The Determination of Rational Parameters of Lock Joints of Ceramic Blades with a Metal Disk in Advanced Aircraft Gas Turbine Engines. Part II. Testing of the Rotor Model

The limited thermal stability of commonly used nickel alloys is an obstacle to further increases in operating temperatures in aircraft gas turbine engines. Alternative solutions that overcome the limitations of the operating temperatures of the gas in front of the turbine can be achieved using ceramic materials, including ceramic composites used for manufacturing blades and rotor. Due to a number of design and technological limitations associated with the production of fully ceramic parts of gas turbine engines, the option of connecting metal impellers with blades made of monolithic ceramic material deserves attention. A design of a model steel impeller with blades made of silicon carbide ceramics with reinforcing diamond particles is proposed. To determine the bearing capacity of the ‘dovetail’ type lock joint, bench tests were carried out. A computer program for probabilistic evaluation of the strength of ceramic parts is developed. A conclusion is made about the required characteristics of ceramic materials for the use in turbine impellers.

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