Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a first O-ring disposed between the annular ring and the fluid transfer tube, a second O-ring disposed between the base member and the annular ring, and an attachment ring configured to secure the annular ring and the base member to the casing.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, a housing configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a bellows surrounding the fluid transfer tube and positioned between the housing and the casing, and a wear ring disposed between the housing and the bellows.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, a housing configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a bellows surrounding the fluid transfer tube and positioned between the housing and the casing, and a wear ring disposed between the housing and the bellows.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a base member having a first side configured to mate with a casing and a second side opposite the first side, an annular ring configured to mate with the second side of the base member and to surround a portion of the fluid transfer tube, a first O-ring disposed between the annular ring and the fluid transfer tube, a second O-ring disposed between the base member and the annular ring, and an attachment ring configured to secure the annular ring and the base member to the casing.

Abstract: A seal assembly for a fluid transfer tube in a gas turbine engine is disclosed. In various embodiments, the seal assembly includes a boot seal configured to surround a length of the fluid transfer tube, the boot seal having a first end and a second end and a seal ring disposed at the first end, an attachment ring configured to mate with the seal ring and to secure the seal ring against a casing, an annular ring configured to mate with an interior surface of the boot seal at the second end and to surround a portion of the fluid transfer tube, and a clamp ring configured to surround the second end of the boot seal proximate the annular ring.

Abstract: A fluid conduit for a gas turbine engine includes a first fluid conduit attachable to a second fluid conduit and securable together with a lockable connector. The connector includes a first portion including external threads and a second portion receiving the first portion and including internal threads mating to the external threads of the first portion. The internal threads include lead threads defining a first thread interface with the external threads for starting attachment of the first portion to the second portion and locking threads defining a second thread interface for locking the first portion to the second portion.

Abstract: A fluid conduit for a gas turbine engine includes a first fluid conduit attachable to a second fluid conduit and securable together with a lockable connector. The connector includes a first portion including external threads and a second portion receiving the first portion and including internal threads mating to the external threads of the first portion. The internal threads include lead threads defining a first thread interface with the external threads for starting attachment of the first portion to the second portion and locking threads defining a second thread interface for locking the first portion to the second portion.

Abstract: A method is provided for repairing a damaged rotor blade on an integrally bladed rotor by removing a damaged portion of a damaged blade leaving a blade stub extending outwardly from the disk and performing a linear friction welding operation to attach a replacement blade segment to the blade stub. The rotor may be disposed operation using a linear friction welding apparatus. The method includes disposing a support collar about the blade stub and securing the support collar to the linear friction welding apparatus prior to a commencement of the bonding operation. A lower surface of the support collar is contoured to mate with a portion of an outer circumference surface of the rotor disk.

Abstract: Methods for repairing gas turbine components damaged by corrosion that not only restores the components back to their original dimensions to ensure proper engine operations, but also have the added benefit of mitigating future corrosion attacks thereby extending the useful life of the components.

Abstract: A ferrule for use with a nut with an internal locking mechanism includes a first tubular portion with a first end and a first outer diameter for connecting to a first object; a second tubular portion with a second end and a second outer diameter for connecting to a second object; a transition portion connecting the first tubular portion and the second tubular portion; and a plurality of pockets spaced circumferentially around the second portion to engage the internal locking mechanism of the nut.

Abstract: A method of repairing a damaged coated vane from a turbine module without removing the vane from the module is taught. The method includes locally removing the coating in the vicinity of the damage as well as any underlying damage in the superalloy substrate. A diffusible coating precursor is then applied to the damage site. A heat treating fixture is then mounted on the vane and repair site is heated to up to 2000° F. in an inert environment to interdiffuse the coating precursor and the substrate. After the diffusion anneal, the vane is cleaned and the module is returned to service.

Abstract: A method of repairing an integrally bladed rotor includes the steps of placing a support collar around at least a leading and trailing edge portions of the blade stub, and performing linear friction welding to add a replacement airfoil to the blade stub. The linear friction welding is generally along a direction between the leading and trailing edges. In addition, the support collar leading and trailing edge portions are connected together.

Abstract: A ferrule for use with a nut with an internal locking mechanism includes a first tubular portion with a first end and a first outer diameter for connecting to a first object; a second tubular portion with a second end and a second outer diameter for connecting to a second object; a transition portion connecting the first tubular portion and the second tubular portion; and a plurality of pockets spaced circumferentially around the second portion to engage the internal locking mechanism of the nut.

Abstract: A method of repairing a damaged coated vane from a turbine module without removing the vane from the module is taught. The method includes locally removing the coating in the vicinity of the damage as well as any underlying damage in the superalloy substrate. A diffusible coating precursor is then applied to the damage site. A heat treating fixture is then mounted on the vane and repair site is heated to up to 2000° F. in an inert environment to interdiffuse the coating precursor and the substrate. After the diffusion anneal, the vane is cleaned and the module is returned to service.

Abstract: A method of repairing a case for a gas turbine engine includes identifying areas of damage on its internal holding structures in a gas turbine case, and utilizing cold metal transfer to deposit weld material to the internal holding structures.

Abstract: A method for peening a component of a gas turbine engine, or a module of a gas turbine engine, without removing the component from the assembled gas turbine engine or module includes blending the damaged area of the component, determining parameters for peening the damaged component, and peening the damaged component without removing it from the engine.

Abstract: A method of repairing an integrally bladed rotor includes the steps of placing a support collar around at least a leading and trailing edge portions of the blade stub, and performing linear friction welding to add a replacement airfoil to the blade stub. The linear friction welding is generally along a direction between the leading and trailing edges. In addition, the support collar leading and trailing edge portions are connected together.

Abstract: A method is provided for repairing a damaged rotor blade on an integrally bladed rotor by removing a damaged portion of a damaged blade leaving a blade stub extending outwardly from the disk and performing a linear friction welding operation to attach a replacement blade segment to the blade stub. The rotor may be disposed operation using a linear friction welding apparatus. The method includes disposing a support collar about the blade stub and securing the support collar to the linear friction welding apparatus prior to a commencement of the bonding operation. A lower surface of the support collar is contoured to mate with a portion of an outer circumference surface of the rotor disk.

Abstract: A method of repairing a hole in a work piece includes mechanically constraining donor plates against a work piece. Constraint plates keep donor plates flush against the work piece during conductive heat resistance welding. By constraining the donor plates, the molten mixture produced by conductive heat resistance welding cannot escape the hole and a weldment substantially free of voids is formed.

Abstract: A process for repairing components includes the steps of providing a component having an affected area on a surface of a component to be repaired; depositing a repair material over the affected area on the surface of the component so that the repair material plastically deforms without melting and bonds to the affected area upon impact with the affected area and thereby covers the affected area; providing a sulfuric acid based anodizing solution; anodizing a deposited repair material on the surface of said component in the sulfuric acid based anodizing solution; consuming only a portion of the deposited repair material to form a hard anodized coating layer upon the deposited repair material to form a hard anodized coated component; providing a corrosion resistant sealant solution; and contacting a hard anodized coated component with the corrosion resistant sealant solution to form a corrosion resistant sealant coating on the hard anodized coated component.