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: An apparatus includes an inlet conduit assembly surrounding a gas flow path and a combustor arranged downstream of the inlet conduit assembly. The inlet conduit assembly includes a thermoelectric (TE) device configured to convert heat into electrical energy, a gas flow conduit arranged between the gas flow path and the TE device, and a resilient member configured to bias the TE device into contact with the gas flow conduit.

Abstract: An injector assembly for a rocket engine includes a thermal insulating layer adjacent to an oxidizer cavity.

Abstract: A sliding connection between components of dissimilar materials includes a first mating surface formed on a first component and a second mating surface formed on a second component and configured to mate with the first mating surface. The first component is connected to the second component at the first and the second mating surfaces by a fastener including a shank, a sleeve received by the shank, and a resilient member received by the shank and contained by the sleeve. The resilient member is configured to press the first mating surface and the second mating surface against one another and to permit the first mating surface to slide against the second mating surface.

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: An apparatus includes an inlet conduit assembly surrounding a gas flow path and a combustor arranged downstream of the inlet conduit assembly. The inlet conduit assembly includes a thermoelectric (TE) device configured to convert heat into electrical energy, a gas flow conduit arranged between the gas flow path and the TE device, and a resilient member configured to bias the TE device into contact with the gas flow conduit.

Abstract: A sliding connection between components of dissimilar materials includes a first mating surface formed on a first component and a second mating surface formed on a second component and configured to mate with the first mating surface. The first component is connected to the second component at the first and the second mating surfaces by a fastener including a shank, a sleeve received by the shank, and a resilient member received by the shank and contained by the sleeve. The resilient member is configured to press the first mating surface and the second mating surface against one another and to permit the first mating surface to slide against the second mating surface.

Abstract: The external flaps of a variable exhaust nozzle for a gas turbine engine are attached to the nozzle by a pair of pivotal rods attached to the nozzle's internal support structure and slidably fits into elongated spaced bushings extending along the longitudinal axis of the flaps formed in bosses extending orthogonally from the inner surface of the flaps. The attachment to the support structure includes a unison ball made from composite material that fits into a spherical track formed in a recess in the end of the rods. The method of installation is to insert one of the post into the first bushing that is offset from the second bushing. After the slight engagement of the first post, the second post is pivoted to align with its complementary bushing and the flap is positioned forward to fully engage the rods into the bushings. The aft end hinge of the flap is then attached, A limit pin that is attached to the post travels in a slot designed to limit the travel of the post.

Abstract: A divergent flap seal for a gas turbine engine exhaust nozzle having a longitudinal axis is provided, having a body, a spine member, and a flap position guide. The flap position guide separates adjacent divergent flaps regardless of the angle the flaps are skewed relative to the longitudinal axis of the nozzle, thereby more evenly distributing the flaps about the circumference of the nozzle.