Abstract: A dual fuel nozzle is provided with two different size injection holes. The first injection holes have larger diameters and are used only for injecting gaseous fuel into a combustion chamber. On the other hand, the second injection nozzles have smaller diameters and are used for injecting either gaseous fuel or liquid fuel as required. When gaseous fuel is used, if the fuel injection amount is large or medium, both of the first and the second injection holes or first injection holes only are used for injecting gaseous fuel depending upon the required fuel injection amount. When the fuel injection amount is low, only the second injection hole is used for injecting gaseous fuel. Therefore, the pressure drop across the fuel nozzle can be kept at sufficiently high level even when the fuel injection amount is low, and thereby combustion vibration is suppressed. Further, when liquid fuel is used, a premixed fuel and steam mixture is injected from the second injection holes.

Abstract: A combustor includes a burner and a combustion chamber including a heat chamber to which fuel is supplied from the burner. The burner includes a nozzle having a fuel discharge outlet from which the fuel is discharged into the combustion chamber; and the nozzle includes a plurality of discharge openings around the fuel discharge outlet from which cooling water is discharged toward inside surfaces of the heat chamber. The plurality of discharge openings may be disposed so that the directions of the cooling water discharged from the discharge openings differ in the radial direction.

Abstract: A hardware synthesis method for synthesizing a hardwired circuit from a behavioral description written in a language including execution control branch instructions such as an if-goto statement and a switch statement is provided. More specifically, hardware is synthesized by converting a behavioral description including an execution control branch instruction into a control flow graph (CFG) using a branch node and a merge node, converting the CFG into a control data flow graph (CDFG), performing scheduling according to the CDFG, and executing allocation according to the result of the scheduling.

Abstract: This invention relates to a fuel discharge member which can reduce the amount of NOx exhaust. The fuel discharge member is fixed on a fuel supply conduit, and comprises: a main body having an internal space which communicates with a fuel passage in the fuel supply conduit, fuel discharge outlets which communicate with the internal space, and a trailing edge. The thickness of the trailing edge is no more than 5 mm, or a flow passage block ratio of the fuel discharge member is no more than 10% with respect to the cross-sectional area of the air flow passage in which the fuel discharge member is to be placed. Alternatively, the main body is a flat tube.

Abstract: In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

Abstract: To present a gas turbine combustor capable of improving the fuel distribution from the main fuel nozzle, suppressing fluctuations of internal pressure and elevation of inner tube metal temperature, and enhancing the combustion stability and durability of the combustor.

Abstract: A nozzle cap (10) is disposed downstream of a nozzle body (1) of a combustor for a gas turbine, an inner surface part (12) of which is of a conical shape diverging downstream to define a fuel-jet guide (17) for guiding fuel jet ejected from one or more nozzle holes (3) provided at the center of a downstream end surface of the nozzle body. Fuel ejected from the one or more nozzle holes smoothly runs along the fuel-jet guide without remaining there to join with a swirl stream (S) in a swirl path (9), and to burn without generating smoke. Air introduced into a first auxiliary air path (6) defined between the nozzle body and a partition (5) at a position upstream thereof passes through a second auxiliary air path (16) defined between a downstream end surface (2) of the nozzle body (1) and an upstream end surface (13) of the nozzle cap and reaches an entrance (19) of the fuel-jet guide.

Abstract: In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

Abstract: In a central portion of inner tube 28 of combustor 20, pilot fuel nozzle 22 and pilot cone 33 are arranged and main fuel nozzles 21 and main swirlers 32 therearound. Air intake portion (X-1) is provided with rectifier tube 11 for making air intake uniform. In air intake portion (X-2), air holes of appropriate number of pieces are provided in circumferential wall of the inner tube 28. In main swirler portion (X-3) and pilot cone portion (X-4), bolt joint of the main swirlers 32 is employed and optimized welded structure having less influence of thermal stress of the pilot swirler 33 is employed, respectively. Tail tube cooling portion (X-5) is provided with cooling structure having less influence of thermal stress to cool flange 71 portion of tail tube 24 uniformly. By the improvements in the portions (X-1) to (X-5), obstacles in attaining higher temperature in the combustor 20 is dissolved and combustor performance is enhanced.

Abstract: Cooling structure of gas turbine combustor in which cooling medium flows through grooves in wall is improved so that adjustment of flow velocity, pressure loss and heat transfer rate of cooling medium flow in the wall becomes possible and cooling effect thereof is enhanced. Wall of combustor tail tube is made in double structure in which outer plate (1) and inner plate (4) are jointed together being lapped one on another. The outer plate (1) has air inlet hole (3) and groove (2) formed therein. The groove (2) is closed by jointing of the inner plate (4) to the outer plate (1). The inner plate (4) has air outlet hole (5) formed therein. The groove (2) communicates with the air inlet hole (3) and the air outlet hole (5). Cross sectional shape of the groove (2) is changed two-dimensionally or three-dimensionally such that width enlarges toward the hole (5) from the hole (3) or depth is constant or changed in tapered form.

Abstract: A high-level synthesis method comprising the steps of converting an operating description describing one or more operations to a control data flow graph (CDFG) including one or more nodes representing the one or more operations and one or more I/O branches representing a flow of data, scheduling the CDFG obtained by the converting step, and allocating one or more logic circuits required for executing the CDFG obtained by the scheduling step. A portion of the CDFG in the converting step is subjected to logical synthesis in advance to generate a node, and the portion of the CDFG is replaced with that node.

Abstract: A circuit synthesis method includes the steps of converting a behavioral description describing a behavior of calculation processing into a control data flowgraph; assigning at least one calculation, at least one input and at least one output in the control data flowgraph into prescribed time slots; assigning the at least one calculation, a plurality of data dependency edges, the at least one input and the at least one output respectively to at least one calculation device, at least one register, at least one input pin and at least one output pin; generating a plurality of paths corresponding to the plurality of data dependency edges; and detecting a first false path among the plurality of paths.

Abstract: A combustor includes a pilot fuel nozzle and a plurality of main premixing nozzles arranged therearound for forming a premixture of air and fuel supplied from a main fuel nozzle, and is improved so as not to cause vibratory combustion. Pilot fuel nozzle unit 104 comprises a plurality of pilot fuel nozzles 103. A plurality of main premixing nozzles 102 are disposed on a coaxial circumference of the pilot fuel nozzle unit 104. The pilot fuel nozzles 103 are arranged irregularly in a circumferential direction of the pilot fuel nozzle unit 104, so as to form portion 105 where there is no pilot fuel nozzle 103. Premature in the main premixing nozzles 102 positioned corresponding to the pilot fuel nozzle 103 burns with comparatively short flames. Premature in the main premixing nozzles 102 positioned corresponding to the portion 105 of no pilot fuel nozzle 103 burns with long flames because of flames spreading from adjacent main fuel nozzles.

Abstract: Liquid fuel purge device uses water, not compressed air as in the prior art, thereby prevented are rapid load change of gas turbine due to sudden discharge of liquid fuel and coking of remaining liquid fuel. Upon supply of liquid fuel to fuel nozzle (05) being stopped, water purge system (15) having stop valve (16) supplies water into fuel system including liquid fuel system (08) and fuel nozzle (05) and liquid fuel remaining therein is purged by water into combustion chamber (013) from the fuel nozzle (05).

Abstract: To prepare a more homogeneous premixture than that of the device of the prior art thereby to suppress an NOx emission and to lower a fuel feed pressure. A gas turbine combustor comprising: an outer cylinder 106 having main swirlers 101 therein and adapted to be fed with air; and an annular fuel feed manifold 110 disposed at the outer circumference of the outer cylinder 106 on the upstream or downstream side of the main swirlers 101 and having a plurality of nozzle ports 111 communicating with the inside of the outer cylinder 106, so that a fuel is injected from the outer circumference to the center of the air flowing in the outer cylinder 106.

Abstract: A combustor has a pilot nozzle 02 arranged at a central portion of an inner cylinder 01 opening at its end into a combustion chamber 018 and includes a plurality of main nozzles 03 arranged around its outer circumference. Along the outer circumference of a flame holding cone 014 for igniting a fuel F injected from the main nozzles 03 there are disposed elliptical extension pipes 016 of an elliptical sectional shape which are extended from the fronts of the main nozzles 03 to have openings at the axial position of the opening of the flame holding cone 014. As a result, a hot premixed flame 013 does not flow back to a main swirler zone 015 of the circumferential edges of the openings of the main nozzles 03 so that mixing between the fuel F and an air flow A can be improved, reducing the Nox emission while eliminating the burning of a base plate 04 and the main nozzles 03.

Abstract: New 2-oxo-1-azetidine sulfonic acid derivatives with an aminoalkyl substituted "anti" (E-isomer) oxyimino group in the acylamino substituent at the 3 position of the monobactam ring. These compounds are potent inhibitors of bacterial .beta.-lactamases. These compounds can be used in combination with .beta.-lactam antibiotics to increase the effectiveness of the .beta.-lactam antibiotics in fighting infection caused by .beta.-lactamase producing bacteria.

Abstract: In a gas turbine combustor of the present invention, a pilot fuel nozzle is composed of at least two systems with different hole diameters, and the fuel flow rate of each system can be controlled independently. Also, even if the operation of main burners is switched in accordance with high or low load, the pilot fuel is selected accordingly. Further, the pilot fuel differential pressure is kept high to effect stable supply of fuel, and stable combustion is maintained.

Abstract: A compound of formula (I) ##STR1## wherein R.sub.1 is selected from the group consisting of 2-thienyl, 2-furyl, 2-pyrrolyl, 1-methyl-2-pyrrolyl, 2-amino-1-thiazolyl and 5-isothiazolyl;R.sub.2 is selected from the group consisting of: ##STR2## and M is hydrogen or a pharmaceutically acceptable cation; wherein the oxyimino fragment (.dbd.N--OR.sub.2) in formula (I) is in the `anti` orientation.

Abstract: A cache memory operates in a first mode, in which a cache hit occurs, and in a second mode, in which a cache miss occurs. A data processor operates in a first state in which instructions are accessed from memory and in a second state in which data is accessed from memory. Cache memory has a condition setting circuit which distinguishes instruction caching from a data caching. The processor sends an access-type signal which is compared with the access-type set in the condition setting circuit. When the access-type signal does not coincide with the contents of the condition setting circuit, a third state is declared which links the main memory and cache memory.