A hybrid method of surface hardening metallic components using a combination of chemical modification achieved through additive manufacturing and/or diffusion-based processing with transformation-based processing using a high energy density heat source. The hybrid process results in increased surface hardness and/or increased average case hardness and/or increased case depth compared to either treatment individually.

A method of increasing a roughness of coiled tubing injector blocks that includes providing a pair of gripper blocks each having a gripper surface configured to grip coiled tubing within an injector head and increasing a first roughness on the gripping surfaces to a second roughness. A coating may be applied to the gripping surfaces to increase the roughness. The coating may be chromium carbide, molybdenum boride, iron boride, titanium boride, or a transitional metal boride. The gripping surfaces may be treated to increase the roughness to a second roughness. The gripping surfaces may be blasted by abrasives or shot peened to increase the roughness. The second roughness may be greater than 20 μm. A system to inject coiled tubing into a wellbore may include an injector head, coiled tubing, and at least two gripper blocks having a gripping surface with a roughness of at least 20 μm.

A method of increasing a roughness of coiled tubing injector blocks that includes providing a pair of gripper blocks each having a gripper surface configured to grip coiled tubing within an injector head and increasing a first roughness on the gripping surfaces to a second roughness. A coating may be applied to the gripping surfaces to increase the roughness. The coating may be chromium carbide, molybdenum boride, iron boride, titanium boride, or a transitional metal boride. The gripping surfaces may be treated to increase the roughness to a second roughness. The gripping surfaces may be blasted by abrasives or shot peened to increase the roughness. The second roughness may be greater than 20 μm. A system to inject coiled tubing into a wellbore may include an injector head, coiled tubing, and at least two gripper blocks having a gripping surface with a roughness of at least 20 μm.

Disclosed are new boronizing compositions consisting of boron fluoride and boron oxide, borax, or an iron boride. The compositions reduce the heating temperature and time. Further disclosed are methods of boronizing a metal substrate including these compositions, or any combination thereof.

Disclosed are new boronizing compositions consisting of boron fluoride and boron oxide, borax, or an iron boride. The compositions reduce the heating temperature and time. Further disclosed are methods of boronizing a metal substrate including these compositions, or any combination thereof.

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A gas turbine engine includes: a turbine section including a casing extending circumferentially about a plurality of turbine blades and having at least one seal member coated with an abradable coating. At least one turbine blade has sides and a tip and at least one seal member is located adjacent to the tip of the at least one turbine blade. The tip of the at least one turbine blade has a wear resistant layer and an abrasive coating disposed on the wear resistant layer. The wear resistant layer has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A gas turbine engine includes an engine static structure extending circumferentially about an engine centerline axis; a compressor section, a combustor section, and a turbine section within the engine static structure. At least one of the compressor section and the turbine section includes at least one airfoil and at least one seal member adjacent to the at least one airfoil. A tip of the at least one airfoil is metal having a wear resistant coating and the at least one seal member is coated with an abradable coating. The wear resistant coating is formed as a layer in a base metal surface of the airfoil, has a thickness less than or equal to 10 mils (254 micrometers) and includes metal boride compounds.

A powder boronizing composition comprising: a. 0.5 to 4.5 wt % of a boron source selected from B.sub.4C, amorphous boron, calcium hexaboride, borax or mixtures thereof; b. 45.5 to 88.5 wt % of a diluent selected from SiC, alumina or mixtures thereof; c. 1.0 to 20.0 wt % of an activator selected from KBF.sub.4, ammonia chloride, cryolite or mixtures thereof; and d. 10.0 to 30.0 wt % of a sintering reduction agent selected from carbon black, graphite or mixtures thereof.