244results about How to "Increase pressure ratio" patented technology

In a combined steam and gas turbine engine cycle, a combustion chamber is made durable against high pressure and enlarged in length to increase the operation pressure ratio, without exceeding the heat durability temperature of the system while increasing the fuel combustion gas mass flow four times as much as the conventional turbine system and simultaneously for greatly raising the thermal efficiency of the system and specific power of the combined steam and gas turbine engine.Water pipes and steam pipes are arranged inside the combustion chamber so that the combustion chamber can function as a heat exchanger and thereby convert most of the combustion thermal energy into super-critical steam energy for driving a steam turbine and subsequently raising the operation pressure ratio and the thermal efficiencies of the steam turbine cycle and gas turbine cycle. The combustion gas mass flow can be also increased by four times as much as the conventional turbine system (up to the theoretical air to fuel ratio) and the thermal efficiency and the specific power of the gas turbine cycle are considerably increased.Further, the thermal efficiency of the combined system is improved by installing a magnetic friction power transmission system to transmit the power of the system to outer loads.

A method and apparatus for boosting the performance of gas turbine engines, pipelines, and other applications using gas turbine engine systems. A pressurizing device or other source is preferably used to deliver an intake air stream to the gas turbine engine at at least 2% above atmospheric pressure. The pressurizing device of other source is preferably not mechanically driven by the gas turbine engine itself.

A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a transpiration member. The transpiration member is at least partially surrounded by a pressure containment member. The combustion chamber has opposed inlet and outlet portions. The inlet portion of the combustion chamber is configured to receive the fuel mixture for the fuel mixture to be combusted at a combustion temperature. The combustion chamber is further configured to direct the resulting combustion product toward the outlet portion. The transpiration member directs a transpiration substance therethrough toward the combustion chamber for buffering interaction between the combustion product and the transpiration member. Associated systems, apparatuses, and methods are also provided.

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO₂ circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO₂ circulating fluid. Fuel derived CO₂ can be captured and delivered at pipeline pressure. Other impurities can be captured.

A method and apparatus for renewable power generation utilizes the chemical potential dissimilarity between solutions of differing ionic formulations. A train is formed by a sequentially ordered set of a plurality of cells in which each successive cell is related to the preceding cell. Each cell has pumping means and hydro-power generation turbine means to form a closed hydraulic loop configured for specified volumetric and flow capacity. Adjacent cells share semipermeable membranes. Each cell is charged with a brine of specified ionizable inorganic salt quantity and type with the brine being cycled in a controlled concentration-pressure loop, with each of the cells operating at progressively increasing concentration and osmotic pressure ratio. A continuous and constant flow rate of substantially salt-free permeate flux is maintained across each cell, the flux being osmotically induced from low salt concentration water being fed at the first cell in the train and exiting at the last cell along with the discarded high concentration water brine. The salt-free permeate flux is continuously induced, in symbiotic mode, through the shared membranes, driven by the chemical influence of concentration potential field bounded by water of low to no salt concentration on one end of the train and by brine of high salt concentration on the other end of the train with sufficient concentration difference to provide driving force for said plurality of cells, while maintaining adequate concentration difference between adjacent cells to enhance osmosis function, as well as defining a concentration ratio within each cell to ensure a net positive power generation.

A system for providing air from a multi-stage to a turbine includes a turbine having a high pressure input port and a low pressure input port. The system also includes a compressor having at least one high pressure extraction air output and at least one low pressure extraction air output. A valve is fluidly connected to the at least one high pressure extraction air output, at least one low pressure extraction air output and low pressure input port of the turbine. The valve is selectively operated to fluidly connect the at least one low pressure extraction air output with the low pressure input port during normal operating conditions and fluidly connect the at least one high pressure extraction air output and the low pressure input port during a turn down condition or below design temperature operation to enhance turbine engine performance.

[Object]

An object of the invention is to provide a fan rotating blade for a turbofan engine capable of increasing a bypass ratio by increasing an intake air flow rate without enlarging a diameter of a fan and an inner diameter of a casing and of realizing a decrease in weight of an engine as well as a decrease in fuel consumption and noise.

[Means for Solving the Problems]

A leading edge part 11 of a fan rotating blade 10 for taking air thereinto is provided with a vertical hub portion 12 positioned on the hub side so as to be substantially perpendicular to a fan rotary shaft, a backward mid-span portion 13 inclined toward the downstream side from the hub side to the mid-span portion, and a forward inclined tip portion 14 inclined toward the upstream side from the mid-span side to the tip portion.

A turbocharger, having an axial compressor wheel and an axial turbine wheel mounted on a first shaft supported by a housing, and a radial compressor wheel and a radial turbine wheel mounted on a second shaft, the second shaft concentrically extending around the first shaft and being supported by the housing. The housing defines a first duct extending axially from the exducer of the axial compressor to the inducer of the radial compressor, and a second duct extending axially from the exducer of the radial turbine to the inducer of the axial turbine. A plurality of controllable compressor guide vanes extend through the first duct, and a plurality of controllable turbine stator vanes extend through the second duct. The housing is provided with variable diffuser vanes at the exducer of the radial compressor, and with variable turbine vanes at the inducer of the radial turbine. The variable turbine vanes and the turbine stator vanes are controlled to accurately control the rotation rate of the radial and axial turbines. The compressor guide vanes are controlled to minimize surge and maximize choke flow rate.

An internal combustion engine/water source system for a vehicle powered by a internal combustion engine wherein liquid water is produced by cooling a portion of engine exhaust gases in a vortex tube to induce condensation. In one embodiment, engine exhaust gases are pumped into the vortex tube by a compressor. After removing a portion of water vapor, cooled exhaust gases may be re-introduced to engine's combustion chamber thereby providing an exhaust gas recirculation. In an automotive vehicle, liquid water generated by the invention may be collected and provided to an electrolytic cell for electrolysis into gaseous hydrogen to reduce exhaust pollutants during cold engine start. Alternatively, water generated by the invention may be injected into engine combustion chamber to increase power and to reduce production of nitrogen oxides.

A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a porous perimetric transpiration member, at least partially surrounded by a pressure containment member. The combustion chamber has longitudinally spaced apart inlet and outlet portions. The fuel mixture is received by the inlet portion for combustion within the combustion chamber at a combustion temperature to form a combustion product. The combustion chamber directs the combustion product longitudinally toward the outlet portion. The transpiration member is configured to substantially uniformly direct a transpiration substance therethrough toward the combustion chamber, such that the transpiration substance is directed to flow helically about the perimeter and longitudinally between the inlet and outlet portions, for buffering interaction between the combustion product and the transpiration member. Associated systems are also provided.

A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a porous perimetric transpiration member, at least partially surrounded by a pressure containment member. The combustion chamber has longitudinally spaced apart inlet and outlet portions. The fuel mixture is received by the inlet portion for combustion within the combustion chamber at a combustion temperature to form a combustion product. The combustion chamber further directs the combustion product longitudinally toward the outlet portion. The porous transpiration member is configured to substantially uniformly direct a transpiration substance laterally therethrough, about the perimeter thereof defining the combustion chamber and longitudinally between the inlet and outlet portions, toward the combustion chamber for buffering interaction between the combustion product and the porous transpiration member. Associated systems are also provided.

A method of designing rotors for a Roots blower comprising a housing having cylindrical chambers, the housing defining an outlet port (19). The blower includes meshed, lobed rotors (37,39) disposed in the chambers, each rotor including a plurality N of lobes (47,49), each lobe having first (47a,49a) and second (47b,49b) axially facing end surfaces. Each lobe has its axially facing surfaces defining a twist angle (TA), and each lobe defines a helix angle (HA). The method of designing the rotor comprises determining a maximum ideal twist angle (TA_M) for the lobe as a function of the number N of lobes on the rotor, and then determining a helix angle (HA) for each lobe as a function of the maximum ideal twist angle (TA_M) and an axial length (L) between the end surfaces of the lobe.

The invention relates to a sweeping and twisting type three-dimensional blade diffuser. According to the structure, the front edges of blades are designed into a sweeping shape, the sweeping angle ranges from -45 degrees to 45 degrees, and the blades are suitable for incoming flow and are twisted to be expanded into different air flow angles. The main blade is designed into a three-dimensional integral structure from an inlet to an outlet in the axial direction. The flow-dividing blades are arranged on the rear section in a main blade channel. The sweeping and twisting type three-dimensional blade diffuser has the advantages that interaction of shock waves and a boundary layer is relieved, so that flow in the diffuser is modified; blade surface air flow separation and load loss which are caused by a relative large positive/negative attack angle in part of the blades in the high portion are eliminated, flow loss is reduced, and therefore a stator part diffuser of a centrifugal/oblique flow gas compressor can reach the higher efficiency and the larger pressure ratio. The strength of the shock waves is changed and the shock waves are even eliminated and influence caused by interaction of the shock waves and the boundary layer is relieved; flow loss caused by the overlarge positive attack angle or the overlarge negative attack angle is avoided, the expansion capacity and the operation range of the diffuser are improved, and therefore the improvement in the performance of the whole-level gas compressor is assisted.

A bypass conduit (23) connects an outlet passage of a compressor (21) of an exhaust gas turbocharger (20) and an inlet passage of an exhaust turbine (22), and a bypass valve (24) is provided therein. When the operating condition of a diesel engine (1) is found to be in a low-speed and high-load region, the bypass valve (24) is controlled by means of a valve controller to adjust the bypass conduit (23) so as to open it. Then, the charge air partly flows into an exhaust conduit (4) to increase the rotational speed of the exhaust turbine (22) and hence the charge air flow rate raises the output of the diesel engine (1). Additionally, as the charge air flow rate is increased, the operating condition of a compressor (21) is prevented from approaching the surging range.

The present invention provides a gas turbine rotor having a first axial compression stage for compressing air in a first direction and a second axial compression stage for compressing the air in a second direction, the second direction being generally opposite the first direction.

A high thermal efficiency reciprocating hydrogen-fueled engine for ultra-high altitude long endurance flight and its method of operation are described. The engine is based on an opposed piston barrel design where long cylinders are employed to accommodate extraordinarily large compression and expansion strokes where the corresponding ratios are over 50:1, taking advantage of the very low ambient air pressures and temperatures at 60,000 ft and higher to reduce the overall weight and strength requirements of the inventive engine that would be a factor for operation at lower altitudes. The engine is designed to obtain more than 70% indicated thermal efficiency when operated at ultra-high altitudes of 60,000 ft and greater. A combination of large compression ratios combustion temperature optimization and management, instantaneous and complete combustion at TDC, followed by a rapid and long expansion stroke using tailored control of piston movement provide the means to achieve such high efficiencies.