Abstract: A rocket engine includes a copper alloy combustion chamber, a non-copper weld transition ring welded to the copper alloy combustion chamber, and an injector assembly welded to the non-copper weld transition ring. The engine can be manufactured by forming the copper alloy combustion chamber using additive manufacturing, welding the non-copper weld transition ring to the copper alloy combustion chamber, and welding the injector assembly to the non-copper weld transition ring.

Abstract: A rocket engine includes a copper alloy combustion chamber, a non-copper weld transition ring welded to the copper alloy combustion chamber, and an injector assembly welded to the non-copper weld transition ring. The engine can be manufactured by forming the copper alloy combustion chamber using additive manufacturing, welding the non-copper weld transition ring to the copper alloy combustion chamber, and welding the injector assembly to the non-copper weld transition ring.

Abstract: A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.

Abstract: A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.

Abstract: A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.

Abstract: A cap for a liquid propellant injection assembly of a rocket engine includes a cap body and a valve assembly. The cap body extends between first and second ends. The cap body has a bore that fluidly connects one or more inlets to an outlet. The inlets are disposed in a tubular sidewall of the cap body. The outlet is disposed in the second end of the cap body. The valve assembly includes a valve cap disposed around the first end of the cap body. The valve assembly is adapted to selectively regulate flow of a propellant through the inlets in the cap body as a function of pressure exerted by the propellant against the valve assembly.

Abstract: A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.

Abstract: A method of manufacturing a duct is disclosed that is suitable for aerospace applications, for example. The method includes the steps of providing a longitudinally extending duct having a first wall thickness at an end portion and a second wall thickness at a portion that is less than the first wall thickness. The duct is bent at the portion to a desired shape to provide a tube having at least one bend located within a distance of one duct diameter from the first wall thickness.

Abstract: A cap for a liquid propellant injection assembly of a rocket engine includes a cap body and a valve assembly. The cap body extends between first and second ends. The cap body has a bore that fluidly connects one or more inlets to an outlet. The inlets are disposed in a tubular sidewall of the cap body. The outlet is disposed in the second end of the cap body. The valve assembly includes a valve cap disposed around the first end of the cap body. The valve assembly is adapted to selectively regulate flow of a propellant through the inlets in the cap body as a function of pressure exerted by the propellant against the valve assembly.

Abstract: In some embodiments fastening apparatus includes a threaded fastening element adapted to be threaded into a hole provided in a first component, the threaded fastening element including a locking collar that is defined by at least one outer peripheral surface, and a locking washer adapted to fit within a recess formed in the component to limit rotation of the threaded fastening element once the element is threaded into the component hole, the washer including an inner opening defined by at least one inner peripheral surface and a non-circular outer shape defined by an outer peripheral surface, the inner opening being adapted to receive the locking collar such that the at least one outer peripheral surface of the collar can contact the at least one inner peripheral surface of the washer.

Abstract: In some embodiments fastening apparatus includes a threaded fastening element adapted to be threaded into a hole provided in a first component, the threaded fastening element including a locking collar that is defined by at least one outer peripheral surface, and a locking washer adapted to fit within a recess formed in the component to limit rotation of the threaded fastening element once the element is threaded into the component hole, the washer including an inner opening defined by at least one inner peripheral surface and a non-circular outer shape defined by an outer peripheral surface, the inner opening being adapted to receive the locking collar such that the at least one outer peripheral surface of the collar can contact the at least one inner peripheral surface of the washer.

Abstract: A thrust chamber assembly cooling system includes a twisted ribbon/wire of any one of many variety of cross-sectional shapes located within a nozzle assembly cooling passage to direct the coolant to flow in a swirling manner which induces mixing and breaks up the boundary layer in the coolant passage to enhance the convective heat transfer.