CLAIMS
What is claimed is:
1. A strengthened exhaust system of gas turbine starter engine (1) through which hot exhaust gases pass and merge with atmosphere comprising:
- an exhaust system with a casing structure (2) radially spaced outward and extending longitudinally from the CCOC (3) to the aircraft mount in order to transfer engine loads to the aircraft frame, wherein said casing structure comprises of features for mounting, weight reduction and better dissipation of heat from the exhaust duct, said casing structure is a half hollow cylinder (6) merging with a circular plate structure (7),
2. The system as claimed in claim 1, wherein, the steps consist of
Conducting thermal and stress analysis of the exhaust system. Arriving appropriate geometry of the exhaust system with casing structure,
- Optimising heat dissipation and weight by providing pockets (10) in the geometry,
- Optimising the strength to weight ratio by providing stiffeners, and
- The Rig testing of strengthened exhaust system along with the starter engine for applicable 'g-loads', shock loads and vibratory loads.