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).

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 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.

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.

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.