An airfoil profile for a turbine blade of a gas turbine is provided. The turbine blade may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

An airfoil profile for a turbine blade of a gas turbine is provided. The turbine blade may include an airfoil portion having an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table 1, wherein the X, Y, and Z coordinates are distances in inches measured in a Cartesian coordinate system, the corresponding X and Y coordinates, when connected by a smooth continuous arc, define one of a plurality of airfoil profile sections at each Z distance, and the plurality of airfoil profile sections, when joined together by smooth continuous arcs, define an airfoil shape.

A system for recapturing energy may include a thermoelectric generator (TEG) assembly for thermally attaching to a surface heated by plasma or ionization heating. The TEG assembly may include a first level thermoelectric generator module (TEM). The first level TEM may include a hot side that is thermally attached to the surface, a cold side and a plurality of TEG devices disposed between the hot side and the cold side. A second level TEM may be stacked on the first level TEM. A hot side of the second level TEM may be thermally attached to the cold side of the first level TEM. The plurality of TEG devices generate an electric current based on a temperature differential across the TEG devices. The TEG assembly may also include an electrical wiring system that electrically connects the TEMs and supplies the electric current generated to an electrical power apparatus.

A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

After a free-form surface is machined on an elongated material 1 with a projection 3 and a blade root 4 held, the holding of the projection 3 is released to release strain generated during machining. Upon release of the holding, the entire elongated material 1 deforms, and the projection 3 moves from a holding position A to a strain-released position B. A re-holding position C obtained by correcting the position B by the deformation amount of the elongated material 1 due to the weight of the elongated material 1 is determined, and the projection 3 is held again at the re-holding position C for further machining the free-form surface on the elongated material 1.

A gas turbine engine has a compressor section with a downstream most end and a cooling air tap at a location spaced upstream from the downstream most end. The cooling air tap is passed through at least one boost compressor and at least one heat exchanger, and then passed to a turbine section to cool the turbine section. The boost compressor is driven by a driveshaft which is driven by the turbine section. A boost turbine selectively drives the boost compressor.

A gas turbine combustor includes: an external cylinder (31); an inner cylinder (32) provided inside the external cylinder (31) to form an air passage (30) between the external cylinder (31) and the inner cylinder (32); a pilot nozzle (35) provided in a center part of the inner cylinder (32) along a direction of a combustor axis (S); a plurality of main nozzles (36) provided on an inner peripheral surface of the inner cylinder (32) along a circumferential direction thereof so as to surround the pilot nozzle (35), the plurality of main nozzles (36) premixing fuel with combustion air introduced to the air passage (30) and ejecting the fuel into the inner cylinder (32); and a top hat nozzle (41) provided inside the air passage (30) across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles (36).

A gas turbine combustor includes: an external cylinder (31); an inner cylinder (32) provided inside the external cylinder (31) to form an air passage (30) between the external cylinder (31) and the inner cylinder (32); a pilot nozzle (35) provided in a center part of the inner cylinder (32) along a direction of a combustor axis (S); a plurality of main nozzles (36) provided on an inner peripheral surface of the inner cylinder (32) along a circumferential direction thereof so as to surround the pilot nozzle (35), the plurality of main nozzles (36) premixing fuel with combustion air introduced to the air passage (30) and ejecting the fuel into the inner cylinder (32); and a top hat nozzle (41) provided inside the air passage (30) across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles (36).

A combustor for a gas turbine engine comprising: a combustion chamber; at least one fuel spray nozzle operable to deliver a fuel-air mixture into the combustion chamber, wherein during operation of the gas turbine engine the fuel-air mixture is combusted in the combustion chamber, thereby producing a combustion flame; a microwave generator coupled to a waveguide arranged to guide microwaves from the microwave generator into the combustion chamber such that the microwaves are incident on at least a portion of the combustion flame; and a detector operable to detect at least a portion of the microwaves reflected by the combustion flame and/or atomised fuel droplets.

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.