A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine.

A method for fabricating a thrust chamber liner for a rocket engine commences with a ring made from a first material on a build plate. A base layer of a second material in powder form is deposited on the exposed axial end of the ring. A laser beam is directed towards the base layer and the ring such that energy associated with the laser beam melts the base layer and a portion of the ring adjacent to the base layer. A melted portion of the base layer intermixes with a melted portion of the ring. Following this step, additional layers of the second material are deposited on the base layer. The first axial end of the ring is then exposed and additional layers of the first material are deposited on the first axial end of the ring.

A method of fabricating a combustor thermal shield comprising a combustor panel, a cooling feature, and an attachment feature, the combustor thermal shield to be used in a gas turbine engine combustor, includes shaping a sheet of material used to form the combustor panel. The method also includes additively manufacturing the cooling feature onto the sheet of material forming the combustor panel. The method also includes attaching the attachment feature to the sheet of material forming the combustor panel. The method also includes curving the sheet of material forming the combustor panel to achieve a curve profile according to a design of the gas turbine engine combustor.

A method of reconditioning and fabricating turbine components is provided. In one embodiment, the method is performed on a fuel nozzle assembly of a gas turbine, and comprises providing a pre-assembled fuel nozzle assembly having a base, a body extending from the base to a fuel nozzle tip, an inner assembly, and an outer assembly. The method further comprises removing at least a portion of the fuel nozzle tip and the inner assembly, coupling and joining a replacement inner assembly to the base, and coupling and joining a replacement fuel nozzle tip to the replacement inner assembly and to the outer assembly to provide a reconditioned fuel nozzle.

A method of assembling an annular combustion chamber assembly comprises positioning a plurality of first combustion chamber segments circumferentially side by side to form an annulus and removably securing the downstream end of each first combustion chamber segment to a first ring to form a first assembly. The method comprises positioning a plurality of second combustion chamber segments circumferentially side by side to form an annulus, removably securing the downstream end of each second combustion chamber segment to a second ring to form a second assembly. The method comprises removably securing the upstream end of each second combustion chamber segment of the second assembly to an annular upstream end wall. The method comprises inserting the second assembly into the first assembly and then removably securing the upstream end of each first combustion chamber segment of the first assembly to the annular upstream end wall to form the annular combustion chamber assembly.

An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.

A method for manufacturing a housing of a turbomachine, in particular a housing of a radial turbo compressor. The method includes the following steps: a) providing a hollow body that is closed in a circumferential direction and extends along an axis; b) coating the inner side of the hollow body with a corrosion-resistant layer that is more resistant to corrosion than the material of the hollow body; c) dividing the hollow body into two half-shells along the axis in a separation joint plane; d) assembling the housing by joining both half-shells and fastening both half-shells in the region of the separation joints, which were created by separation, by means of detachable fastening elements.

A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.

A method for manufacturing a housing of a turbomachine, in particular a housing of a radial turbo compressor. The method includes the following steps: a) providing a hollow body that is closed in a circumferential direction and extends along an axis; b) coating the inner side of the hollow body with a corrosion-resistant layer that is more resistant to corrosion than the material of the hollow body; c) dividing the hollow body into two half-shells along the axis in a separation joint plane; d) assembling the housing by joining both half-shells and fastening both half-shells in the region of the separation joints, which were created by separation, by means of detachable fastening elements.

A combustor which can be manufactured without requiring large-scale equipment and with a small number of processes and has a cooling fluid flow path sealed with high reliability. The combustor includes an inner cylinder made of metal constituting a combustion chamber, a cooling fluid flow path formed on an outer surface of the inner cylinder, and a sealing layer covering the outer surface of the inner cylinder to seal the cooling fluid flow path. The sealing layer is constituted by a bonded body of metal wires wound around the outer surface of the inner cylinder and metallurgically bonded to each other, and the sealing layer is bonded to the outer surface of the inner cylinder by metallurgical bonding.