Macro-Level Analysis of Ti-SiC Metal Matrix Composite Ring Based on Finite Element Method

Abstract This is an exploratory study on bladed ring (BLING) technologies for gas turbine engine compressors. The BLING is basically a modification of the bladed disk assembly, wherein the massive conventional disk made of an isotropic material is replaced by a sleek and stiff ring constructed with MMC. The purpose of this study is to replace the existing bladed disk (BLISK) assembly with a bladed ring (BLING) made up of metal matrix composites (MMCs) in an aero-engine turbine compressor blade design. A 3-D finite element model of existing bladed disk assembly is investigated to analyze the permissible limit of stresses under specified thermo-mechanical operating conditions. The obtained stress pattern sets a benchmark to design a bladed ring of a metal matrix composite. The design of BLING consists of two methods: stiffness and strength-based. Stiffness criteria are used to avoid resonance between the natural frequency of the ring and the frequency of the applied external load (engine RPM). At the same time, the strength criteria are utilized to check the permissible stress limit of the proposed material for BLING design. The applicability and accuracy of the proposed model satisfy all the permissible limits for a safer design with a considerable reduction in the mass of the overall system.