METHOD OF ELEMENT HARDENING IN THE FORM OF TURBO MACHINE ROTOR ROTATION BODY WITH METAL MATRIX COMPOSITE Russian patent published in 2019 - IPC C23C24/10 

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering, to methods of forming reinforcing element from metal matrix composite on disk and/or drum of gas turbine engine rotor. Method of element hardening in the form of turbo machine rotor rotation body metal-matrix composite includes layer-by-layer winding of ceramic threads on said element, supply of powder alloy to ceramic layer from threads and subsequent alloying of alloy and layer of threads to form metal matrix composite. Said element is rotated relative to its longitudinal axis, and ceramic thread is wound in form of strip with distance between threads in it, equal to 1–3 diameters of ceramic thread with surface density of 40–180 g/m². Powder alloy is pre-melted and continuously supplied not earlier than point of contact of strip and element of rotor or formed on rotor layer of metal matrix composite with flow rate, providing fusion of ceramic thread and formation of metal matrix composite layer on section of normalized length, length of which is determined from ratio L=(0.52–1.05)*r, where L is the length of the newly formed surface layer, r is the radius of the element in the form of a rotation body. Formed metal matrix composite at the specified section of the normalized length is machined, at that the width of the processing tool is equal to or greater than the width of the ceramic threads strip. In particular embodiments of the invention, the rotor elements are hardened in the form of disks or drums. Along outer surface of rotor element there arranged at equal intervals are means for fixing shank end of blades, made in form of root elements for welding in form of blade profile. Powder alloys based on titanium, nickel and aluminum are used as powder alloy. Carbide-silicon fibers are used as ceramic threads.

EFFECT: higher technological effectiveness of the coating formation process, reduced weight of the structure, repairability of the rotor of the blade machine, improved mechanical properties of coating due to guaranteed creation of preliminary stress in threads and increase of amount of reinforcing threads by 3 to 4 times per 1 mm of coating thickness and improvement of coating quality.

5 cl, 3 dwg, 1 ex