Abstract: A gas turbine combustor (26) disposed in a combustion air plenum (65) and a transition piece (28) for the combustor disposed in a separate cooling air plenum (58, 67). The combustion air plenum may receive combustion air (50) from a high-pressure compressor stage (22A). The cooling air plenum may receive cooling air (52) from an intermediate-pressure compressor stage (22B) at lower temperature and pressure than the combustion air. This cools the transition piece using less air than prior systems, thus making the gas turbine engine (20) more efficient and less expensive, because less expensive materials are needed and/or higher combustion temperatures are allowed. The cooling air may exit the cooling air plenum through holes (62) in a downstream portion (61) of the transition piece. An outer wall (72) on the transition piece may provide forced convection along the transition piece.

Abstract: A strut cover for use in a gas turbine engine having structure defining an annular flow path for receiving exhaust gas from a turbine section of the engine. The strut cover is located downstream from a last row of blades of the turbine section and extends radially through the flow path between inner and outer walls. The strut cover includes an upstream section and a downstream section. The upstream section defines a leading edge for the strut cover and is supported on a pivot axis for pivotal movement about the pivot axis. The downstream section defines a trailing edge for the strut cover and includes an upstream end positioned adjacent to a downstream end of the upstream section. The downstream section is stationary relative to the inner and outer walls to define a predetermined flow angle for directing exhaust gases flowing from the upstream section and passing through the diffuser.

Abstract: A turbine blade includes an airfoil, a blade tip section, a squealer tip rail, and a plurality of chordally spaced fence members. The blade tip section includes a blade tip floor located at an end of the airfoil distal from the root. The blade tip floor includes a pressure side and a suction side joined together at chordally spaced apart leading and trailing edges of the airfoil. The squealer tip rail extends radially outwardly from the blade tip floor adjacent to the suction side and extends from a first location adjacent to the airfoil trailing edge to a second location adjacent to the airfoil leading edge. The fence members are located between the airfoil leading and trailing edges and extend radially outwardly from the blade tip floor and axially from the squealer tip rail toward the pressure side.

Abstract: A combustion turbine includes a compressor section, a combustion section downstream from the compressor section, and a turbine section downstream from the combustion section. A diffuser section is downstream from the turbine section and has an outer wall, an inner wall, and at least one strut member extending therebetween. The outer wall has at least one first gas passageway therein, the inner wall has at least one second gas passageway therein, and the at least one strut member has at least one third gas passageway therein. The at least one first, second and third gas passageways deliver gas therethrough to assist attachment of a boundary layer to adjacent surfaces of the outer wall, the inner wall, and the at least one strut, respectively.

Abstract: A turbine blade includes an airfoil, a blade tip section, a squealer tip rail, and a plurality of chordally spaced fence members. The blade tip section includes a blade tip floor located at an end of the airfoil distal from the root. The blade tip floor includes a pressure side and a suction side joined together at chordally spaced apart leading and trailing edges of the airfoil. The squealer tip rail extends radially outwardly from the blade tip floor adjacent to the suction side and extends from a first location adjacent to the airfoil trailing edge to a second location adjacent to the airfoil leading edge. The fence members are located between the airfoil leading and trailing edges and extend radially outwardly from the blade tip floor and axially from the squealer tip rail toward the pressure side.

Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.

Abstract: A seal assembly limits gas leakage from a hot gas path to one or more disc cavities in a gas turbine engine. The seal assembly includes a seal apparatus associated with a blade structure including a row of airfoils. The seal apparatus includes an annular inner shroud associated with adjacent stationary components, a wing member, and a first wing flange. The wing member extends axially from the blade structure toward the annular inner shroud. The first wing flange extends radially outwardly from the wing member toward the annular inner shroud. A plurality of regions including one or more recirculation zones are defined between the blade structure and the annular inner shroud that recirculate working gas therein back toward the hot gas path.

Abstract: There is disclosed an electronic gaming system (100) comprising one or more player interfaces (6, 7, 17), and a main video display screen (1). The system enables players to simultaneously play a plurality of reel-type games and to place bets on lines of the games. The system displays a plurality of display windows on the main display screen, each window being associated with a respective one of the simultaneously played games and displaying the reels of that game, each reel displaying reel indicia. The system is configured for any one of the games to enter a feature phase when a feature-triggering event occurs. At the start of the feature phase, all the display windows on the main screen, except the particular display window associated with the feature phase, reduce in size or disappear, while the size of the feature game's display window increases, and the other games are also suspended, until the feature phase is completed.

Abstract: Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.

Abstract: There is disclosed an electronic gaming system (100) comprising one or more player interfaces (6, 7, 17), and a main video display screen (1). The system enables players to simultaneously play a plurality of reel-type games and to place bets on lines of the games. The system displays a plurality of display windows on the main display screen, each window being associated with a respective one of the simultaneously played games and displaying the reels of that game, each reel displaying reel indicia. The system is configured for any one of the games to enter a feature phase when a feature-triggering event occurs. At the start of the feature phase, all the display windows on the main screen, except the particular display window associated with the feature phase, reduce in size or disappear, while the size of the feature game's display window increases, and the other games are also suspended, until the feature phase is completed.

Abstract: A gas turbine engine (34) including a compressor (36) for producing compressed air, a first stage of combustion (24) in the compressed air producing combustion gas, an expansion turbine (61) expanding the combustion gas to produce work and an exhaust gas (14), a second stage of combustion (26) in the combustion gas disposed downstream of a first stage of expansion in the turbine (61), and a third stage of combustion (28) in the combustion gas disposed downstream of the second stage (26) of combustion. None of the stages of combustion produce a temperature in the combustion gas of more than about 1,400° C.

Abstract: Aspects of the invention relate to a system and method for operating a turbine engine assembly. The turbine engine assembly has a turbine engine having a compressor section, a combustor section and a turbine section. The combustor section has a lower T_PZ limit and the turbine engine has a design load. The assembly further includes at least one air bleed line from the compressor and at least one valve for controlling air flow through the bleed line. Control structure is provided for opening the valve to allow bleed air to flow through the bleed line when an operating load is less than the design load. The flow rate through the bleed line is increased as the operating load is decreased, reducing the power delivered by the turbine assembly while maintaining the T_PZ above a lower T_PZ limit. A method for operating a turbine engine assembly is also disclosed.

Abstract: A combined cycle power plant (10) that is optimized to reduce total life cycle cost rather than only thermal efficiency. A steam bottoming cycle (16) is fed with exhaust gas (14) from a gas turbine topping cycle (12). The topping cycle incorporates multiple stages of combustion in order to maintain a desired high temperature of the exhaust gas being delivered to the bottoming cycle while at the same time avoiding peak combustion temperatures that would produce undesirable levels of NOx emissions. Accordingly, no post-combustion exhaust gas treatment is needed. In one embodiment, an aspirated compressor (36) provides compressed air to a torus-configured combustion chamber (20) that is integrated with a first stage of vanes (22), and a plurality of stages of in-situ reheat combustion (26, 28) are utilized. In other embodiments, torus-configured combustion chambers may be utilized for more than one of the stages of combustion.

Abstract: A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.

Abstract: The present invention relates to the selection of a set of polymorphism markers for use in genome wide association studies based on linkage disequilibrium mapping. In particular, the invention relates to the fields of pharmacogenomics, diagnostics, patient therapy and the use of genetic haplotype information to predict an individual's susceptibility to SCHIZOPHRENIA disease and/or their response to a particular drug or drugs.

Abstract: A transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine has an internal passage from an inlet to an outlet that is offset from the inlet in the longitudinal, radial and tangential directions. The offset outlet and the curved internal passage discharge the gas flow toward the first stage blade array at an angle in the tangential direction relative to the longitudinal direction. This angled discharge can be presented directly to the blades, thus avoiding the need for first stage vanes and the associated costs and complexity.

Abstract: The present invention relates to the selection of a set of polymorphism markers for use in genome wide association studies based on linkage disequilibrium mapping. In particular, the invention relates to the fields of pharmacogenomics, diagnostics, patient therapy and the use of genetic haplotype information to predict an individual's susceptibility to ADHD disease and/or their response to a particular drug or drugs.

Abstract: The present invention relates to the selection of a set of polymorphism markers for use in genome wide association studies based on linkage disequilibrium mapping. In particular, the invention relates to the fields of pharmacogenomics, diagnostics, patient therapy and the use of genetic haplotype information to predict an individual's susceptibility to psoriasis disease and/or their response to a particular drug or drugs.

Abstract: The present invention relates to the ATG16l1 gene and genetic variants associated with Crohn's disease. In particular, the invention relates to the fields of pharmacogenomics, diagnostics, patient therapy and the use of genetic haplotype information to predict an individual's susceptibility to Crohn's disease and/or their response to a particular drug or drugs.

Abstract: The present invention relates to the selection of a set of polymorphism markers for use in genome wide association studies based on linkage disequilibrium mapping. In particular, the invention relates to the fields of pharmacogenomics, diagnostics, patient therapy and the use of genetic haplotype information to predict an individual's susceptibility to Crohn's disease and/or their response to a particular drug or drugs.