FIELD: engines and pumps.
SUBSTANCE: gas turbine engine component comprises an inner bandage, an outer bandage and guiding vanes which are made of a composite material having an interlaced fiber reinforcement packed with a matrix. A fiber reinforcement includes a set of threads extending continuously along a trajectory adjoining longitudinally through two successively located guide vanes and passing through the inner bandage and the outer bandage. The threads of the interlaced fiber reinforcement extend continuously in a circular direction along the entire segment of the inner bandage and the entire segment of the outer bandage. In the manufacture of the gas turbine engine component, an interlaced fiber preform is formed including a first set of threads extending continuously along the full circumference of the first part of the preform, forming the preform for the inner bandage, and then extending successively longitudinally along the second parts of the preform, forming the preforms for the guide vanes, and also along the full circumference of the third part of the preform forming the preform for the outer bandage. The threads of the first set of threads extend successively along the mentioned second parts of the preform by passing from one second part of the preform to the next alternately through the first part of the preform and through the second part of the preform. The fiber preform is then compacted with a matrix.
EFFECT: group of inventions allows to increase the mechanical strength of the components of the gas turbine engine made of composite material.
18 cl, 17 dwg
