• 专利标题:   Blade for use in turbine with cooling structure of aircraft engine, has turbine blade whose inner portion is provided with cooling channel, and spoiler rib arranged in cooling channel according to preset distance and preset angle.
  • 专利号:   CN113279819-A
  • 发明人:   YANG X, ZHANG W, ZHENG L, JI R, ZHENG J, YU B, SUN D, DENG Y
  • 专利权人:   BEIJING INST PETROCHEMICAL TECHNOLOGY
  • 国际专利分类:   F01D005/18
  • 专利详细信息:   CN113279819-A 20 Aug 2021 F01D-005/18 202172 Pages: 10 Chinese
  • 申请详细信息:   CN113279819-A CN10779994 09 Jul 2021
  • 优先权号:   CN10779994

▎ 摘  要

NOVELTY - The structure has a multi-scale micro-structure provided with a micro-convex structure and a micro-concave structure. An inner portion of a turbine blade is provided with a cooling channel. A spoiler rib is arranged in the cooling channel according to preset distance and preset angle. A surface of the cooling channel and the spoiler rib are provided with the multi-scale micro-structure. The multi-scale micro-structure is provided with nickel crystal particles and graphene-shaped redox graphene. USE - Blade for use in a turbine (claimed) with a cooling structure of an aircraft engine. ADVANTAGE - The turbulent flow rib has function of cooling and strengthening heat transfer. The electric brush is plated with a layer of the multi-scale micro-structure on the base of the turbulent flow rib, which can increase specific surface area of convection heat exchange, improves disturbance of cooling fluid on a wall surface and heat conductivity coefficient of fluid heat-conducting equivalent, so as to obviously provide heat exchange effect. The structure has obvious effect on cooling strengthening heat transfer in a high temperature nickel base alloy turbine blade of an aircraft engine, and has wide application prospect in a turbine blade cooling technology field. DESCRIPTION OF DRAWING(S) - The drawing shows a perspective view of a blade for use in turbine with cooling structure of aircraft engine.