Abstract: There is provided an exhaust section of a gas turbine and a gas turbine that can cool a strut and the periphery of a bearing without decreasing the efficiency of the gas turbine. A structure of an exhaust section of a gas turbine has: a casing in which a gas path part is formed; a bearing part that rotatably supports moving blades of a turbine section; a strut that extends inwardly from the casing and supports the bearing part; an opening formed in the casing; and a cooling flow channel that extends from the opening toward the bearing part along the strut to guide air at a lower temperature than an exhaust gas flowing in the gas path part to the gas path part and opens into the gas path part at a position downstream of a last-stage moving blade of the turbine section.

Abstract: There is provided an exhaust section of a gas turbine and a gas turbine that can cool a strut and the periphery of a bearing without decreasing the efficiency of the gas turbine. A structure of an exhaust section of a gas turbine has: a casing in which a gas path part is formed; a bearing part that rotatably supports moving blades of a turbine section; a strut that extends inwardly from the casing and supports the bearing part; an opening formed in the casing; and a cooling flow channel that extends from the opening toward the bearing part along the strut to guide air at a lower temperature than an exhaust gas flowing in the gas path part to the gas path part and opens into the gas path part at a position downstream of a last-stage moving blade of the turbine section.

Abstract: Such a gas turbine is provided as can put into practical use a control technology which detects clearance between the tip of rotating blade and the inner circumference surface of ring segment surrounding them and adjusts the temperature, the pressure and the flow volume of the cooling fluid for blade rings/ring segments and the cooling fluid for rotors based on the output. A sensor is provided to detect the clearance between the tip of the rotating blade and the inner circumference surface of the ring segment. A sensor is integrated together with a first guide pipe by having a posterior portion thereof screwed together to a secondary pipe being installed to an edge of the first guide pipe inside of which a cooling fluid is introduced into. The first guide pipe is pressed to the blade ring from the outside of the casing so as to retain.

Abstract: A gas turbine exhaust diffuser, comprising: a flow liner for guiding a hot gas; a flow guide portion extending downstream of the flow liner; an exhaust casing cylindrical portion in a form of a thick plate disposed outwardly of the flow liner at a distance from the flow liner; and an exhaust hood outer tube portion in a form of a thin plate having an outward end portion connected to a downstream side of the exhaust casing cylindrical portion, and having an inward end portion connected to the flow guide portion, and wherein a heat insulating material is applied to outer surfaces of the exhaust casing cylindrical portion and the flow guide portion and to an inner surface of the exhaust hood outer tube portion.

Abstract: A metallic packing is used to seal a connection between steam pipes. The metallic packing has an annular basement. This annular basement has an opening that joins the holes of the steam pipes. Two annular lips project from an inner circumference of the annular basement towards a central axis of the opening. Each annular lip steps away form the other lip, and the distance between free ends of the lips is longer than the width of the annular basement along the direction of the central axis.

Abstract: Such a gas turbine is provided as can put into practical use a control technology which detects clearance between the tip of rotating blade and the inner circumference surface of ring segment surrounding them and adjusts the temperature, the pressure and the flow volume of the cooling fluid for blade rings/ring segments and the cooling fluid for rotors based on the output. A sensor is provided to detect the clearance between the tip of the rotating blade and the inner circumference surface of the ring segment. A sensor is integrated together with a first guide pipe by having a posterior portion thereof screwed together to a secondary pipe being installed to an edge of the first guide pipe inside of which a cooling fluid is introduced into. The first guide pipe is pressed to the blade ring from the outside of the casing so as to retain.

Abstract: The steam-cooling-type gas turbine is provided with communication passages in number equal to that of the front-stage stator blades and the rear-stage stator blades. Many communication passages are placed in the blade ring densely. As a result, in the blade ring, the temperature difference between the portion having the communication passages and the portion without the communication passages becomes smaller. This makes it possible to minimize the thermal deformation of the blade ring, thereby making it possible to provide uniform clearance between the fixed side such as the blade ring and the rotary side members.

Abstract: A vapor tube structure in a gas turbine comprises first connecting tubes fixed to a casing, second connecting tubes fixed to a blade ring, a recovery ring and a cooling recovery ring, a bellows tube of the flexible structure, springs, a tube and a piston rings provided between the first connecting tubes and the second connecting tubes. As a result, it is possible to absorb and follow the thermal expansion/contraction difference and prevent leaking of vapor.

Abstract: A metallic packing (1) according to the present invention is used to seal a connection between steam pipe (50a) and another steam pipe (50b). This metallic packing has an annular basement (3) that has an opening (2) that joins holes (51 and 54) of the steam pipes (50a and 50b), and annular lips (4 and 5) that forms a pair and project from inner circumference of the annular basement (3) towards a central axis of the opening (2). Each annular lip (4 and 5) steps away from the other lip, and the distance (H) between free ends (4a and 5a) of the lips (4 and 5) is longer than the width (D) of the annular basement (3) along the direction of the central axis.

Abstract: A shaft structure of a rotor tail end of a gas turbine in which a steam passage for supplying and recovering a steam for cooling rotor blades of the gas turbine extends along a center axis of the rotor assembly of the gas turbine is provided, wherein a center hole of the rotor tail end coaxial to the center axis of the steam passage is formed in the rotor tail end. Provision is also made of a thermal sleeve between the steam passage and the inner surface of the center hole of the rotor tail end, so that a thermal insulation gas layer is formed between the inner surface of the center hole of the rotor tail end and the thermal sleeve. The thermal insulation gas layer is isolated gas-tightly and liquid-tightly from the outside.

Abstract: Gas turbine steam passage seal structure between a blade ring and a stationary blade absorbs thermal deformation to prevent occurrence of minute gaps to thereby reduce leakage of steam as cooling medium. A blade ring steam passage hole, provided in the blade ring (10), has a stepped portion formed in a middle portion thereof. A stationary blade steam passage hole, provided in the stationary blade (50) so as to oppose the blade ring steam passage hole, has a stepped portion formed in an outer peripheral portion thereof. A cooling steam supply passage connection portion is constructed comprising a seal pipe (25) provided between the blade ring and stationary blade steam passage holes so as to communicate them with each other and a seal urging guide device (44, 47) provided at each of the stepped portions of the blade ring and stationary blade steam passage holes so as to effect a seal while fixedly supporting the seal pipe (25).

Abstract: The steam-cooling-type gas turbine is provided with communication passages in number equal to that of the front-stage stator blades and the rear-stage stator blades. Many communication passages are placed in the blade ring densely. As a result, in the blade ring, the temperature difference between the portion having the communication passages and the portion without the communication passages becomes smaller. This makes it possible to minimize the thermal deformation of the blade ring, thereby making it possible to provide uniform clearance between the fixed side such as the blade ring and the rotary side members.

Abstract: A vapor tube structure in a gas turbine comprises first connecting tubes fixed to a casing, second connecting tubes fixed to a blade ring, a recovery ring and a cooling recovery ring, a bellows tube of the flexible structure, springs, a tube and a piston rings provided between the first connecting tubes and the second connecting tubes. As a result, it is possible to absorb and follow the thermal expansion/contraction difference and prevent leaking of vapor.

Abstract: Gas turbine steam passage seal structure between a blade ring and a stationary blade absorbs thermal deformation to prevent occurrence of minute gaps to thereby reduce leakage of steam as cooling medium. A blade ring steam passage hole, provided in the blade ring (10), has a stepped portion formed in a middle portion thereof. A stationary blade steam passage hole, provided in the stationary blade (50) so as to oppose the blade ring steam passage hole, has a stepped portion formed in an outer peripheral portion thereof. A cooling steam supply passage connection portion is constructed comprising a seal pipe (25) provided between the blade ring and stationary blade steam passage holes so as to communicate them with each other and a seal urging guide device (44, 47) provided at each of the stepped portions of the blade ring and stationary blade steam passage holes so as to effect a seal while fixedly supporting the seal pipe (25).

Abstract: A shaft structure of a rotor tail end of a gas turbine in which a steam passage for supplying and recovering a steam for cooling rotor blades of the gas turbine extends along a center axis of the rotor assembly of the gas turbine is provided, wherein a center hole of the rotor tail end coaxial to the center axis of the steam passage is formed in the rotor tail end. Provision is also made of a thermal sleeve between the steam passage and the inner surface of the center hole of the rotor tail end, so that a thermal insulation gas layer is formed between the inner surface of the center hole of the rotor tail end and the thermal sleeve. The thermal insulation gas layer is isolated gas-tightly and liquid-tightly from the outside.