FIELD: engine devices and pumps.
SUBSTANCE: turbomachine comprises a rotor defining a longitudinal axis of the turbomachine and a blade connected to the rotor and a reinforcement strip. The reinforcement strip is connected to the blade and is designed to resist delamination of the blade by applying compressive load to the blade of the turbomachine. The reinforcement strip is located on the blade at its outer part and at some distance from the rotor in the radial direction. In another embodiment, the turbomachine blade comprises first and second layers of laminated material, and the reinforcement strip is designed to resist delamination of the first and second layers of the laminate material by applying compressive load to compress the layers together. Another invention relates to a gas turbine engine comprising a compressor having blades, a combustion chamber, a turbine having the blades, and reinforcing strip connected to blade of compressor or turbine. Said blade comprises first and second layers of laminated material. The reinforcement strip is designed to resist delamination of the first and second layers of the laminate material by applying compressive load to compress the layers together. The reinforcement strip is located on the blade at its outer part and at some distance from the compressor rotor or turbine in radial direction.
EFFECT: increased durability of the turbomachine blades.
19 cl, 7 dwg
