Mitsubishi Heavy Industries Limited

Mitsubishi Power, Ltd.

Mitsubishi Hitachi Power Systems, Ltd.

Yoshitaka Terada

Katsuyoshi Omae

Koichi Nishida

Tetsu Konishi

Hironori Tsukidate

Kunihiro Oga

Takashi Onozuka

Kenji Miyamoto

Satoshi Tanimura

Tomomi Koganezawa

Keisuke Miura

Shohei Yoshida

Yoshitaka Hirata

Kenta Taniguchi

Shin Kato

Shohei Numata

Jose Rodriguez

Toshihiko Saitoh

Kenta Kurihara

Shota Igarashi

Eiji Takami

Takehiko Nishikawa

Tadashi Kamiya

Hiroaki Nagahashi

Provided is a transition piece including a first flow path group formed by arraying a plurality of in-wall flow paths that extend inside a plate material forming the transition piece and a second flow path group that is positioned on a side closer to a combustor liner than the first flow path group is. Each in-wall flow path in the first flow path group and the second flow path group has an inlet that is located at one end section in a flow direction of a combustion gas and that faces a compressed air main flow path, and an outlet that is located at the other end section in the flow direction of the combustion gas and that faces a combustion gas flow path. An installation area of the first flow path group and an installation area of the second flow path group partially overlap in the flow direction of the combustion gas by a predetermined overlap amount, and the overlap amount is set large for a portion where a shape change of the transition piece is relatively large, as compared with a portion where the shape change of the transition piece is relatively small.

Transition piece, combustor, and gas turbine engine

A gas turbine combustor includes multiple aft frames each having a floating seal that seals a gap between an aft frame and a gas turbine in inner and outer peripheries of the aft frame, and a side seal that seals a gap between the aft frames adjacent to each other in a circumferential direction, and a corner seal that is placed in a gap portion provided between corner portions of the aft frames adjacent to each other in the circumferential direction, seals air leaking from at least the gap portion into the gas turbine side, and is independent of the floating seal and the side seal.

Gas turbine combustor

The present invention reduces the concentration of thermal stress on a burner. A gas turbine combustor receiving compressed air from a compressor, mixing the compressed air with a fuel, burning the mixture to generate a combustion gas, and supplying the combustion gas to a turbine. The combustor includes: an inner cylinder internally forming a combustion chamber; an outer cylinder covering the inner cylinder and forming a cylindrical outer circumferential flow path between the inner and outer cylinders to allow the compressed air to flow; and a burner mounted on an end of the outer cylinder, which is positioned on an opposite side to a turbine side, and facing the combustion chamber. The burner includes a cylindrical base frame including a cavity distributing the fuel, and fuel nozzles circularly arranged as viewed from the combustion chamber and connected to the cavity. When viewed from the combustion chamber, slits extending radially are formed in the base frame such that each separate the circumferentially adjacent fuel nozzles from each other.

Gas turbine combustor and gas turbine

The present invention reduces thermal stress that is applied to the weld zone of a cavity formed in the structural material of a burner. The burner includes the cavity distributing a fuel to fuel nozzles. The cavity is demarcated by a groove formed in the structural material of the burner so as to create a level difference at an opening, and a cover fitted into the level difference to close the groove. The cover is formed by a web covering the opening in the groove and a flange extending in the depth direction of the groove to be fitted into the level difference, and is joined by welding to the structural material in such a manner as to have an L-shaped cross-section. When viewed in a cross-section orthogonal to the groove, a cover-side inner surface that is an inner surface of the flange forming a lateral surface of the cavity is flush with a groove-side inner surface that is an inner surface of the groove forming a lateral surface of the cavity. The boundary between the cover-side inner surface and the groove-side inner surface is away from a first corner of the cavity sandwiched between the cover-side inner surface and the inner surface of the web forming a ceiling surface of the cavity.

A combustor nozzle assembly includes: a nozzle mounting base which blocks a combustor insertion opening formed in a turbine casing; a nozzle rod which passes through the nozzle mounting base and has a rod tip portion and a rod base end portion; an oil fuel pipe which is as a whole inserted into the nozzle rod, which has a pipe tip portion and a pipe base end portion, in which fuel is supplied to the inside through the rod base end portion, and which injects the fuel from the pipe tip portion through the rod tip portion; and an O-ring which is disposed in the rod base end portion and suppresses leakage of fuel to the pipe tip portion side between the inner periphery side of the nozzle rod and the outer periphery side of the oil fuel pipe.

Combustor nozzle assembly, combustor equipped with the same, and gas turbine

A combustor of the present invention includes: a plurality of nozzles which is arranged around the central axis of a combustor and of which each base end is connected to an oil supply tube; a nozzle tube base which supports the plurality of nozzles and includes an oil chamber supplying fuel to the nozzles via an oil inflow portion provided in each oil supply tube; a first guide portion which faces the center of the combustor inside the oil chamber and guides the oil remaining inside the oil chamber to the oil inflow portion; and a second guide portion which faces the base end of the combustor inside the oil chamber and guides the oil remaining inside the oil chamber to the oil inflow portion.

Combustor and gas turbine

An object is to provide a low cost gas turbine combustor. The gas turbine combustor has a plurality of main nozzles annularly supported on a nozzle pipe base (), and the main nozzles each have an oil fuel path for supplying oil fuel and a gas fuel path for supplying gas fuel. A plurality of the oil fuel paths are provided to penetrate the nozzle pipe base (), and a plurality of lengths of upright piping () are provided to be connected to the oil fuel paths, respectively, and be erected on the nozzle pipe base (). A plurality of lengths of connection piping () for interconnecting the lengths of the upright piping () in a polygonal shape at a minimum distance are provided outside the nozzle pipe base (). An oil fuel supply section () is connected to one of the lengths of the connection piping () to distribute oil fuel to each of the oil fuel paths.

Gas turbine combustor having a dual fuel supply system

A low cost gas turbine combustor has main nozzles having a cylindrical central tube using an interior as an oil fuel path, a cylindrical outer tube disposed on an outermost periphery of the main nozzle, and a support tube disposed between the central tube and the outer tube, the central tube, the outer tube and the support tube each being formed independently. The support tube has such an internal diameter as to form a clearance becoming an insulating air layer between the support tube and an outer periphery of the central tube, and includes supporting portions formed on an axially upstream side and radially contacting an inner periphery of the outer tube groove portions formed along an axial direction between the supporting portions, and a cylindrical portion formed on an axially downstream side and having an external diameter equal to or smaller than an external diameter of the groove portions.

A punched metal plateis constructed so as to be in a ring shape covering a space between the outside wall of the combustor basketand the inside wall of the external cylinderand at the same time is constructed to be a perforated plate having a plurality of holes. In addition, ribsare provided in a radial pattern against the axis of a combustor in a manner that both ends of a ribare in contact with the outside wall of the combustor basketand the inside wall of the external cylinder. Additionally, ribsare provided in a plural number, and the plurality of ribsare arranged so as to be equally spaced in the circumferential direction of a combustor and connected to the external cylinder, thereby supporting the combustor basket

Growing community of inventors

Yokohama, Japan

Yoshitaka Terada