A method for manufacturing an annular heat exchanger intended to be mounted on the radially inner or outer face of an annular shell of a casing of a double-flow turbomachine, the method including: obtaining by extrusion a heat exchanger preform by a die shaped so that the preform includes: first pipes for the circulation of a fluid to be cooled, second pipes arranged on either side of the first pipes in a direction perpendicular to the direction of extrusion; making a hole from the outside in the preform, the hole leading into one of the second pipes of the preform; and introducing into the hole of the second given pipe a member for partially closing off its passage cross-section.

A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.

A method of producing a propellant material element, such as an electrically-operated propellant material, includes extruding a propellant material through a heated nozzle. The nozzle may be heated to a temperature that is above the boiling point of a solvent that is part of the propellant material, yet is below a decomposition temperature of the propellant material. This allows some of the solvent to be driven off during the extruding process, while still preventing initiation of an energy-creating reaction within the material. The heating of the material in the extruding process, and especially the heating of the nozzle that the material is extruded through, may be controlled to remove an amount of solvent that results in the extruded material having desirable properties.

A method for producing a can formed from a can part and a flange part is provided, the flange part being formed as an annular body and, on a side oriented inward toward an axis of symmetry of the annular body, an interface forming a bearing for the can part. A base and a lateral wall are formed on the can part, and the can part is deep drawn and made into a target geometry with a defined wall thickness by virtue of the lateral wall being flow formed. The lateral wall has a formed interface with a material thickness greater than the wall thickness of the lateral wall, and the flange part is connected to the can part at the interface.

A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.

A seal assembly for a component of a turbomachine and method of assembly thereof is provided. The seal assembly includes at least one mating face positioned adjacent to the component and a seal coupled to the mating face. The seal includes an outer shell defining an interior space; an inner matrix filling the interior space comprising a plurality of unit cells comprising one or more metamaterials, wherein at least a portion of the plurality of unit cells are identical, and wherein the plurality of unit cells are repeated throughout the inner matrix; and one or more support struts extending throughout the inner matrix. The method of building the seal assembly may include selecting a first material for the outer shell and selecting the one or more metamaterials for the inner matrix based on the first material.

A method for manufacturing a turbo fan unit includes a step for preparing multiple fan blades and an other-side side plate, and a step for connecting each of the multiple fan blades to the other-side side plate by a welding process. In the preparing step, one of the fan blade and the side plate is prepared, in which a connecting-surface forming portion having a connecting surface and a welding projection protruded from the connecting surface is formed. The connecting surface connects one of the fan blade and the side plate to the other one of the fan blade and the side plate. In the connecting step, the welding projection is melted down and the connecting surface is connected to an opposing surface, which is the surface of one of the fan blade and the side plate and which is opposing to the connecting surface.

A method for manufacturing an annular heat exchanger intended to be mounted on the radially inner or outer face of an annular shell of a casing of a double-flow turbomachine, the method including: obtaining by extrusion a heat exchanger preform by a die shaped so that the preform includes: first pipes for the circulation of a fluid to be cooled, second pipes arranged on either side of the first pipes in a direction perpendicular to the direction of extrusion; making a hole from the outside in the preform, the hole leading into one of the second pipes of the preform; and introducing into the hole of the second given pipe a member for partially closing off its passage cross-section.

A turbocharger includes a wastegate valve, an actuator for the wastegate valve, and a link mechanism linking the wastegate valve with the actuator via a specific rod. A plate is a component of the link mechanism and connects the wastegate valve with the rod or connects the rod with the actuator. The plate includes a body portion in a plate shape and a pin portion protruding from the main body portion. The pin portion is in a tubular shape having a hollow portion opened to its outside. The pin portion is engageable with an other component of the link mechanism on its outer periphery to form a rotation axis of the other component.

A hybrid rocket motor includes a solid fuel element, and an oxidizer tank containing an oxidizer. The solid fuel element adjoins and at least partially defines a combustion chamber in which the solid fuel and the oxidizer are burned, to produce thrust from the hybrid rocket motor. The oxidizer tank is at least partially within the combustion chamber, and the entire oxidizer tank may be within the combustion chamber. The oxidizer tank may be protected by an insulating material, which may also serve as a structural material that contains the pressure of the oxidizer. The insulating material and the fuel material may both be polymer-based materials, although they may be different materials having different characteristics, for example including different additives to the same polymer material. The fuel element and the oxidizer tank may be made by additive manufacturing processes, for example by adding different materials in different locations.