![]() ‘Damage tolerant’ components are designed using methodology and substantiation to predict and limit crack growth.ī. ‘Damage tolerant’ gas turbine engine rotor components using powder metallurgy materials specified by 1C002.b. ![]() Gas turbine engine components using “diffusion bonding” “technology” specified by 2E003.b. Airfoil‑to‑disk blade combinations using solid state joining ħ. 'Gas path temperature' is the bulk average gas path total (stagnation) temperature at the leading edge plane of the turbine component when the engine is running in a ‘steady state mode’ of operation at the certificated or specified maximum continuous operating temperature.Ħ. ![]() Cooled turbine blades, vanes, " tip-shrouds" other than those described in 9E003.a.1., designed to operate at a 'gas path temperature' of 1,693 K (1,420☌) or more Uncooled turbine blades, vanes or " tip-shrouds", designed to operate at a 'gas path temperature' of 1,373 K (1,100☌) or more ĥ. Ī 'splitter duct' performs the initial separation of the air-mass flow between the bypass and core sections of the engine.Ĥ.
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