Abstract: An object is to realize combustion flame which can further reduce the amount of NOx generation. A combustor (14) includes a pilot nozzle (40); a plurality of main nozzles (44) arranged apart from the pilot nozzle (40) in the circumferential direction on the outer peripheral side of the pilot nozzle (40) and configured to perform premix combustion; a combustor basket (34) surrounding the pilot nozzle (40) and each main nozzle (44); an outlet outer ring (50) provided at a tip end of the combustor basket (34); and a combustion liner (36) fitted, at an inner surface thereof, onto the outer periphery of the combustor basket (34) and surrounding the outlet outer ring (50). The outlet outer ring (50) is formed parallel to an inner wall surface (66) of the combustion liner (36).

Abstract: A combustor (10) according to the invention includes: a combustor basket (14) in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece (17) in which a tip portion of the combustor basket (14) is inserted with a gap (C) therebetween; a spring clip (19) that seals the gap between the combustor basket (14) and the transition piece (17); a throttle section (21) that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece (17) on the tip side of the combustor basket (14), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device (22) for cooling the throttle section (21).

Abstract: 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).

Abstract: An object is to realize combustion flame which can further reduce the amount of NOx generation. A combustor (14) includes a pilot nozzle (40); a plurality of main nozzles (44) arranged apart from the pilot nozzle (40) in the circumferential direction on the outer peripheral side of the pilot nozzle (40) and configured to perform premix combustion; a combustor basket (34) surrounding the pilot nozzle (40) and each main nozzle (44); an outlet outer ring (50) provided at a tip end of the combustor basket (34); and a combustion liner (36) fitted, at an inner surface thereof, onto the outer periphery of the combustor basket (34) and surrounding the outlet outer ring (50). The outlet outer ring (50) is formed parallel to an inner wall surface (66) of the combustion liner (36).

Abstract: A combustor includes a combustion chamber and an acoustic liner, wherein through-holes through are formed in a wall of the combustion chamber, a plurality of rows of the through-holes is arranged in a lengthwise direction of the combustor, the through-holes of a first through-hole row are shifted with respect to the through-holes of a second through-hole row so that centers of the through-holes of the first and second through-hole rows adjacent each other are staggered in the circumferential direction, cooling grooves are formed so as to avoid the through-holes inside that is sandwiched between the outer peripheral surface and the inner peripheral surface of the combustion chamber, and the cooling grooves include transverse cooling grooves extending in the circumferential direction between rows of the through-holes, and longitudinal cooling grooves extending in the lengthwise direction between the through-holes and connecting the transverse cooling grooves adjacent to each other.

Abstract: In a gas turbine combustor and a gas turbine, an air passage (54) that supplies combustion high-pressure air, a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) that supply fuel, and openings (64) that supply film air (cooling air) are provided with respect to a combustor inner cylinder (42), and contraction members (71, 72, and 73) are arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder (42). The contraction members (71, 72, and 73) are provided in a predetermined area in the circumferential direction excluding penetrating portions (74, 75, and 76), which do not disturb the flow of cooling air, thereby enabling to suppress generation of carbon monoxide and the like and to suppress the occurrence of unstable combustion.

Abstract: A combustor (10) according to the invention includes: a combustor basket (14) in which compressed air and fuel are mixed with each other and the mixture is combusted; a transition piece (17) in which a tip portion of the combustor basket (14) is inserted with a gap (C) therebetween; a spring clip (19) that seals the gap between the combustor basket (14) and the transition piece (17); a throttle section (21) that is provided in an opening portion (Ck) of the gap (C) that is opened to the transition piece (17) on the tip side of the combustor basket (14), and narrows an opening area of the opening portion (Ck), compared to the base end side; and cooling device (22) for cooling the throttle section (21).

Abstract: 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).

Abstract: In a gas turbine combustor and a gas turbine, an air passage (54) that supplies combustion high-pressure air, a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) that supply fuel, and openings (64) that supply film air (cooling air) are provided with respect to a combustor inner cylinder (42), and contraction members (71, 72, and 73) are arranged along a circumferential direction on an inner wall surface in a downstream of a flow direction of combustion gas in the inner cylinder (42). The contraction members (71, 72, and 73) are provided in a predetermined area in the circumferential direction excluding penetrating portions (74, 75, and 76), which do not disturb the flow of cooling air, thereby enabling to suppress generation of carbon monoxide and the like and to suppress the occurrence of unstable combustion.

Abstract: In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor (3) is provided with a first box body (30), which is installed outside an object body (20) such as a combustor basket (6), a transition piece (7) or a bypass duct (11) so as to form a first internal space (31) having a predetermined capacity; and a first throat (32) having a predetermined length which has one end (32a) open to a side wall (20a) of the object body (20) and has the other end (32b) open to a first internal space (31); wherein, a first resistive element (33) having a multiple number of through-holes is inserted and engaged to one end (32a).

Abstract: Pilot fuel injected from fuel injection ports 21 of a pilot nozzle 2 bumps against an inner wall surface of a tapered portion of an inner circumference of a cone 41 of a pilot cone 4. At this time, the position where a pilot fuel from the fuel injection ports 21 hits is located in a range from a middle of the tapered portion of the inner circumference of a cone 41 to a downstream-side tip thereof.

Abstract: A gas turbine combustor having an inner tube and a transition pipe connected together is provided. The combustor includes an internal swirler and an external swirler. The internal swirler is composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring. The external swirler is composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring. The internal swirler and the external swirler are disposed within the inner tube.

Abstract: A premixing nozzle includes swirler blades for agitating combustion air inside a nozzle body. Each one end of the swirler blades is fitted to the nozzle body, and the other end is connected to a hub, respectively. The tip portion of a fuel nozzle shaft is conical, and a part of the tip portion is arranged inside the hub. A combustion gas flows into the hub from a space between the tip portion of the fuel nozzle shaft and the upstream end of the hub, passes through between the tip portion and the inner peripheral surface of the hub, and flows toward the downstream of the hub.

Abstract: Pilot fuel being injected from fuel injection ports 21 of a pilot nozzle 2 bumps against an inner wall surface of the tapered portion of the inner circumference of a cone 41 of a pilot cone 4. At this time, the position where the pilot fuel from the fuel injection ports 21 hits is located in the range from the middle of the tapered portion of the inner circumference of a cone 41 to the downstream-side tip thereof.

Abstract: A combustor of a gas turbine, which is composed of an inner tube and a transition pipe connected together, comprising: an internal swirler composed of a cylindrical inward swirler ring disposed concentrically with respect to a central axis of the inner tube, and a plurality of inward swirler vanes provided on an outer peripheral surface of the inward swirler ring; and an external swirler composed of a cylindrical outward swirler ring disposed on an outer peripheral side of the inward swirler vanes and concentrically with respect to the inward swirler ring, and a plurality of outward swirler vanes provided on an outer peripheral surface of the outward swirler ring, the internal swirler and the external swirler being disposed within the inner tube.

Abstract: A combustor for a gas turbine has an arrangement to form a layer of cooling-air on an inner surface of a liner of a combustion chamber. This layer of the cooling air extends from a fuel nozzle block of the combustor toward a downstream side with respect to the liner.

Abstract: For the purpose of reduced NOx gas emission, a gas turbine engine comprises a cylinder having a combustion region inside of the cylinder; a resonator having a cavity and provided around the surface of the cylinder and sound absorption holes formed on the cylinder and having opening ends on the cylinder.

Abstract: In order to realize a stable decrease in NOx, a gas turbine combustor is supplied which can reduce combustion vibration. A combustor (3) is provided with a first box body (30), which is installed outside an object body (20) such as a combustor basket (6), a transition piece (7) or a bypass duct (11) so as to form a first internal space (31) having a predetermined capacity; and a first throat (32) having a predetermined length which has one end (32a) open to a side wall (20a) of the object body (20) and has the other end (32b) open to a first internal space (31); wherein, a first resistive element (33) having a multiple number of through-holes is inserted and engaged to one end (32a).

Abstract: There is provided a combustor comprising a fuel nozzle which is comprised of a rodlike body which has a fuel passage and which is located in an air passage; a plurality of hollow members which are connected to the fuel passage and which extend in radial directions from the rodlike body into the air passage; at least one injection port formed in each hollow member to inject a fuel from the fuel passage into the air passage; and a projection which extends from a farmost inner wall of each hollow member that is most distant from an axis of the rodlike body to the injection port that is most distant from the axis. A hole for leaking fuel that is connected to an air passage may be formed in a farmost inner wall of the hollow member that is more distant from an axis of a rodlike body than the injection port that is most distant from the axis, or may be formed to be adjacent to all the injection ports on an upstream or downstream side in the direction of the airflow.

Abstract: There is provided a combustor to burn fuel, comprising a bypass passage connected to one side of the combustor to supply air into the combustor; and an annular passage provided around the combustor and connected to the bypass passage, wherein air supplied through the bypass passage passes in the annular passage in the circumferential direction, and is uniformly supplied into the combustor in the circumferential direction thereof through an opening which connects the combustor and the annular passage. Accordingly, compressed air passing through the bypass passage can be supplied uniformly into a tail portion of the combustor, and unevenness of temperature distribution in a cross section of the combustor tail portion can be reduced.