493 results about "Leakage flow" patented technology

A stepped labyrinth seal for a turbomachine, the seal having a stepped portion with a redirecting groove formed thereon to redirect a leakage flow through the gap in substantially a reverse direction and onto a surface of the finger such that the dynamic pressure of the leakage flow is not substantially reduced and the static pressure increased. The cavity formed between adjacent fingers has a flow guiding surface that maintains the dynamic pressure of the flow, thereby keeping the flow at high velocity and low static pressure.

A heart assist device comprising a rotary pump housing having a cylindrical bore, a pumping chamber and a motor stator including an electrically conductive coil located within the housing and surrounding a portion of the cylindrical bore. A rotor has a cylindrical shaft, at least one impeller appended to one end of the shaft, and a plurality of magnets located within the shaft. The rotor shaft is positioned within the housing bore with the magnets opposite the motor stator, and the impeller is positioned within the pumping chamber. The housing bore is closely fitted to the outer surface of the shaft forming a hydrodynamic journal bearing, with the pumping chamber and journal bearing connected by a leak path of blood flow between the pumping chamber and the journal bearing. A backiron of the motor stator attracts the rotor magnets to resist longitudinal displacement of the rotor within the housing during operation. The relative orientation of positions of the inflow, outflow, and leakage flow paths may be varied within the pump, such as to accommodate different intended methods for implantation and/or use.

A fan system, such as a turbofan, marine propeller, or a cooling fan, includes a fan noise control system for reducing noise generated by the fan system. The noise control system may be configured to reduce either broadband noise, blade-passage noise, or both. In particular, the fan noise control system suitably includes a pre-swirl generator configured to provide a layer of fluid upstream from the fan blades. The layer swirls in the direction of the fan's rotation, reducing the angular velocity differential between the fan blades and the incident fluid. In addition, the fan noise control system may also include a fluid seal generator configured to create a fluid barrier between the fan blade tips and the interior surface of the fluid flow channel. The fluid seal inhibits leakage flow between the fan blade tips and the interior surface as well as the formation of blade vortices. By minimizing the blade wake and the blade tip vortices without adding solid surfaces, noise tends to diminish.

A method and system for detecting and estimating leaks in an industrial boiler whereby the method and system formulate the leak detection problem as a least squares fitting problem, where one or more of the fitted parameters estimate leak flows. The method and system create a representation that incorporates a leak model component, a process model component and a noise model component into the representation. This invention provides a variety of leak flow estimates and associated significance tests that have a much higher statistical efficiency and are sensitive to leaks with a wider range of leak growth rates than prior approaches.

A fuel nozzle 110 having a plurality of swirl vane 130 on an outer peripheral surface thereof is installed within a burner tube 120, with a clearance 121 being provided. Each swirl vane 130 progressively curves from an upstream side toward a downstream side (inclines along a circumferential direction) in order to swirl compressed air A flowing through an air passage 111 to form a swirl air flow a. Here, curvature of each swirl vane 130 is greater on its outer peripheral side than on its inner peripheral side. By suppressing occurrence of an air streamline heading from the inner peripheral side toward the outer peripheral side, therefore, flow velocity on the inner peripheral side and flow velocity on the outer peripheral side become equal, thus preventing flashback on the inner peripheral side. Moreover, a swirl imparting force in the circumferential direction per unit length on the inner peripheral side and that on the outer peripheral side become equal, equalizing the fuel concentration on the inner peripheral side and the fuel concentration on the outer peripheral side. Furthermore, a leakage flow, which passes from the vane dorsal surface side through the clearance 121 and leaks to the vane ventral surface side, generates a vortex air flow, promoting mixing of fuel and air.

A fluid control device for use in a high pressure fluid system, the device including a device body with a cavity and a high pressure circuit, a plunger positioned for reciprocal movement in the cavity, and a leakage reduction cap mounted to the plunger for reducing fluid leakage flow. In one implementation, the leakage reduction cap includes a flexible portion positioned between the device body and the plunger, and defining an annular clearance gap between the leakage reduction cap and the device body. The flexible portion of the leakage reduction cap resiliently flexes radially outwardly in response to fluid pressure forces to reduce the annular clearance gap so as to minimize fluid leakage flow through the annular clearance gap.

Disclosed is a seal for turbomachinery including a seal face locatable between a first turbomachinery component and a second turbomachinery component. At least one fluid channel extends through the seal. The at least one fluid channel is capable of injecting fluid flow between the first turbomachinery component and the second turbomachinery component at the seal face thereby disrupting a leakage flow between the first turbomachinery component and the second turbomachinery component. Further disclosed is a turbomachine utilizing the seal.

A dechuck control method includes performing a discharge process by introducing an inert gas into a processing chamber and maintaining the pressure within the processing chamber at a first pressure; monitoring the pressure of a heat transmitting gas supplied to the processing object rear face and/or the leakage flow rate of the heat transmitting gas; obtaining the amount and polarity of the residual electric charge of the electrostatic chuck surface and applying a voltage for supplying an electric charge that is of the same amount as the residual electric charge but of the opposite polarity to a chuck electrode; evacuating the inert gas from the processing chamber while applying the voltage to the chuck electrode and reducing the pressure within the processing chamber to a second pressure; and turning off the voltage applied to the electrostatic chuck and dechucking the processing object from the electrostatic chuck.

A shaft seal serves to reduce leakage between a rotating shaft and a static shell. The shaft seal includes a plurality of compliant plate members, each having a root and a tip. The compliant plate members are secured to one of the static shell and the rotating shaft at their root in facing relation. The tips of the compliant plate members define a sealing ring between the static shell and the rotating shaft. An axial flow resistance member is disposed within the compliant plate members and serves as a harrier to axial leakage flow between the compliant plate members.

Arcuate seal layers conforming with one another are disposed between inner retainer segments and inner rails of nozzle segments of a gas turbine. The layers are secured to the aft axial face of the segments and project radially outwardly to seal against the forward axial faces of the rails. The rear axial faces of the rails have chordal seals for sealing against the forward axial faces of the support rings. The seal layers have radial cuts misaligned with one another in an axial direction to preclude leakage flows through gaps formed by the cuts. Arcuate spacers are staggered circumferentially with the arcuate retainer segments whereby an intermediate pressure plenum is formed between the finger seals and chordal seals.

A seal for stemming leakage flows between adjacent components (9, 20), especially of a gas turbine, has an elastically deformable, thin-walled sealing element (1) and a thin-walled cover element (13) which is U-shaped in cross section and between its legs (15) and its base (14) partially accommodates the sealing element (1). The legs (15) of the cover element (13) are arranged in the sealing arrangement, which features the seal, between two oppositely disposed walls (28) of the other component (9) in a movable manner relative to these walls (28) which, together with the sealing surface (8) of the other component (9), form a groove (27) which is U-shaped in cross section. Forces, which act laterally upon the seal, are absorbed by the cover element (13) and via the legs (15) are diverted into the other component (9) so that the integrity of the seal is maintained even in the case of lateral forces.

A shaft seal serves to reduce leakage between a rotating shaft and a static shell. The shaft seal includes a plurality of compliant plate members, each having a root and a tip. The compliant plate members are secured to the static shell at their root in facing relation. The tips of the compliant plate members define a sealing ring between the static shell and the rotating shaft. An axial flow resistance member is disposed within the compliant plate members and serves as a barrier to axial leakage flow between the compliant plate members.

Provided is a turbine blade cascade endwall that is capable of suppressing a vortex generated on a suction surface of a turbine stator blade and that is capable of reducing secondary-flow loss due to this vortex. A turbine blade cascade endwall that is positioned on a tip side of a plurality of turbine stator blades arranged in a ring form is provided with a pressure gradient alleviating part that alleviates a pressure gradient generated in the blade height direction at a suction surface of the turbine stator blades due to a clearance leakage flow, leaking out of a gap between a tip of a turbine rotor blade located on the upstream side of the turbine stator blades and a tip endwall disposed facing the tip of this turbine rotor blade.

A stepped labyrinth seal having a plurality of teeth forming gaps between a stationary honeycomb member, where the cavities formed between adjacent teeth include a plurality of vortex flow generating strips on the wall of the cavity that redirect the leakage flow from a gap back toward the gap and in a direction toward the gap in order to limit the leakage flow through the gap. The vortex generating strips extend along the cavity floor and up the sides of the teeth forming the cavity. The strips slope downward from the downstream tooth toward the upstream tooth in the direction of rotation, and with a curvature in the direction of rotation. The stepped labyrinth seal is intended for use in a gas turbine engine having a plurality of stages in the turbine, with the labyrinth seal being used to seal the gap between rotating blades and the honeycomb surface on the stationary casing.

A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.

The invention relates to a fuel injector for injecting fuel into a combustion chamber, having a solenoid valve for controlling a mini-servo valve. A movable armature can be placed in a sealing fashion on a valve seat in a lower armature chamber, wherein in addition the mini-servo valve is held in an injector body and seals a control line against a flat seat. By means of the flat seat, during an actuation of the solenoid valve, the control line can be relieved of pressure from a high fuel pressure to a return pressure into at least one return line. A mechanism for reducing pressure oscillations are provided in the at least one return line, which includes at least one diaphragm cell which is held in a recess and which is placed in fluidic connection with the at least one return bore. A fuel injector with the mechanism for reducing pressure oscillations is therefore created in the at least one return line which operates without a leakage flow and has a simple and effective function.

A human-machine synchronization method and device of an invasive ventilator operating in a noninvasive ventilation mode. The method includes steps of: measuring an airway pressure, an inspiratory flow, and an expiratory flow; calculating a gas leakage flow according to a pre-established gas leakage estimation model and by using the airway pressure, the inspiratory flow and the expiratory flow; and compensating a basic flow according to the gas leakage flow. In the above method, the gas leakage flow is estimated by means of the gas leakage estimation model, to compensate the gas leakage, thereby facilitating the noninvasive ventilation of the invasive ventilator and improving the human-machine synchronization.

Durable pumps for abrasives are provided. An example centrifugal pump stage for subsurface operation has a thrust washer located inside the circumference of an outboard clearance seal between an impeller shroud and the diffuser. Relocation of the thrust washer allows the clearance seal to protect the thrust washer from abrasives. A centrifugal action of an outboard seal lip effects a separation of the particles from the fluid nearest the gap of the outboard seal and drives the particles away from the gap of the outboard seal. When an abrasive particle in the leakage flow does clear the outboard seal, the particle is readily flushed across the thrust washer by the leakage flow to the central fluid inlet to prevent wear of the thrust washer. In an implementation, the inside diameter of the thrust washer is approximately flush with the bore of a central fluid inlet of the pump stage.

The invention relates to a device comprising gratings, which are used to form a reverse flow from a jet engine thrust flow. The inventive device comprises a plurality of flow diverter gratings which are disposed side-by-side at the outer edge of an annular thrust flow circulation channel. Each of the gratings comprises a plurality of intersecting inner transverse blades and inner longitudinal blades, two adjacent gratings being separated by a side clearance which generates a leakage flow. The device also comprises means of re-directing the aforementioned leakage flow in a direction such as to increase the effectiveness of the reverse flow, said re-direction means comprising aerodynamic appendages which are mounted to at least one outer longitudinal edge of each grating.

This progressing cavity pump including a helical rotor (2) mounted to turn inside a helical stator (3), said stator (3) and said rotor (2) being disposed such that the cavities (4) formed between said rotor (2) and said stator (3) move from the inlet (5) towards the outlet (6), is characterized by the fact that hydraulic regulation (HR) means are provided for obtaining internal recirculation of the pumped fluid between at least two of said cavities (4) under conditions capable of performing at least one function selected from: achieving the desired pressure distribution along the pump, stabilizing the temperatures, controlling the leakage flow rates, and compensating for the volumes of compressed gas.

A method for monitoring a fuel supply system for a turbine engine, the fuel supply system comprising a fuel pump and a pressure regulation valve configured to receive fuel from an outlet of the fuel pump includes determining by a bypass monitor an amount of bypass flow in a bypass path located between the pressure regulation valve and an inlet of the fuel pump; determining an amount of leakage flow in the fuel supply system by the bypass monitor based on the bypass flow; and determining whether the leakage flow exceeds a predetermined threshold by the bypass monitor, and in the event the leakage flow exceeds the predetermined threshold, indicating a need for maintenance of the fuel supply system.

A sealing system is applied to the interface between a stator and a rotor in a turbine engine to minimize fluid leakage across the interface. One interface can be defined between portions of neighboring rotor disks and a stator. The sealing system includes one or more rows of flow guides, such as airfoils, provided on the rotor disk near the upstream end of the interface. These flow guides can impart tangential velocity on the leakage flow. One or more undulating seal structures can be connected to the stator downstream of the flow guides. These undulating seals can have a periodic waveform conformation. The undulating seals can create unsteadiness in the flow and recirculation of the leakage flow, which causes losses. The sealing system can also include other types of seals, such as labyrinth seals and brush seals, to further create a tortuous path for any leakage flow.