DEVICE FOR LOCALISATION OF TURBOJET ENGINE BROKEN BLOWER BLADE Russian patent published in 2009 - IPC F02C7/05 

FIELD: engines and pumps.

SUBSTANCE: proposed device designed to localise turbojet engine broken blade consists of aligned layered outer and inner blower casings making chamber between them and interjointed with help of adjacent engine modules. The outer casing incorporates reinforced layer impenetrable by broken blade made from high-strength polymer material, e.g. organic plastic material. The inner casing incorporates the main layer penetrable by blade made from material with increased modulus of elasticity and dynamic rigidity, that makes outer shape of the blower air path. The aforesaid main layer inner surface has abrasive-wear material applied thereon. The aforesaid chamber between the inner and outer casings accommodates additional layer to get in contact with broken blade that features preset controlled resistance to the said blade travel in radial direction. The blade, when broken, features its free end moving tangentially towards the inner casing main layer inner surface to penetrate it to leave the zone of the blades rims rotation. The additional layer facilitates the loss of the broken blade remained kinetic power by turning and laying the blade between the casings in the medium with preset resistance. Further on, the blade lies down flatwise on the outer casing surface with minor contact strains and does not penetrate it.

EFFECT: removal of broken blade from rotation zone and localisation in integrated blower casing, smaller weight and sizes.

14 cl, 7 dwg