Mitsubishi Heavy Industries Limited

Other

Tohoku Electric Power Company, Inc.

Mitsubishi Heavy Industries, Co., Ltd.

Kouichi Akagi

Tanehiro Shinohara

Masanori Yuri

Hidekazu Uehara

Mitsuru Inada

Takashi Nakano

Shin Nishimoto

Ryotaro Magoshi

Tadao Yashiki

Yasuhiro Ojiro

Koji Watanabe

Katsunori Tanaka

Satoshi Hada

Minoru Sato

Shinya Hashimoto

Shigemi Mandai

Eisaku Ito

Kazuo Uematsu

Taku Ichiryu

Hitoshi Morimoto

Keita Takamura

Yukihiro Hashimoto

Yutaka Ozawa

Rintaro Chikami

Zenichi Yoshida

Mitsuru Kondo

Yutaka Kawata

Nobuhiro Kunitake

Yoshichika Sato

Jun Kubota

Mitsuo Hasegawa

Masahiko Toyoda

Takahiro Ohta

Hironobu Hakoda

Shin Koga

Koji Takeshita

Souichirou Tomimoto

Takehiko Shimizu

Akihiro Kawaguchi

Setunori Sakakibara

Hidehiko Nakane

Kazuhiro Matsui

Yuichi Kobayashi

Kiryo Igarashi

Akio Ogose

Such a rotating blade body is supplied as can prevent not only local wear and deformation but also inadvertent vibration and can maintain cooling efficiency. A rotating blade body consists of a rotor discand rotating bladeswhich are assembled so as to extend from the outer circumference of the rotor discin a radial pattern, wherein blade root portionsof the rotating bladesare engaged into blade grooveswhich are formed along a direction of a rotating shaft on an edge of the outer circumference of the rotor discCirculation spacesfor the cooling air are formed along the direction of a rotating shaft between the bottom-end portionsof the blade root portionsand the bottom portionsof the blade grooves. Pushing-up memberswhich push up the rotating bladesoutward in a radial direction are inserted into the circulation spaces, maintaining circulation of the cooling air.

Rotating blade body and rotary machine using rotating blade body

An object of the present invention is to provide a shaft seal which reduces the leakage of gas from the high pressure side to the low pressure side, and has excellent corrosion-resistance, and a gas turbine which is equipped with the shaft seal; in order to achieve the object, the present invention provide a shaft seal comprising a plurality of flexible thin plates having width in the axial direction of a rotary shaft, tips thereof sliding against a peripheral face of said rotary shaft, and outer peripheral bases thereof being secured to a casing side maintaining a gap therebetween, said thin plates being laminated in the peripheral direction of said rotary shaft, enabling the outer periphery of said rotary shaft to be sealed, an acute angle being formed between the thin plates and the peripheral face of said rotary shaft; and a low pressure side side-plate and a high pressure side side-plate which are provided on both sides of said thin plates in the axial direction of said rotary shaft, wherein it further comprises a gas pressure adjusting mechanism, which when said thin plates are viewed cross-sectionally along an imaginary plane which is perpendicular to the direction of their width, the face of each thin plate which faces the rotary shaft is deemed a bottom face and the rear side is deemed a top face, and gas pressure from said high pressure side side-plate to said low pressure side side-plate is applied to said thin plates, ensures that the gas pressure applied to said bottom faces is higher than the gas pressure applied to said top faces at a given point along said cross-sectional face of said thin plates, and a gas turbine comprising such shaft seal.

Shaft seal and gas turbine

The shaft seal structure is based on a leaf seal that includes springs, disposed between the stator blades and the leaf seal ring, to force the leaf seal ring away from the rotation shaft, and pressure guiding grooves for guiding the fluid pressure, through a boundary of planar plates, to a space between the outer peripheral surface of the leaf seal ring and the inner peripheral surface of the stator blade. Also, a turbine may be provided with the leaf seal so as to reduce gas leakage from the high-pressure-region to the low-pressure-region as well as to control the frictional wear between the planar plates and the rotation shaft.

Shaft seal structure and turbine

This pilot nozzle has a fuel oil supply pipe disposed at the center of a heat-shielding air layer that is provided along an axial core, and a plurality of atomized-fluid supply paths are disposed in the circumferential direction of a cylinder unit that surrounds the outside of the heat-shielding air layer. The atomized-fluid supply paths and the fuel gas supply paths are disposed alternately and uniformly. Based on this structure, it is possible to take a large thickness for the heat-shielding air layer to a maximum extent in a radial direction. Therefore, it is possible to protect the fuel oil supply pipe disposed at the center, from high temperature at the outside of the pilot nozzle.

Pilot nozzle for a gas turbine combustor and supply path converter

A gas turbine blade ring is cooled by steam whose temperature, pressure and flow rate are controlled so that a clearance between a moving blade tip and blade ring is maintained appropriately. Steam from a steam turbine bottoming cycle ( ) flows into a blade ring cooling passage ( ) of a gas turbine ( ) via piping ( ) for cooling the blade ring. The steam, having cooled the blade ring, is supplied into a transition piece cooling passage ( ) of a combustor ( ) for cooling the transition piece, and is then recovered into the steam turbine bottoming cycle ( ) via piping ( ). While the steam cools the blade ring, the temperature, pressure and flow rate of the steam are controlled so that thermal elongation of the blade ring is adjusted and the clearance at the moving blade tip is controlled so as to approach a target value. Thus, the clearance is maintained as small as possible in operation and the gas turbine performance is enhanced.

Gas turbine cooling passages for blade rings, combustor transition piece connecting portions and stationary blades

The present invention reduces the amount of gas which leaks and flows from a high pressure side to a low pressure side of the axis and maintains good sealing performance even at high differential pressures. The invention discloses an axis sealing mechanism comprising casings which are supported inside of the stable portion, a plurality of planar plates, which are mutually spaced around the axis, each of which is fixed to the casings, positioned so that an inner end of each planar plate makes an acute angle with a peripheral surface of the axis and contacts the peripheral surface of the axis over a predetermined length in an axial direction, a high pressure side plate which is arranged at a high pressure side and a low pressure side plate which is arranged at a low pressure side so as to hold the planar plates therebetween and a flexible plate which is arranged between the planar plates and the high pressure side plate, and is flexible in an axial direction. The invention also discloses a turbine which provides the above sealing mechanism.

Axis seal mechanism and turbine

An internal cylinder which has the opening section from which combustion gas is blown out is inserted into the tail cylinder which becomes a flow path of the combustion gas, and is engaged with the tail cylinder, while securing a clearance between the edge of the opening section and the internal wall surface of the tail cylinder. Air compressed with a compressor is jetted from the clearance along the internal wall surface of the tail cylinder, and a film of cooling air is formed on the internal wall surface of the tail cylinder.

Gas turbine combustor

Cooling air passages are formed in the wall of an exhaust casing connected to a turbine casing of a gas turbine. Low pressure air extracted from the low pressure stage of an air compressor of the gas turbine is supplied to the cooling air passage from the portion near the downstream end of the exhaust casing. Cooling air flows through the cooling air passage toward the upstream end of the exhaust casing and then flows into an annular cavity formed in the turbine casing near the portion corresponding to the last turbine stage. Therefore, the metal temperature of the exhaust casing near the upstream end (near the joint between the exhaust casing and the turbine casing) is lowered by the cooling air and, as cooling air of a relatively high temperature is supplied to the cavity in the turbine casing, the metal temperature of the turbine casing near the downstream end becomes higher than that provided by a conventional cooling system. Therefore, the difference between the metal temperatures of the turbine casing and the exhaust casing becomes very small and the thermal stress exerted on the exhaust casing due to the temperature difference can be largely reduced.

Air-cooled gas turbine exhaust casing

A cooling structure of a combustor tail tube is capable of avoiding the formation of cracks in the tail tube by lessening thermal stress and preventing thermal deformation, thus extending the service life. A multiplicity of cooling jackets ( ) extend in the longitudinal direction of the tail tube of a gas turbine combustor along the entire circumference of the tail tube wall. The passage sectional area of the cooling jackets ( ) is varied depending on the metal temperature of parts of the tail tube ( ). For example, the passage sectional area of the cooling jackets ( ) formed at the rotor side wall and the mutually opposite side walls of the adjacent tail tube is larger than the passage sectional area of the cooling jackets ( ) formed at the casing side wall.

Cooling structure of a combustor tail tube

A shaft seal having a high abrasion resistance is disclosed, by which the leakage of the gas from the high-pressure side to the low-pressure side can be reduced. In the shaft seal, flexible leaves are multi-layered to form a ring shape. The shaft seal is mainly arranged around the rotation shaft of a gas turbine or the like. The relevant turbine comprises a casing, a compressor, a rotation shaft, moving blades attached to the rotation shaft, and stationary blades attached to the casing in a manner such that the stationary blades face the moving blades, wherein the shaft seals are provided between a plurality of stationary blades and the rotation shaft wherein the leaves of each shaft seal contact the rotation shaft. Under the rated operating conditions, the top ends of the leaves slightly separate from the surface of the rotation shaft due to the dynamic pressure generated by the rotation of the rotation shaft. When the turbine is not operated, the top ends of the leaves contact the rotation shaft again due to the elastic restoring force of the leaves.

Shaft seal and turbine using the same

Gas turbine combustor tail tube cooling structure is improved so that temperature distribution along tail tube axial direction is made gentle and large thermal stress is prevented from occurring resulting in enhancement of safety and reliability of the combustor tail tube. Supply jacket (,) is disposed between upstream side discharge jacket (,) and downstream side discharge jacket (,). The upstream side discharge jacket (,) is disposed apart from tail tube inlet (,) at position close to by-pass passage (,) so as to form non-cooled zone (A) in the vicinity of the tail tube inlet (,). On the downstream side thereof, the supply jacket (,) is disposed at position in tail tube (,) contracting portion and near the downstream side discharge jacket (,) so as to shorten length of cooling pipes there.

Cooling structure for combustor tail pipes

This invention concerns the use of pressurized steam as the cooling medium for a gas turbine combustor. It is distinguished by the following. Steam supply manifolds or ports for the cooling steam are provided on the gas inlet and outlet sides of the combustion chamber in the gas turbine combustor. A steam exhaust manifold or port for the cooling steam is provided between the gas inlet and outlet sides, in approximately the center of the chamber. Cooling channels for the steam are created in the external wall panel of the chamber between the steam supply manifolds and the exhaust manifold. The steam supplied into the wall panel through the steam supply manifolds on the gas inlet and outlet sides of the chamber is exhausted to the exterior via the steam exhaust manifold in the center of the chamber. This design allows pressurized steam with a high thermal capacity to be used to effectively cool the wall panels of the combustor, which are exposed to extremely hot combustion gases.

Steam cooling method for gas turbine combustor and apparatus therefor

Steam cooling type gas turbine combustor

A rotor shaft that is supported by a deep groove ball bearing a radial load and a unidirectional thrust load, and by a cylindrical roller bearing for bearing a radial load. Also, a pretension applying means is provided for applying a pretension to the rotor shaft in the same direction as the thrust load which is borne by the deep groove ball bearing.

Rotor shaft

Growing community of inventors

Takasago, Japan

Kouichi Akagi