Abstract: A gas atomization nozzle includes a through-hole formed along a center line; a nozzle portion configured of a Laval nozzle which is disposed around the center line and provided to be inclined at a predetermined angle toward the center line; and swirling motion imparting means for imparting a swirling flow around the center line to gas which is injected from the nozzle portion. The nozzle portion is formed in a ring shape which is continuous around the center line, and the swirling motion imparting means is configured as a fin provided in the nozzle portion to impart a swirling flow.

Abstract: A gas turbine for an aircraft includes: blades each including a blade body extending outward from a rotor rotating about an axis in a radial direction of the rotor and a fin protruding from an outer peripheral surface of a blade shroud formed on a distal end of the blade body; a casing installed to form gaps between the casing and the fins; and vanes each including a vane shroud formed such that at least a leading end portion of the vane shroud formed upstream in an axial direction is located outside with respect to an extended line of an inner peripheral surface of the casing in the radial direction.

Abstract: Provided is a blade manufacturing method by which a blade of a stable quality can be manufactured. The present invention involves: a shaping process in which a blade is molded by means of metal injection molding by injecting metal powder toward a mold; a jig attaching process in which a jig serving as a mold, which is divided into at least two parts forming the shape of the blade therebetween, is attached to the blade by sandwiching the blade between the shape-forming surfaces; and a thermal treatment process in which a thermal treatment is applied to the blade to which the jig has been attached.

Abstract: A coating method includes depositing a slurry including a coarsely particulate ceramic and a finely particulate ceramic on a base material configured with an oxide-based ceramics matrix composite such that a proportion of coarse particles decreases towards a surface of the base material; forming a bond coating by performing a heat treatment on the base material on which the slurry has been deposited; and forming a top coating by thermally spraying a ceramic onto the bond coating. The oxide-based ceramics matrix composite is an alumina silica type oxide-based ceramics matrix composite. The coarsely particulate ceramic and the finely particulate ceramic are alumina-based powder.

Abstract: A gas turbine includes a compressor, a combustor, and a turbine. The compressor, the combustor, and the turbine are arranged along an extending direction of a rotating shaft. The gas turbine also includes a combustor casing housing the combustor and a turbine casing housing the turbine. The combustor casing and the turbine casing are joined to each other via respective flanges thereof projecting toward the outside. The gas turbine further includes a projection part on an inner face of the combustor casing. The projection part projects toward the inside in a radial direction in at least part of a range in the extending direction of the rotating shaft between the flanges and an end of a combustion chamber on the compressor side in the combustor.

Abstract: Included in a gas turbine casing and a gas turbine are a first casing that has a first flange portion, first connecting holes, and first notches; a second casing that has a second flange portion, a plurality of second connecting holes, and second notches; and fastening bolts to fasten the first flange portion and the second flange portion with the portions being closely attached to each other and with each fastening bolt penetrating the corresponding first and second connecting holes. A first radial direction ratio (L/H) is set to be from 0.09 to 0.11 where H is a length of each of the first flange portion and the second flange portion in a radial direction, and L is a length of each of the first notch and the second notch in a radial direction.

Abstract: The present invention enables machining to be easily performed and reduces stress concentration on a machined hole that is formed in a cylindrical member. Recesses (2) recessed in the depth direction of a machined hole (1) are formed on circumferential side-portions of the machined hole 1 formed in a cylindrical member (10). In each of the recesses (2), a part of the opening edge is formed to be a circular arc portion (2a) that has a circular arc shape, the bottom is formed to be gradually shallowed by an inclined surface (2c) toward an opened portion (2b) in which the circular arc shape is opened, from a part along the circular arc portion (2a), and the circular arc portion (2a) is disposed toward the machined hole (1).

Abstract: A metal member related to the present invention is provided with crystal grains of a metal and a granular reinforcing substance formed at boundaries of the crystal grains. The reinforcing substance includes grains of a shape with a grain area equivalent grain size larger than 1/100 of a grain area equivalent grain size of the crystal grains. The granular reinforcing substance preferably includes grains with a grain area equivalent grain size smaller than ? of the grain area equivalent grain size of the crystal grains. Additionally, the granular reinforcing substance preferably includes grains of a shape wherein a value of a length, in a first direction in which a length thereof is longest, divided by a length of a longest part in a direction orthogonal to the first direction is smaller than 5. A metal member with a high strength at high temperatures is manufactured by metal powder injection molding.

Abstract: A method for implementing an abradable coating comprising: a pattern-forming step in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a firing step in which the slurry pattern formed on the surface of the thermal barrier coating layer is fired to form an abradable coating layer. A ceramic material included in the thermal barrier coating layer and ceramic particles included in the abradable coating layer are of the same type.

Abstract: A method for metal powder injection molding includes injecting a first metal powder of a TiAl-based intermetallic compound into a mold, and molding the first metal powder through use of an injection molding machine; injecting a second metal powder of a TiAl-based intermetallic compound having a same constituent as the first metal powder and having a different average particle diameter from the first metal powder into a mold, and molding the second metal powder through use of the injection molding machine; and sintering molded articles obtained by molding the first metal powder and the second metal powder, and producing a mixed sintered compact in which a first sintered compact of the molded article obtained by molding the first metal powder and a second sintered compact of the molded article obtained by molding the second metal powder are integrated.

Abstract: A gas atomization nozzle includes a through-hole formed along a center line; a nozzle portion configured of a Laval nozzle which is disposed around the center line and provided to be inclined at a predetermined angle toward the center line; and swirling motion imparting means for imparting a swirling flow around the center line to gas which is injected from the nozzle portion. The nozzle portion is formed in a ring shape which is continuous around the center line, and the swirling motion imparting means is configured as a fin provided in the nozzle portion to impart a swirling flow.

Abstract: Provided is a transition duct that forms an annular gas flow channel through which a main flow gas flows from a high-pressure turbine to a low-pressure turbine, wherein the gas flow channel has an inner peripheral flow channel surface and an outer peripheral flow channel surface, the inner peripheral flow channel surface and the outer peripheral flow channel surface extend radially outward while angles of inclination relative to an axial direction of a rotating shaft change from the high-pressure turbine (first turbine) toward the low-pressure turbine (second turbine), and an inner peripheral maximum inclined part is provided in a range A2 that extends in the axial direction from a position of alignment with an outer peripheral maximum inclined part to a position advanced toward the low-pressure turbine by a length no more than 20% of the duct length.

Abstract: A method for constructing an abradable coating comprises: a slurry layer formation step S2 in which a slurry layer 31 is formed on the surface of a base material 30 using a slurry containing ceramic particles and a solvent; a calcination step S3 in which the slurry layer 31 formed on the surface of the base material 30 is sintered and a sintered layer 35 to be a portion of an abradable coating layer 22 is formed; and a slurry removal step S5 in which extraneous slurry is removed after the abradable coating layer 22 has been formed on the surface of the base material 30, a plurality of the sintered layers 35 having been laminated in the abradable coating layer 22 through a plurality of repeated cycles of the slurry layer formation step S2 and the calcination step S3.

Abstract: A method is for producing a TiAl-based intermetallic sintered compact. The method includes mixing Ti powder, Al powder, and a binder to yield a mixture; molding the mixture into a molded product having a predetermined shape with a metal injection molder; placing the molded product in a preliminary sintering die having a storage space inside; performing sintering at a predetermined preliminary sintering temperature to produce a preliminary sintered compact; releasing the preliminary sintered compact from the preliminary sintering die; and performing sintering at a sintering temperature higher than the preliminary sintering temperature to form the TiAl-based intermetallic sintered compact.

Abstract: A method for producing a TiAl-based intermetallic sintered compact includes sintering TiAl-based powder to produce a TiAl-based intermetallic sintered compact. The TiAl-based powder contains a TiAl-based intermetallic compound in which Ti and Al are bonded and an additional metal. The additional metal is Ni, or Ni and Fe.

Abstract: An aircraft component is used in a gas turbine engine for an aircraft. The aircraft component includes an annular part having an outer peripheral surface, and a boss part protruding from the outer peripheral surface of the annular part in a radial direction. In the boss part, at least two through-holes are formed to penetrate the boss part in the radial direction at predetermined intervals. In the boss part around the two through-holes, a cut-out part where a part of the boss part is cut out is formed.

Abstract: An aircraft component is used for an aircraft gas-turbine engine. The aircraft component includes an annular part, a flange, and a boss. The annular part has an outer circumferential surface. The flange is formed at one end portion of the annular part in an axial direction. The boss projects from the outer circumferential surface of the annular part to the radial direction. On a section cut along an axial direction of the annular part, the outer circumferential surface of the annular part between the flange and the boss has a taper part that is formed into a tapered shape in which plate thickness becomes thicker from the flange toward the boss.

Abstract: By melting a shaping material in which a metal powder and a binder are mixed and by carrying out injection molding (primary shaping) in an injection mold, an injection molded body, or an intermediate shaped body are produced. The injection molded body or the intermediate shaped body is placed by a transfer mold and is subjected to a gravity shaping (secondary shaping) with a transformation. A sintered body is manufactured by carrying out debindering and sintering to the injection molded body.

Abstract: A method for implementing an abradable coating comprising: a pattern-forming step in which, using a slurry containing ceramic particles and solvent, a slurry pattern is formed on the surface of a thermal barrier coating layer; and a firing step in which the slurry pattern formed on the surface of the thermal barrier coating layer is fired to form an abradable coating layer. A ceramic material included in the thermal barrier coating layer and ceramic particles included in the abradable coating layer are of the same type.

Abstract: Provided are a nickel-base alloy having high high-temperature strength, a turbine blade using same, and a method for producing an injection molded article of the nickel-base alloy. The nickel-base alloy contains: at least one metal element from among chrome, molybdenum, and niobium; nickel; aluminum; and carbon. The nickel-base alloy comprises a plurality of crystal grains and a plurality of precipitates. The areas between the individual crystal grains in the nickel-base alloy, i.e., the boundaries of the individual crystal grains serve as crystal grain boundaries. The crystal grains are crystals in which nickel is the primary component. The precipitates are precipitated on the crystal grain boundaries. The precipitates are carbides comprising: at least one metal element from among chrome, molybdenum, and niobium; and carbon. The carbides have a diameter of 0.1-10 ?m and an aspect ratio of 3 or more.