COMBUSTION ENGINE, GAS TURBINE, AND ABRASIVE LAYER

摘要

The present invention provides a gas turbine in which a proper clearance is kept between a rotor blade and a shroud for a long period of time from the start of operation, so that damage to the rotor blade is less likely to occur. In a turbine portion of the gas turbine, the rotor blade and the shroud face each other. At the tip end of the rotor blade an abrasive layer is formed, and on the inner peripheral surface of the shroud a heat insulating layer is formed. The abrasive layer is formed of a matrix with many abrasive particles dispersed in the matrix. The abrasive particles include protruding particles protruding from the matrix, and embedded particles embedded in the matrix. In the initial sliding of the rotor blade and the shroud in the early stage of operation, the inner peripheral surface of the shroud is ground by the protruding particles. After the protruding particles have disappeared, the inner peripheral surface of the shroud is ground by the embedded particles.