42results about How to "Solve the problem of chip removal" patented technology

The invention discloses a drill bit for breaking rock by rotary cutting (a rotary cutting drill bit for short as follows), which comprises a drill bit main body, a roller cone, cutting teeth, an oil storage bag and a spray nozzle, wherein the drill bit main body comprises a roller cone shaft neck, a centralizing block, a high-pressure slurry channel and a connecting screw thread; and the roller cone and the shaft neck on the main body adopt a general bearing and a sealing structure of a tricone drill bit; a plurality of circles of cutting teeth are arranged from the large end to the small end of the roller cone; an included angle beta (an included angle of a cone body for short as follows) between a roller cone shaft neck plane on the main body and an axial line of the drill bit ranges from 0 to 90 degrees (containing beta i=beta(i+1) and beta i is not equal to beta(i+1)); the offset s (containing s i=s(i+1) and s i is not equal to s(i+1)) of the shaft neck ranges from-D / 2 to D / 2; i (greater than or equal to 1) represents a serial number of the roller cone; the included angle of the cone body corresponding to the cone i is represented by beta i; the offset of the shaft neck corresponding to the cone i is represented by s i; and D represents the diameter of the drill bit. According to the drill bit disclosed by the invention, an inner-row large gear ring is used for cutting the center of a shaft bottom and has high rock-breaking efficiency; each circle of cutting teeth can be used for scratching and cutting the shaft wall and has favorable effects for gauge protection and side drilling; the size of the shaft neck is large; the speed ratio of the cone body is smaller than 1; and the bearing has a long service life.

The invention relates to a guide vane air film hole composite machining method which comprises the steps that the surface and a cavity of a to-be-machined high-pressure turbine guide vane are coated with an anti-splashing agent, and the high-pressure turbine guide vane with an anti-splashing coating is obtained through drying; to-be-machined air film holes are located in a blade body and an edge plate of the high-pressure turbine guide blade correspondingly, and the to-be-machined air film holes in the blade body comprise the first air film hole and the second air film hole. A protection plateis placed in a cavity of the blade, the first air film hole and the second air film hole in the blade body are machined through electric sparks, the rest air film holes in the blade body and the airfilm holes in the edge plate are machined through lasers, and laser-electric spark composite machining of the air film holes of the high-pressure turbine guide blade is completed through aftertreatment. The protection plate is adopted for protection and partial machining, the problems that the wall is damaged by the hollow blade and metal splashes are discharged are solved, the percent of pass ofair film hole diameters and the machining efficiency are greatly improved, and the surface quality integrity of parts is improved through an anti-splashing agent.