Abstract: A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber.

Abstract: A gas turbine combustor and a method of operating the gas turbine combustor, with the gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of the combustion sleeve and having an air and fuel supply system, and a combustion main chamber disposed on a downstream side of the sub-chamber and having an air and fuel supply system. The combustion sub-chamber and combustion main chamber are formed in such a manner that the start-up of the gas turbine is effected by the hot combustion gas generated in the sub-chamber. The combustion sub-chamber is provided with an inner sleeve protruding from a side wall of the sub-chamber such that a tip of the inner sleeve is located in the vicinity of a downstream end of the sub-chamber, and a fuel nozzle is provided in a tip of the inner sleeve for increasing the fuel-to-air ratio during an initiating period of an increase in the gas turbine rotation speed.

Abstract: A gas turbine combustor comprising a head combustion chamber and a rear combustion chamber connected to a downstream side of the head combustion chamber, a first stage burner for premixing first stage fuel and air and supplying the resultant fuel and air premixture into the head combustion chamber to effect first stage premix combution, a second stage burner for premixing second stage fuel and air and the resultant fuel and air premixture into the rear combustion chamber to effect premix combustion in addition to the first stage premix combustion, and a device for regulating flow rates of combustion air to be premixed with first and second stage fuel. The combustor is further provided with a pilot burner in the head combustion chamber to form pilot flame and stabilize the first stage premix combustion.

Abstract: A gas turbine combustor including a first-stage combustion chamber being arranged to serve as a premix chamber for a second-stage combustion chamber and an auxiliary burner provided in the first-stage combustion chamber and arranged to effect, when fired, combustion and holding of a flame in the first-stage combustion chamber and to effect, when extinguished, feed a flame from the first-stage combustion chamber to the second-stage combustion chamber; and a method of driving the gas turbine combustor including a step of preparing the auxiliary burner in the first stage combustion chamber, the auxiliary burner being sparked when said combustion is fired, and causing the first-stage combustion camber to serve as the premixing chamber for the second-stage combustion chamber by extinguished the auxiliary burner.

Abstract: In a combustion air flow rate adjusting device in which a cylindrical regulating ring fitted about an outer peripheral surface of an inner cylinder of a gas turbine combustor is translated along the outer peripheral surface of the inner cylinder in order to vary an opening area of air intake ports formed in the peripheral wall of the inner cylinder, an arcuately moving part at a forward end of a lever fixedly connected to a forward end of a shaft extending inwardly through a peripheral wall of an outer cylinder of the gas turbine combustor is connected to a part reciprocating together with the regulating ring, by leaf springs.

Abstract: A combustor of two-stage combustion type in which fuel is supplied only from primary fuel nozzles for combustion only in primary combustion chamber under the operating condition where gas turbine load is low, and premixed mixture is supplied into a secondary combustion chamber provided on the downstream side of the primary combustion chamber for combustion in both the primary and secondary combustion chambers under the operating condition where the load is high. An air-bleed passageway opens on a downstream side of air holes for intaking secondary combustion air to be mixed with secondary fuel and communicates with the outside of the combustor. The air-bleed passageway is provided with a regulating valve and the secondary combustion air is bled at the minimum point of the load where the secondary fuel is supplied so that the fuel to air ratio of secondary premixed mixture may not be excessively lean, thereby reducing the production of non-burned components.

Abstract: A method of starting a gas turbine plant, which plant has at least one combustor including a primary combustion chamber into which primary fuel nozzles open and a secondary combustion chamber into which secondary fuel nozzles open, a compressor for supplying the combustor with compressed combustion air, and a gas turbine driven by the combustion gas generated in the combustor and adapted to drive a load such as an electric power generator. When the gas turbine is being accelerated to a rated speed or while the load is still below a normal load range, a fuel is supplied only to the primary fuel nozzle, whereas, in other loaded operation range, the fuel is supplied to both the primary and secondary fuel nozzles. Before the fuel supply to the secondary fuel nozzles is commenced, a part of the compressed air is bled through at least one air bleed pipe leading from the compressor and having an air bleed valve.

Abstract: A gas turbine combustor having a head combustion chamber and a rear combustion chamber, with a plurality of air supply ports arranged in a circumferential wall of the rear combustion chamber, and a fuel nozzle. An outer cylinder forms a cylindrical air flow passage between the inner cylinder and the outer cylinder. A cylindrical control member is provided which is adapted to be movable in an axial direction for regulating an opening of the air supply ports. The control member is supported by a supporting means which is adapted to maintain a gap between the control member and the wall of the rear combustion chamber. The supporting member includes a flexible member for absorbing a deformation of the control member during the axial movement of the control member so that it is possible to prevent, if not avoid, mechanical wear on the control member and to reduce the No.sub.x concentration as well as obtain a highly reliable operation of the gas turbine combustor.

Abstract: A stage structure of an axial turbine includes a stationary inner ring, a stationary outer wall, a row of stationary blades mounted on the stationary inner ring and outer wall, a row of moving blades, and a shroud ring mounted on the tips of the moving blades. An annular solid substance, disposed immediately downstream of an axial gap formed between an axial end of the shroud ring and surface of the outer wall axially facing the axial end of the shroud ring, reduces an expansion space provided immediately downstream of the axial gap, whereby circulation of an ejection flow from a main stream through the axial gap is reduced so that the turbine stage efficiency is improved. The annular solid substance may be a ring fixed to the stationary outer wall, a protrusion or a cylinder formed by a portion of the outer wall.

Abstract: A turbine blade of a low blade profile loss with a crossing point of an inlet angle .alpha..sub.1 an outlet angle .alpha..sub.2 being located in a position in which a distance between a crossing point of the outlet end of the blade is greater than one-half of the blade width L.sub.ax, with the inlet angle .alpha..sub.1 being in the range of 35.degree.-40.degree. and the outlet angle .alpha..sub.2 being in the range of 25.degree.-28.degree.. A ratio of a narrowest width S.sub.2 of the flow channel at the blade outlet end to a narrowest width S.sub.1 of a flow channel defined between a backside of the blade in an area of the crossing point and a front side of adjacent blade lies in the range of 0.81-0.96. A ratio of a distance L.sub.ax to a blade width L.sub.ax is in the range of 0.5-0.54, with a ratio of a distance L.sub.m from an outlet end of the blade to the blade width L.sub.ax being in a range of 0.75-0.89.

Abstract: A steam turbine rotor shaft made of precipitation-hardened forged austenite steel, comprising first, second and succeeding layers of build-up welding provided on an outer surface of a bearing portion of a journal section in the rotor shaft, the first layer being provided by use of a welding rod of Ni base alloy, the second and succeeding layers being provided by use of a welding rod of low alloy steel which layers have better bearing characteristics than those of the austenite steel.

Abstract: A steam turbine rotor shaft comprising the main body of the rotor shaft made of a high Cr steel of martensite structure, and a journal having a plurality of built-up welding layers formed successively said main body, the outer surface portion of the journal being made of steel containing 0.5 to 3 wt % of Cr, and a method of producing same.

Abstract: A rotor shaft for steam turbines has a journal portion to be supported by a bearing. The journal portion is provided with a sleeve for a bearing made of an alloy of bainite structure comprising 0.04 to 0.35% C, 0.2 to 2% Mn, less than 1% Si, 0.5 to 3% Cr, less than 5% Ni, and less than 0.5% V, having yield strength of more than 50 kg/mm.sup.2 and Lt of less than 24. The sleeve is divided into two semicylindrical segments, and they are arranged on a small diameter portion of the shaft adjacent to said journal portion, welded into one piece, and subjected to stress relief treatment at a temperature higher than a temperature of tempering conducted to the sleeve before welding. The welded sleeve is fitted on the journal portion by shrink-fit so that the sleeve can be served as a superior bearing.

Abstract: A method and apparatus for detecting the occurrence of rubbing in a rotary machine, in which at least one acoustic sensor is mounted on at least the rotor part or the stator part of the rotary machine, and the output signal from the acoustic sensor is detected and then filtered to extract a frequency component having a frequency substantially equal to the rotational frequency of the rotary machine, so as to detect the occurrence of rubbing in the rotary machine as early as possible and also to locate the source of the rubbing. Even when the occurrence of abnormal metal-to-metal contact at a bearing of the rotary machine is detected, it is discriminated from rubbing so that the occurrence of the rubbing can be reliably detected.

Abstract: A rotor shaft suitable for use as the rotor shaft of a steam turbine. The rotor shaft has a rotor shaft portion made of a Cr alloy steel having martensite structure and containing 8 to 13% Cr. The rotor shaft body is provided with at least one journal portion at which the rotor shaft is rotatably supported by a bearing. The rotor shaft further has a sleeve fitted around each journal portion. The sleeve is divided in the circumferential direction into a plurality of segments which are assembled together by welding or fitting into the sleeve having a circular cross-section. Due to the provision of the sleeve around the journal portion, the rotor shaft made of Cr alloy steel can have improved bearing properties.

Abstract: A device for connecting the turbine blades of a turbine having a plate-shaped member provided at the radially outer end of each turbine blade and extended substantially at a right angle to the longitudinal plane of the turbine blade. The plate-shaped member is projected from the leading and trailing edges of the turbine blade, and is provided with through bores formed in each projected portion. Connecting members having cylindrical pins or the like projections are disposed between two adjacent turbine blades in such a manner that the projections are rotatably received by respective through bores. Namely, one of the connecting members is connected to the plate-shaped member of the leading edge of the turbine blade while the other connecting member is connected to the plate-shaped member of the trailing edge of the preceding adjacent turbine blade.

Abstract: A moving blade for use in a steam turbine has a turbine rotor carrying a multiplicity of radially outwardly extending moving blades, each moving blade being provided at its leading edge of the radially outer end thereof with an anti-erosion plate attached by welding. The turbine blade has thicknesswise protrusions formed on both surfaces thereof at a portion near the base of the anti-erosion plate where it is attached to the moving blade. Thanks to these thicknesswise protrusions, the moving blade has such a radial distribution of cross-sectional area that the cross-sectional area is greater at the portion where the thicknesswise protrusions are formed than at other portions which are adjacent to the above-mentioned portion of the moving blade in the radial direction. As a result, the stresses at the portion of the moving blade near the base of the anti-erosion plate are reduced.

Abstract: A moving blade fastening construction comprising moving blade fingers formed in the moving blade root portion and rotor wheel fingers formed in the rotor wheel root portion and arranged so that the fingers of the moving blade are inserted in spaces defined between the fingers of the rotor wheel, thereby to provide at least two engaging portions radially spaced from each other. An average thickness of the moving blade finger is larger than that of the rotor wheel finger which is made of material larger in Young's modulus than the moving blade fingers, whereby stresses induced in the moving blade root portion are made uniform.

Abstract: A cross compound turbine apparatus and method of operating the same wherein the apparatus includes a first turbine generator having a high pressure turbine and a first low pressure turbine connected to a first generator driving shaft, with the second turbine generator having an intermediate pressure turbine connected to a second generator driving shaft. Driving steam is supplied to the high pressure turbine and a primary steam line communicates exhaust steam from the high pressure turbine to drive the intermediate pressure turbine during a steady state operation of the first and second turbine generator sections. A bypass steam line communicates steam from the system supplying driving steam to the high pressure turbine to the intermediate pressure turbine in a bypassing relationship to the high pressure turbine.

Abstract: A stress controlling system for a rotor of a steam turbine determines thermal and rotational conditions of the rotor. Thermal and centrifugal stresses produced in the rotor during operation of the steam turbine are calculated from the thermal and rotational conditions, respectively, of the rotor. Also, brittle fracture toughness of the material of the rotor under the thermal condition determined is calculated. Operation of the steam turbine is controlled to prevent the calculated brittle fracture toughness from being exceeded by the combined stress of thermal and centrifugal stresses during operation of the steam turbine.