Abstract: Broken remnants of turbine engine rotor thru-bolt/nut interfaces are enveloped in a housing that is coupled to the rotor, so that the remnant does not migrate to other portions of the engine. In exemplary embodiments the housing directly mates with and engages the thru-bolt stud male threaded portion that projects outwardly from the nut, such as by a female threaded sleeve that is engaged with the male threads. The sleeve is in turn coupled to and/or supported by the rest of the housing. Some housing embodiments surround one or more of the threaded stud/nut interfaces. Housing embodiments of the invention are installed in situ without removing the rotor structure from the engine.

Abstract: Broken remnants of turbine engine rotor thru-bolt/nut interfaces are enveloped in a housing that is coupled to the rotor, so that the remnant does not migrate to other portions of the engine. In exemplary embodiments the housing directly mates with and engages the thru-bolt stud male threaded portion that projects outwardly from the nut, such as by a female threaded sleeve that is engaged with the male threads. The sleeve is in turn coupled to and/or supported by the rest of the housing. Some housing embodiments surround one or more of the threaded stud/nut interfaces. Housing embodiments of the invention are installed in situ without removing the rotor structure from the engine.

Abstract: A method of servicing an airfoil for use in a gas turbine engine. The airfoil assembly is defined by a base material and includes an airfoil and a platform from which the airfoil extends. A predetermined amount of the base material is removed from the airfoil assembly proximate to a fillet area of the airfoil assembly via water jet material removal. The fillet area comprises a junction between the airfoil and the platform and is located at an intersection between the airfoil and the platform. A remainder of the base material comprising base material of the airfoil assembly other than proximate to the fillet area is left intact.

Abstract: A method of servicing an airfoil for use in a gas turbine engine. The airfoil assembly is defined by a base material and includes an airfoil and a platform from which the airfoil extends. A predetermined amount of the base material is removed from the airfoil assembly proximate to a fillet area of the airfoil assembly via water jet material removal. The fillet area comprises a junction between the airfoil and the platform and is located at an intersection between the airfoil and the platform. A remainder of the base material comprising base material of the airfoil assembly other than proximate to the fillet area is left intact.