FIELD: mechanical engineering; aircraft industry; methods of manufacture of the gas-turbine engines details.
SUBSTANCE: the invention is pertaining to the method of manufacture of the products containing the protective coating forming the heat barrier and which may be used for production of the details of the gas-turbines, such as the turbine blades of the turbojet engines. The method provides for formation on the substrate by the physical settling from the vapor phase of the binding sublayer, formation on the surface of the binding sublayer of the film made out of the aluminum oxide and formation of the outer layer. The binding sublayer is made out of the intermetallic compound containing aluminum. The binding sublayer is formed by means of the alternating deposition of elementary layers out of the metal from the group of platinum and from aluminum and formation out of them of the intermetallic compound by the exothermic reaction between them. The outer layer is formed out of ceramics on the film made out of aluminum oxide. The invention also offers the detail of the gas-turbine. combustion turbine is tendered also. The technical result of the invention is development of the method allowing formation of the protective coating, which forms the heat barrier and is chemically resistant, and the detail containing the coating deposited by this method.
EFFECT: the invention ensures, that the developed method allows to create the protective chemically resistant coating forming the heat barrier and the detail containing the coating deposited by this method.
32 cl, 7 dwg, 7 ex
