701 results about "Turbomachinery" patented technology

A system includes a turbine housing, a turbine mount disposed in the turbine housing, and a turbine moving machine disposed at least partially within the turbine housing. The turbine moving machine includes a turbine support configured to couple to a turbine and a first translational portion coupled to the turbine support. The turbine moving machine is configured to move the turbine lengthwise along the first translational portion between a first turbine position within the turbine housing and a second turbine position outside of the turbine housing. The turbine moving machine includes a vertical adjustment assembly configured to raise and lower the turbine.

A protective wind energy conversion chamber provides a protected multiple turbine mechanism axially aligned to convert kinetic energy of a moving fluid (e.g., wind) into rotational mechanical power by the reaction of the moving fluid with the turbine. The conversion chamber may either be configured as a vertical axis wind turbine (VAWT) or horizontal axis wind turbine (HAWT). The conversion chamber repositions an intake windward to collect and concentrate the wind prior to converting the wind into energy via the axially aligned multi-turbine mechanism. The remaining wind is released via a leeward-facing exhaust. Completely enclosed by the protective wind energy conversion chamber, the axially aligned multi-turbine mechanism avoids interference by birds and other outside objects.

A power generation system includes a first compressor, a second compressor, a combustor configured to receive compressed air from the second compressor to produce an exhaust stream, a first turbine, and a power turbine. The first turbine is configured to receive the exhaust stream, generate a rotational power from the exhaust stream, output the rotational power to a second compressor, and output the exhaust stream. The system includes a coupling device configured to couple and decouple the first compressor to / from a second turbine, an electrical generator coupled to an output of the power turbine and configured to output electrical power, and a controller configured to cause the coupling device to mechanically decouple the second turbine from the first compressor, and cause the coupling device to direct compressed air from an air storage cavern to an inlet of the second compressor.

A method and apparatus are disclosed that allow Conformal Vortex Generator art to improve energy efficiency and control capabilities at many points in a turbomachine or device processing aero / hydrodynamic Newtonian fluid-flows.

A compliant seal for use between rotating blades and a static shroud surrounding the rotating blades in a steam or gas turbine is disclosed. The seal includes a tip surface, substantially resistant to wear due to rubbing by the tip of the rotating blades, and an elastic biasing member, comprising a biasing element. The wear-resistant surface is thus biased against the tips of the rotating blades to seal a gas path between the rotating blades and the static shroud.

A gas turbine engine includes a turbomachinery core operable to generate a flow of pressurized combustion gases at a variable flow rate, while maintaining a substantially constant core pressure ratio; a rotating fan disposed upstream of the core, the fan adapted to extract energy from the core and generate a first flow of air which is compressed at a first pressure ratio; and at least a first bypass duct surrounding the core downstream of the fan adapted to selectively receive at least a first selected portion of the first flow which is compressed at a second pressure ratio lower than the first pressure ratio, and to bypass the first selected portion around the core, thereby varying a bypass ratio of the engine. The fan is adapted to maintain a flow rate of the first flow substantially constant, independent of the bypass ratio.

Electrodynamic control of fluid leakage loss is provided. Embodiments utilize electrohydrodynamic (EHD) principles to control and / or reduce leakage flow in turbomachinery. Electrodes can be used to provide a flow actuation mechanism inside the clearance gap for generating discharge. The electrodes can be positioned to have geometric asymmetry. Embodiments provide the electrodes on a turbine blade. The blade can have a DC power that can function as a square pulsed DC wave with the duty cycle equal to the blade passing frequency and the stator can be grounded. In an embodiment, the stator can have the actuator of the electrode-insulator assembly attached to the inside. In one embodiment, the actuators can be arranged just on the stator or casing. The phase and power supply to individual electrodes can be adapted as needed. In one embodiment, the phase can be lagged for accurate control of leakage flow. The control of the power supply to the electrodes can involve a closed control loop that monitors tip gap size.

A nonlinearly stacked low noise turbofan stator vane having a characteristic curve that is characterized by a nonlinear sweep and a nonlinear lean is provided. The stator is in an axial fan or compressor turbomachinery stage that is comprised of a collection of vanes whose highly three-dimensional shape is selected to reduce rotor-stator and rotor-strut interaction noise while maintaining the aerodynamic and mechanical performance of the vane. The nonlinearly stacked low noise turbofan stator vane reduces noise associated with the fan stage of turbomachinery to improve environmental compatibility

A method is provided of reducing lockout time of a gas turbine engine which includes: an inlet, a compressor, a combustor, a turbine, and an exhaust duct, where the compressor and the turbine are carried on a turbomachinery rotor and each include an array of blades mounted for rotation inside a casing of the engine. The method includes: operating the engine at a first power output; shutting down operation of the engine without substantially reducing the power output beforehand, wherein thermomechanical changes occur in the engine subsequent to shutdown that tend to reduce a radial clearance between at least one of the blades and the casing; and subsequent to shutting down the engine, (1) heating the casing and / or (2) pumping an airflow of ambient air into the inlet and through the casing, past the rotor, and out the exhaust duct, so as to reverse at least partially the thermomechanical changes.

Supersonic Magnetic Advanced Generation Jet Electric Turbine (S-MAGJET) described herein, and a subsonic derivative, MAGJET, integrate a gas power turbine, superconducting electric power and propulsion generation, and magnetic power flux field systems along with an ion plasma annular injection combustor which utilizes alternative petroleum-based fuel and combustion cycles to create a hybrid turbine turbomachine for aerospace propulsion. The propulsion unit is able to achieve a dramatic increase in horsepower, combustion and propulsion efficiency, and weight reduction. In addition, the turbomachinery structures may be disposed within an exo-skeleton architecture that achieves an increase in thrust to weight ratio with a concomitant increase in fuel efficiency and power generation over traditional gas turbine technology today. The engine continuously adjusts the temperature, pressure and mass airflow requirements using an electromagnetic power management system architecture. Engine performance may be controlled across the entire desired flight envelope, whether subsonic, transonic or supersonic flight conditions.

A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.

The invention discloses a low-noise design method of a centrifugal pump with low specific speed, and relates to an active control method of flow noise of turbomachinery. The design method comprises the steps that firstly, main structural dimensions of a centrifugal pump impeller and a helical pumping chamber (volute) are obtained by the traditional low-specific-speed pump design method; secondly, an internal flow field of the pump is computed by a computational fluid mechanics method; the performance of the pump is predicted whether to meet a design requirement; an optimum design improvement is performed by analyzing a stationary flow field; thirdly, flow induction noise of the pump with low specific speed is predicted by a computational acoustics method; if a flow noise index is qualified, the design is accomplished; if the flow noise index is disqualified, subsequent steps are performed; fourthly, the diameter of the impeller basically meeting a performance requirement in the design is adjusted to allow a gap between the impeller and a volute tongue to be increased continuously to 20%; splitter blades are added in the middles of blades to increase the lift, control the flow situation, and ensure the efficiency; and finally, the pump subjected to the impeller improvement design is subjected to noise prediction; if the flow noise index is qualified, the design is accomplished; and if the flow noise index is disqualified, the beginning step is repeated. The design method shortens the research and development period, saves the development cost, effectively improves the design quality of the centrifugal pump, can simultaneously meet low-noise requirements of the lift and the efficiency, and realizes optimization of the performance of the complete centrifugal pump with low specific speed.

A gas turbine engine includes a turbomachinery core operable to generate a flow of pressurized combustion gases at a variable flow rate, while maintaining a substantially constant core pressure ratio; a rotating fan disposed upstream of the core, the fan adapted to extract energy from the core and generate a first flow of air which is compressed at a first pressure ratio; and at least a first bypass duct surrounding the core downstream of the fan adapted to selectively receive at least a first selected portion of the first flow which is compressed at a second pressure ratio lower than the first pressure ratio, and to bypass the first selected portion around the core, thereby varying a bypass ratio of the engine. The fan is adapted to maintain a flow rate of the first flow substantially constant, independent of the bypass ratio.