Methods and apparatus for sealing variable area fan nozzles of jet engines are disclosed. An apparatus in accordance with the teachings of this disclosure includes a frame and a seal to be coupled to the frame. The seal to enclose petals of a variable area fan nozzle to substantially prevent airflow between the petals.

Provided are an exhaust duct, an exhaust duct assembly, and an aircraft using the exhaust duct. The exhaust duct has a structure that enables combustion gas to be diverged and discharged from an inlet end to a first outlet end and a second outlet end at respective sides of the exhaust duct. The exhaust duct includes a first housing including a first body forming an outer wall of the inlet end, and further includes second bodies respectively extending on respective sides from the first body and respectively forming the first outlet end and the second outlet end; a second housing spaced apart from the first body, forming an inner wall of the inlet end, and extending curvedly toward the second bodies; and a connection housing connecting the first housing to the second housing and including at least one recess portion recessed toward the inlet end.

Provided are an exhaust duct, an exhaust duct assembly, and an aircraft using the exhaust duct. The exhaust duct has a structure that enables combustion gas to be diverged and discharged from an inlet end to a first outlet end and a second outlet end at respective sides of the exhaust duct. The exhaust duct includes a first housing including a first body forming an outer wall of the inlet end, and further includes second bodies respectively extending on respective sides from the first body and respectively forming the first outlet end and the second outlet end; a second housing spaced apart from the first body, forming an inner wall of the inlet end, and extending curvedly toward the second bodies; and a connection housing connecting the first housing to the second housing and including at least one recess portion recessed toward the inlet end.

An aft section structure of a jet engine with an axis is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; spray bars, each of the spray bars extending radially within the duct and comprising trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.

An aft section structure of a jet engine with an axis is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; spray bars, each of the spray bars extending radially within the duct and comprising trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.

The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

The present invention provides a thrust flow powered vehicle comprising a first thrust flow expeller for expelling a first thrust flow in a first direction, a second thrust flow expeller for expelling a second thrust flow in a second direction, the second direction being a different direction to the first direction but sharing a plane with the first direction, a thrust flow deflector surface at an angle to the plane of the first and second directions, and an outlet portion for providing an output thrust flow, such that, in use, the thrust flow deflector surface deflects at least a portion of both the first and second thrust flows to form the output thrust flow such that the output thrust flow has a component in the plane of the first and second directions, and a component out of that plane.

The present disclosure comprises a thrust augmentation device for liquid rocket engines that will enable higher thrust throttling when launch vehicles require the additional thrust and be turned off when the additional thrust is no longer required. The present disclosure provide a higher mission-average engine specific impulse (Isp) performance by offering a greater nozzle exit area ratio and option of MR-shift in main combustion chamber. The present disclosure retains the technology advancements made in historical rocket engine development where cost and technical challenges were great, that is in the turbopump and main injector/combustion chamber, and take advantage of engine component that is least developed and understood, the nozzle section by providing a secondary propellant injection port and combustion zone to optimize liquid rocket engine performance required by launch vehicles.

The present disclosure comprises a thrust augmentation device for liquid rocket engines that will enable higher thrust throttling when launch vehicles require the additional thrust and be turned off when the additional thrust is no longer required. The present disclosure provide a higher mission-average engine specific impulse (Isp) performance by offering a greater nozzle exit area ratio and option of MR-shift in main combustion chamber. The present disclosure retains the technology advancements made in historical rocket engine development where cost and technical challenges were great, that is in the turbopump and main injector/combustion chamber, and take advantage of engine component that is least developed and understood, the nozzle section by providing a secondary propellant injection port and combustion zone to optimize liquid rocket engine performance required by launch vehicles.

The present disclosure relates to a method for producing a final metal part for a nacelle of a turbojet. The method includes brazing at least two parts, one being an inner part having an inner surface and the other being an outer part having an outer surface. The method further includes a step of heating the outer surface of the outer part using an external heating means, and a step of heating the inner surface of the inner part using an internal heating means.