hermal expansion mismatch of different blade and disc materials. The turbine blades, which are mounted parallel to the axis of the discs, are imprisoned between the retaining covers so that they do not protrude towards the front or the back of the engine.Simplified disc, blade and retainer assembly are shown on the side. In addition to these, the basi
Background: Turbine discs and turbine blades are critical components used in gas turbine engines and aviation engines. The gases, which are compressed and pressurized in the compressor and mixed with the fuel in the combustion chamber, hit the turbine blades and cause rotational movement in the turbine discs where these blades are mounted. These blades are designed to be installed into the slots on the disc for ease assembly and to compensate for the thermal expansion mismatch of different blade and disc materials. The turbine blades, which are mounted parallel to the axis of the discs, are imprisoned between the retaining covers so that they do not protrude towards the front or the back of the engine.Simplified disc, blade and retainer assembly are shown on the side. In addition to these, the basic dimensions of the turbine blade are given. It is known that the gas at a certain pressure acts on the blade in question and the disc rotates with a certain revolution, and every surface of the blade is at the same temperature given. Since it is known that the material of the blade is 316L stainless steel, calculate what is required below?
Average temperature is 200 degree Celsius
a)Find the stress pattern and value for the most important loading condition affecting the blade?
b) Find the strain value for the most important loading condition affecting the blade?
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