Abstract: A coolant injection system for a nuclear power generation system includes the coolant injection system, and method of operation of the coolant injection system. The nuclear power generation system includes a reactor pressure vessel having a reactor core, a pressuriser in fluid communication with the reactor pressure vessel, and the injection system, which comprises a make-up tank having a tank inlet and a tank outlet. The injection system has an operating condition, and a fault response condition, and is configured to switch between these conditions when coolant level in the pressuriser drops below a threshold level. In the operating condition, the tank outlet is isolated from the reactor pressure vessel such that coolant is retained in the make-up tank, and the tank inlet is in fluid communication with the reactor pressure vessel and the pressuriser.

Abstract: A turbine power plant employs a radial staging of a liquid injection system to provide a uniform fluid distribution, for use in wet compression. The liquid injection system can be actuated to inject liquid to various radial regions of an air intake case of the turbine power plant. During a stage one actuation, liquid is directed to a first radial region of the air intake case. During a stage two actuation, liquid is directed to the first radial region and also to a second radial region of the air intake case.

Abstract: A mounting arrangement for locating a stator (10) within a casing (16) of a rotating machine comprises at least one mounting plate (12) adapted to engage with the stator (10) and the casing (16). The mounting plate (12) has a series of discrete apertures (20) therein. The apertures (20) extend through the plate (12) and are arranged in an array to provide a convoluted path which impedes the transmission of the dynamic forces through the plate (12) and into the casing (16). The apertures (20) render the plate (12) more resilient to the dynamic forces that the stator (10) experiences in operation. Each aperture (20) divides the plate (12) into portions which provide anisotropic stiffness in the radial and tangential directions.

Abstract: One embodiment is a gas turbine engine premix injector including a mixing duct, a plurality of air inlet slots leading to the duct, a plurality of gaseous fuel inlet apertures leading to the duct, a plurality of vanes positioned in the duct downstream from said air inlets, a plurality of liquid fuel inlet apertures leading to the duct, and a plurality of discharge windows positioned between the vanes.

Abstract: An apparatus and method for minimizing and/or preventing thermal degradation of fuel in a fuel injector is disclosed. The body of the injector includes a fuel gallery with a contoured scarf formed therein. The scarf is configured to minimize and/or prevent fuel recirculation thus reducing the likelihood that fuel will dwell in an area long enough to sufficient to cause the degradation of the fuel.

Abstract: A gas turbine engine is disclosed that has with two or more compressors. A first one of the compressors include a compressor variable geometry mechanism that may be in the form of adjustable vanes, bleed valves, or the like. A first one of the compressors is turned at a first speed and the second one of the compressors is turned at a second speed. The first speed is maintained approximately constant while the second speed varies and position of the compressor variable geometry mechanism is modulated in accordance with the second speed of the second one of the compressors to regulate surge margin for the first one of the compressors.

Abstract: One aspect relates to an apparatus having a combustion chamber and a duct in fluid flow communication with the combustion chamber. The apparatus includes at least one opening adapted for delivering a liquid fuel into the duct. The apparatus further includes at least one passage adapted for delivery of a gas upstream of the at least one opening for minimizing the entrance of a fluid other than the gas into the fuel delivery opening.

Abstract: One embodiment is a unique gas turbine engine combustion chamber including primary and secondary burning zones. Other embodiments include unique gas turbine engine apparatuses, systems, methods, and combinations.

Abstract: A technique is provided for operating a gas turbine engine that has a combustor with a primary stage and one or more other stages and a first compressor providing an air flow to the combustor. This technique includes driving a variable load device with the rotating shaft of the gas turbine engine and sensing pressure of the air flow and an engine speed. In response to a decrease in loading of the engine by the variable load device: selectively bleeding the air flow as a function of the engine speed and regulating temperature in the primary stage of the combustor as a function of a ratio between fuel flow provided to primary stage and the pressure to prevent engine flame out. In one form, the combustor is arranged as a dry load emissions type and the variable load device includes an electric power generator.

Abstract: An acoustic viscous damper for a compressor including a porous liner located within the discharge duct, the porous liner having a plurality of holes for passage of a purge working fluid therethrough into the discharge duct.

Abstract: The present invention provides an airfoil for a third stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract: The present invention provides an airfoil for a first stage turbine blade having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract: The present invention provides an airfoil a second stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract: The present invention provides an airfoil for a third stage blade having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract: The present invention provides an airfoil for a second stage turbine blade having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract: The present invention provides an airfoil for a first stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.

Abstract: A gas turbine engine system including a plurality of bleed off doors forming a portion of a conical surface in the flow path between the low pressure compressor and the intermediate pressure compressor. A plurality of actuators are coupled to a unison ring and move the unison ring in a substantially axial direction. The plurality of bleed off doors are coupled to the unison ring and move therewith.

Abstract: A turbine power plant employs a radial staging of a liquid injection system to provide a uniform fluid distribution, for use in wet compression. The liquid injection system includes a hub to be coupled to an air intake case of a turbine power plant. An annular ring assembly is spaced radially outwardly from the hub. Spray bars are spoked about the hub and the annular ring. The spray bars each include a body portion having an inner end coupled to the hub and an outer end coupled to the ring assembly. The spray bars each have at least two nozzle assemblies along the body portion. The spray bars each define at least two liquid supply manifolds each having an inlet at the annular ring assembly and an outlet at an associated nozzle assembly. The liquid supply manifolds each supply liquid to one or more associated nozzle assemblies.

Abstract: A generator transfer function regulator incorporating two control loops. The first control loop produces a first generator excitation control signal (U) which varies to compensate for variations in the magnitude of the generator output voltage (V.sub.1) . The second generator loop produces a second generator excitation control signal (U.sub.e) which varies so as to maintain substantially constant the response of the generator system to variations in the generator output. The two control signals are combined and applied to a conventional generator exciter circuit (2). As a result, the generator terminal voltage (V.sub.1) control performance achieved by the AVR under open circuit conditions is effectively maintained when the generator is loaded over its range of operation, irrespective of the power system which the generator feeds.

Abstract: An electrical machine has a rotor shaft (12) which carries a plurality of rotor discs (14) for rotation therewith. Each rotor disc (14) has pairs of rotor rims (16) secured thereto. Each rotor rim (16) consists of a single row of alternate magnets (20) and laminated pole pieces (18) and is opposed by a series of stator cores (22) which straddle the rotor rim (16). Armature windings (24) are disposed within the stator cores (22) for operably exciting said stator. The phase relationship between the currents through the armature windings (24) and the orientation of the stator cores (22) or the magnets (20) in opposing rims (16) are such that the effects of electromagnetic coupling, long path fluxes and torque ripple is reduced.