An example multi-dimensional component building system includes a first chamber having at least one base disposed therein, a second chamber adjacent to and in fluid communication with the first chamber through a first door, and a third chamber adjacent to and in fluid communication with the second chamber through a second door. The second chamber is fluidly sealed from the first chamber if the first door is in a closed position. The second chamber is configured to receive the at least one base via a first transfer mechanism if the fluid parameters of the first chamber are approximately equal to the fluid parameters of the second chamber. The second chamber includes a directed heat source and a build-up material configured to form a component on the at least one base by melting or sintering. The third chamber is fluidly sealed from the second chamber if the first door is in a closed position. The third chamber is configured to receive the at least one base, having a formed component disposed thereon, via a second transfer mechanism if the second door is in an open position. The fluid parameters of the second chamber are not substantially affected by fluid communication with the first chamber or the third chamber.

A jet engine has an inlet 11 configured to introduce air, and a combustor 12 having a fuel injection port 30a that injects a fuel, and configured to combust the fuel injected from the fuel injection port 30a by using the air. The combustor 12 has a separation section 14 defining the air passage FA through which the air flows, between a rear end 15 of the inlet and the fuel injection port 30a. A plurality of turbulent flow generating sections (20;25) are arranged in the separation section 14 to makes the air flow turbulent. Each of the plurality of turbulent flow generating sections (20;25) contains a member (21;22;25B) which can restrain the turbulence of the air flow by moving or disappearing. It can be prevented that a high-pressure region reaches the inlet so that the thrust of the jet engine is reduced.

A jet engine has an inlet 11 configured to introduce air, and a combustor 12 having a fuel injection port 30a that injects a fuel, and configured to combust the fuel injected from the fuel injection port 30a by using the air. The combustor 12 has a separation section 14 defining the air passage FA through which the air flows, between a rear end 15 of the inlet and the fuel injection port 30a. A plurality of turbulent flow generating sections (20;25) are arranged in the separation section 14 to makes the air flow turbulent. Each of the plurality of turbulent flow generating sections (20;25) contains a member (21;22;25B) which can restrain the turbulence of the air flow by moving or disappearing. It can be prevented that a high-pressure region reaches the inlet so that the thrust of the jet engine is reduced.

A system and method for cleaning an installed gas turbine engine is provided. The system may include a controller on an engine core, wherein the engine core defines a primary gas path and includes at least one airfoil extending into the primary gas path. The method may include initiating a cleaning program and directing a cleaning fluid toward the engine core in response to the initiation of the cleaning program. The method may further include initiating delivery of the cleaning fluid as a non-vaporized liquid within the primary gas path to the engine core.

A center vent tube support device includes: an annular sleeve having an inner surface that comes into contact with an outer surface of a center vent tube; a ring formed of a pair of segments and placed between the sleeve and a shaft; and an annular nut for fixing the ring to the sleeve. An outer surface of the sleeve or the nut includes a pressurizing surface formed as a conical surface. Each ring segment includes a supporting surface formed as a cylindrical surface having a diameter equal to an inner diameter of the main shaft in a portion where the device is installed, a bearing surface formed as a conical surface having a vertex angle equal to that of the conical surface forming the pressurizing surface, a pair of side surfaces, and a pair of end faces formed as planes each spaced from a plane including the axis.

A center vent tube support device includes: an annular sleeve having an inner surface that comes into contact with an outer surface of a center vent tube; a ring formed of a pair of segments and placed between the sleeve and a shaft; and an annular nut for fixing the ring to the sleeve. An outer surface of the sleeve or the nut includes a pressurizing surface formed as a conical surface. Each ring segment includes a supporting surface formed as a cylindrical surface having a diameter equal to an inner diameter of the main shaft in a portion where the device is installed, a bearing surface formed as a conical surface having a vertex angle equal to that of the conical surface forming the pressurizing surface, a pair of side surfaces, and a pair of end faces formed as planes each spaced from a plane including the axis.

This power generation system (20A) includes a plurality of power generation units (50A, 50B, 50C, . . . ) which are provided in parallel, wherein each of the power generation units (50A, 50B, 50C, . . . ) includes an expander (26) configured to be rotated by a working medium, a power generator (28) configured to generate power through rotation of the expander (26), a rectifier (29), a medium circulation system (22) configured to pump the working medium into the expander (26), a relay (70) configured to interrupt power between the power generator (28) and an external power system (30), an operating unit (40A, 40B) configured to be operated when maintenance starts, and a relay driving unit (71) configured to interrupt power between the power generator (28) and the external power system (30) by the relay (70) when the operating unit (40A, 40B) has been operated.

This power generation system (20A) includes a plurality of power generation units (50A, 50B, 50C, . . . ) which are provided in parallel, wherein each of the power generation units (50A, 50B, 50C, . . . ) includes an expander (26) configured to be rotated by a working medium, a power generator (28) configured to generate power through rotation of the expander (26), a rectifier (29), a medium circulation system (22) configured to pump the working medium into the expander (26), a relay (70) configured to interrupt power between the power generator (28) and an external power system (30), an operating unit (40A, 40B) configured to be operated when maintenance starts, and a relay driving unit (71) configured to interrupt power between the power generator (28) and the external power system (30) by the relay (70) when the operating unit (40A, 40B) has been operated.

A system includes an internal manifold ring defining at least one circumferentially extending flow channel. A plurality of feed arms extends outward from the manifold ring. A circumferentially segmented outer ring can be supported from the feed arms, outboard of the feed arms. Each feed arm can include a plurality of branches extending therefrom, wherein each branch is in fluid communication with the manifold ring through a respective one of the feed arms. A plurality of nozzles can be included, each nozzle connected to a respective one of the branches, wherein the system is devoid of nozzles radially inward from the manifold ring.

A gas turbine engine includes a nosecone assembly attached to a gas turbine engine. The nosecone assembly includes a support structure and a nosecone attached to the support structure. The nosecone includes at least a first tool hole extending through the nosecone. The first tool hole is structurally reinforced.