The present application relates to a kind of high-pressure
turbine guide vane, and specifically relates to a kind of preparation method of
ceramic matrix composite multi-cavity structure high-pressure
turbine guide vane.Solve the technical problems that
ceramic matrix composite high-pressure
turbine guide vane component forming is difficult, blade component
size difference and pre-embedded split joint model is easy to be bonded with blade.The method of the present application comprises the following steps:1) preparing upper edge plate component preform, lower edge plate component preform and blade body preform;2) preparing
boron nitride interface layer for each preform respectively;3) preparing SiC matrix for each preform respectively, during the densification process of blade body preform, new
graphite tooling and
graphite paper pad are used at split joint structure for each furnace deposition;4) preparing self-healing matrix for each preform respectively;5)
processing each component;Installing inner core baffle and multiple
spoiler columns;Online
assembly of each component, deposition and
processing obtain turbine guide vane.