125results about How to "Improve gas efficiency" patented technology

A method of generating energy in a power plant (30) having a gas turbine (29), includes a first step a gas containing air (1) is compressed in a first compressor (2) of the gas turbine (29), a second step the compressed gas (3, 3a, 3b; 5; 7a, 7b) is fed to a combustion process with the addition of fuel (8) in a combustor (23), a third step the hot flue gas (9) from the combustor (23) is expanded in an expander or a turbine (10), driving a generator (18), of the gas turbine (29) while performing work, and a fourth step a partial flow of the expanded flue gas (11) is recirculated to the inlet of the first compressor (2) and admixed with the gas containing air (1). Carbon dioxide (CO2) is separated from the compressed gas (3, 3a, 3b; 5; 7a, 7b) in a CO2 separator (6) before the third step. In such a method, the overall size and energy costs are reduced by virtue of the fact that, to permit increased CO2 concentrations in the CO2 separator (6), not more than about 70% of the carbon dioxide contained in the compressed gas (3, 3a, 3b; 5, 5a, 5b; 7a, 7b) is removed from the compressed gas (3, 3a, 3b; 5, 5a, 5b; 7a, 7b).

The invention relates to a gas turbine blade or vane ring having a supporting structure and gas turbine blades or vanes secured to it. The gas turbine blades or vanes have a blade or vane root, which is successively adjoined by a platform and then a blade profile which is curved in the longitudinal direction, the blade or vane root running in the longitudinal direction of the blade profile, and the platform having two platform longitudinal edges which are bent parallel and run in the longitudinal direction. To provide an alternative gas turbine blade or vane ring with simplified assembly, it is proposed that the blade or vane root be shaped in such a manner that the suction-side or pressure-side blade or vane root surface of the associated platform longitudinal edge be curved convexly or concavely, respectively. Moreover, the invention relates to the use of a gas turbine blade or vane ring of this type.

An air bypass system for a gas turbine inlet filter house having a power augmentation system. The air bypass system may include a duct positioned on the inlet filter house about the power augmentation system and a damper positioned within the duct so as to open and close the duct.

A flexible diffuser membrane is provided with a unique system of perforations arranged to result in uniform distribution of gas even though the membrane deflects to different extents or the submergence varies in different parts of the membrane. The perforations are arranged to provide less perforation area per unit of perforated membrane surface area in the membrane parts that deflect the most or are submerged least and greater perforation area in membrane parts that deflect the least or are submerged most. The perforations can be slits arranged in parallel rows on a tubular membrane, in concentric circles or another pattern on a disk membrane, or in still a different pattern on a flat panel diffuser membrane. The slit length or separation can be varied between different zones on the membrane surface or the spacing between rows or circles can be varied.

An aeronautical propulsion system including a turbine engine having a fan and an electric motor drivingly coupled to at least one of the fan or the turbine engine. The aeronautical propulsion system additionally includes a fuel cell for providing electrical energy to the electric motor, the fuel cell generating water as a byproduct. The aeronautical portion system directs the water generated by the fuel cell to the turbine engine during operation to improve an efficiency of the aeronautical propulsion system.

A flexible diffuser membrane is provided with a unique system of perforations arranged to result in uniform distribution of gas even though the membrane deflects to different extents or the submergence varies in different parts of the membrane. The perforations are arranged to provide less perforation area per unit of perforated membrane surface area in the membrane parts that deflect the most or are submerged least and greater perforation area in membrane parts that deflect the least or are submerged most. The perforations can be slits arranged in parallel rows on a tubular membrane, in concentric circles or another pattern on a disk membrane, or in still a different pattern on a flat panel diffuser membrane. The slit length or separation can be varied between different zones on the membrane surface or the spacing between rows or circles can be varied.

A paintball gun kit preferably includes a plurality of non-fully assembled paintball gun components packaged for retail sale to a consumer. Instructions are preferably provided to instruct the consumer how to assemble the paintball gun components into an operational paintball gun. The paintball gun components can be packaged together or separately. The paintball gun kit can include, for example, a body, a grip, and a pneumatic assembly. Various numbers and arrangements of components are contemplated. Various styles, materials, and colors of paintball gun components can also be provided consistent with the principles of the present invention.

The aim of the invention is to increase the efficiency of a gas turbine system. Said aim is achieved by transferring at least one portion of the heat of the waste gases of a gas turbine to a working medium of a thermodynamic circulation process, which comprises at least two substances featuring non-isothermal evaporation and condensation. Said circulation process allows the residual heat of the waste gases to be used for additionally generating electrical or mechanical power, especially at waste gas temperatures ranging from 100 to 200° C. Even previously existing systems can be retrofitted in a simple manner with such a circulation process.

A system and method for cleaning sulfur and other pollutants from bunker oil to be used for fuel in large cargo ships is described. Preferably, the system includes two or more stages having a mixer to create an emulsion of oil and water. One or more treatment chemicals are added to the water before it is mixed with the oil in order to assist in separating the sulfur from the oil and freeing it up so that it can combine with various other molecules present in the water or be dissolved in the water. The emulsion may pass through a microcavitation chamber as well as an electrolysis reactor chamber in order to further clean the fuel oil by removing additional sulfur content. The clean fuel is sent to a fuel service tank for use in a diesel engine combustion cycle.

An air bypass system for a gas turbine inlet filter house having a power augmentation system. The air bypass system may include a duct positioned on the inlet filter house about the power augmentation system and a damper positioned within the duct so as to open and close the duct.

In a gas engine 1 that uses a gas having a lower specific gravity than air and has a pre-mixing device before a turbocharger, a pre-mixed gas mixture compressed by a turbocharger 3 is cooled by an intercooler 4 located downstream of the turbocharger 3 in the intake system. Condensed water produced as the gas is cooled and the pre-mixed gas mixture discharged with the condensed water are separated into condensed water, air, and fuel gas in a vapor-liquid separator 7. The fuel gas is returned to the intake system upstream of the turbocharger 3, while the condensed water is discharged to atmosphere.

The invention discloses an integral style gas, combustion catalyst and method for the making same, wherein the base material of the catalyst is integral ceramic honeycomb body or metallic honeycomb body, the catalyst coating layer coated on the base material surface comprises catalytic functional components and coating layer aiding agents, the catalytic functional components are classified into compound catalytic functional components having at least three different catalytic functions, each of which is prepared through corresponding predecessor physical process. The catalyst by the invention has high activity, high stability, high heat efficiency and low contaminant discharge.

A paintball gun kit preferably includes a plurality of non-fully assembled paintball gun components packaged for retail sale to a consumer. Instructions are preferably provided to instruct the consumer how to assemble the paintball gun components into an operational paintball gun. The paintball gun components can be packaged together or separately. The paintball gun kit can include, for example, a body, a grip, and a pneumatic assembly. Various numbers and arrangements of components are contemplated. Various styles, materials, and colors of paintball gun components can also be provided consistent with the principles of the present invention.

An airbag is formed by an outer panel member for constituting the bag having a front side and a rear side with an opening for receiving gas to be inflated. The airbag includes at least three compartments arranged inside the bag including a first compartment communicating with the opening, a second compartment situated adjacent to the first compartment, and a third compartment situated adjacent to the second compartment. The gas flows from the first compartment to the third compartment through the second compartment.

A control system in a gas engine includes a water injection means which injects water toward an interior of a cylinder in the gas engine; a water injection control means which controls the water injection section; and a knocking occurrence ratio measuring means which measures a measurement value of a knocking occurrence ratio in the cylinder. The water injection control means controls the water injection means to set the amount of the water injected toward the interior of the cylinder, based on a deviation between the measurement value and a target value.

A gas cooking appliance includes a combination radiant / convection cooking system mounted below a bottom wall portion of an oven cavity. The combination cooking system includes a gas burner in the form of a ring element having a central portion within which is positioned a convection fan. In addition to the convection fan, a forced air combustion fan supplies a combustion airflow to the gas burner. The oven preferably includes a glass panel arranged in a bottom wall portion of the oven cavity, above the gas burner. Arranged about the central opening are a plurality of vented openings for introducing the convective airflow into the oven cavity. The glass panel provides both a conductive heat surface transmitting at least a portion of the radiate heat energy into the oven cavity and a viewing surface allowing a consumer to view the operation of the gas burner.

An airfoil having cooling passages inside is provided, wherein each radial cross section of the airfoil has a shape of specific profile, wherein hot gas flows along the airfoil's surface from a leading edge to trailing edge, the airfoil's surface comprises a pressure-side and suction-side defined by the trailing edge and leading edge, wherein the trailing edge has cooling fluid discharge exits, the pressure-side and suction-side are respectively defined by a wall comprising an inner surface and an outer surface, which inner surface has ribs extending in a rib-direction inclined to the radial direction, wherein along a portion of at least 10% of the profile's lengths the inclined ribs contact each other at respective cross-contact-points, forming a 2-dimensional matrix. At least one additional blocking-rib extends from the pressure-side to the suction-side and extends from one cross-contact-point to another to cause additional turbulence of said cooling fluid flow to be discharged.

An airbag is formed by an outer panel member for constituting the bag having a front side and a rear side with an opening for receiving gas to be inflated. The airbag includes at least three compartments arranged inside the bag including a first compartment communicating with the opening, a second compartment situated adjacent to the first compartment, and a third compartment situated adjacent to the second compartment. The gas flows from the first compartment to the third compartment through the second compartment.

The invention relates to a gas turbine (3) with reheat in the turbine section (11), whereby a fuel injection device (37) is provided for the injection of fuel (33) in to a combustion air flow (61) in the direction of flow before a cooling air flow (65) branching. By means of the early mixing of fuel (63) in the combustion air flow (61) and concomitant additional use of the cooling air flow (65) as combustion air, the specific output and the efficiency of the gas turbine (3) are improved.

The object of the present invention is to provide a turbine moving blade that has high heat resistance and can be used for a long period of time by improving the cooling efficiency of the turbine moving blade, and to improve both the thermal efficiency and operating efficiency of a gas turbine through the use of this turbine moving blade. In order to achieve the object, the present invention provide a turbine moving blade arranged in a combustion gas flow path in which a plurality of blow-out openings for blowing out a cooling medium are formed in its outer surface, wherein among a plurality of cooling medium trailing edge blow-out openings arranged from the vicinity of a blade base to the vicinity of a blade tip along a blade trailing edge of turbine moving blade, the opening area of a blade tip trailing edge blow-out opening located in the vicinity of blade tip is set to be larger than the opening area of the other trailing edge blow-out openings.

A gas turbine includes a cooling-air transfer system. The cooing-air transfer system extracts part of air discharged from a compressor to a chamber, and transfers the part of air as cooling air to a rotor disk. The cooling-air transfer system includes a plurality of tubular nozzles independently arranged in a circle inside the chamber to surround a rotor, and a seal disk having seal-disk cooling conduits arranged in a circle around the axis of the rotor so as to receive cooling air ejected from the tubular nozzles. The cooling-air transfer system swirls the cooling air ejected from the tubular nozzles.

A turbine power generation system, comprising a stator including a shroud and a rotor rotatably situated within the shroud, wherein the shroud is structured such that the inner diameter of the inner surface of the shroud reduces when the inner surface is exposed to a thermal load. The reduction of the inner diameter allows a minimum blade-casing clearance to be achieved during steady-state operation instead of during transient operations. Blade-casing clearance is configured to be greatest at when the engine is in a cold, stationary position. The clearance is further configured to decrease as thermal load increases until a steady-state, thermal equilibrium is achieved. The clearance grows during shutdown as the stator and rotor begin to cool.

A fuel injection system is provided for a gas turbine, comprising a mains airblast fuel injector having an annular shape, and inner and outer mains swirlers for swirling air past the mains airblast fuel injector. The inner and outer mains swirlers are concentric with the mains airblast fuel injector and are located radially inwardly and radially outwardly of the mains airblast fuel injector, respectively. The mains airblast fuel injector and the inner and outer mains swirlers are so arranged as to produce a fuel spray stream which expands from the mains airblast fuel injector and has a double flame front. The double flame front comprises flame fronts on both the radially inner and radially outer surfaces of the fuel spray stream.

An aeronautical propulsion system including a turbine engine having a fan and an electric motor drivingly coupled to at least one of the fan or the turbine engine. The aeronautical propulsion system additionally includes a fuel cell for providing electrical energy to the electric motor, the fuel cell generating water as a byproduct. The aeronautical portion system directs the water generated by the fuel cell to the turbine engine during operation to improve an efficiency of the aeronautical propulsion system.

A method and system for optimizing the efficiency of an LNG liquification system of the gas expansion type, wherein an incoming feed gas is first separated in a fractionation column by counter current contact with a cold reflux fluid, and a gaseous stream introduced into the heat exchanger system at a reduced temperature such that an intermediate pinch point is created in the warm composite curve.

A tube seal is fitted with a spherical spring, being an elastic member, at one end of a tubular barrel. The end where the spring is fitted to the tubular barrel is inserted into a steam supply pipe outlet, which is a coolant passage provided in a rotor disk. The other end of the barrel is formed into a spherical shape, and this end is inserted into a steam supply port in a dynamic blade, being another coolant passage port, and abuts against the internal surface of the steam supply port.

A paintball gun having a rearwardly removable pneumatic assembly is provided. The pneumatic assembly preferably comprises a bolt and a bolt housing. A pneumatic cylinder is preferably arranged within a body of the paintball gun to receive the pneumatic assembly. A rearward opening is preferably provided in the body to provide access to the pneumatic cylinder for positioning and removal of the pneumatic assembly. The pneumatic assembly can be configured for removal with or without tools. In one embodiment, a cover plate can also be provided to cover the rearward opening in the body and prevent access to the pneumatic assembly until the cover plate is removed. A solenoid valve assembly is also provided having an upper and lower body section connected together through a tab and detent structure.