turbine stator components under high temperature gradient environment is solved, achieving precise positioning and low-cost maintenance.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AVIC GUIYANG ENGINE DESIGN & RES INST
- Filing Date
- 2026-04-27
- Publication Date
- 2026-07-17
AI Technical Summary
The existing mounting edge structure of turbine stator components in aero engines cannot effectively coordinate the radial thermal expansion differences under high temperature gradient environments, resulting in thermal stress concentration, which increases maintenance costs and safety risks.
It adopts a modular mounting edge structure, including flow channel components, limit rings and casing mounting edges. By setting double radial movement clearances and precision positioning holes, the flow channel components are allowed to expand freely in the radial direction, eliminating thermal stress and supporting convenient disassembly and maintenance.
It achieves precise positioning and radial deformation coordination in high-temperature gradient environments, reducing maintenance costs and improving the reliability and service life of the structure.
Smart Images
Figure CN122407296A_ABST