Abstract: A mixture of hydrocarbons in vapour phase is passed through a feed scrubber. Feed scrubber vapour discharged from the feed scrubber is passed to a compression suction scrubber, and a vaporous compressor feed stream from the compression suction scrubber is compressed in a compressor train. A compressed vaporous discharge stream from the train of compressors is de-superheated, and at least a portion of the de-superheated stream is passed to a condenser, wherein this portion of the de-superheated stream is at least partly condensed to form a pressurized and at least partially condensed mixture of hydrocarbons. A recycle portion is split off from the de-superheated hydrocarbon stream, and a recycle flow is established to the compressor train of via a surge recycle separator drum and the compression suction scrubber. Liquid constituents removed and drained from the recycle portion in the surge recycle separator drum are fed to the feed scrubber.

Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.

Abstract: The present disclosure is directed to a clamping apparatus for securing a main bearing of a wind turbine. The clamping apparatus includes a clamp member configured for securement to a seal ring arranged with the main bearing, at least one clamping fastener configured through the clamp member, and at least one jacking fastener configured through the clamp member. Thus, the clamping fastener is configured to tighten the clamp member around the seal ring, whereas the jacking fastener is configured to push against the main bearing when tightened so as to maintain the main bearing in place during and installation and/or repair procedure.

Abstract: A steam turbine include a steam chest casing that is provided with a plurality of nozzle openings along a circumferential direction; a partition wall to partition the steam chest casing into the main steam chest and a sub-steam chest with smaller capacity than the main steam chest; a main steam pipe that supplies steam to the main steam chest; a steam chest connection pipe that distributes part of the steam, which is supplied to the main steam chest, to the sub-steam chest; a steam chest connection valve; a pressure gauge that measures the pressure of the steam flowing in the main steam pipe; and a control unit that closes the steam chest connection valve when the measured pressure is less than more than or equal to a predetermined threshold value, and opens the steam chest connection valve when the measured pressure is less than the predetermined threshold value.

Abstract: A compressor control system includes: a compressor; an inlet guide vane (IGV) arranged at an inlet of the compressor, and configured to adjust opening of the inlet based on a supplementary surge control signal or a performance control signal; an anti-surge valve (ASV) connected to an outlet of the compressor, and configured to prevent a surge based on a surge control signal; and a controller configured to generate the surge control signal for controlling the ASV when an operating point enters a surge control range, generate the supplementary surge control signal for controlling the IGV in an anti-surge mode when the operating point enters a supplementary surge control range set between the surge control range and a surge range, and generate the performance control signal for controlling the IGV in a performance mode until the operating point enters the surge control range.

Abstract: Methods and apparatus are disclosed for detecting and preventing compressor surge. A transmitter determines a derivative process value of a compressor. A controller obtains the derivative process value from the transmitter. The transmitter is separate from the controller. The controller compares the derivative process value to a threshold value. The threshold value is indicative of the initiation of a surge event in the compressor. In response to determining that the derivative process value fails to satisfy the threshold value, the controller actuates a valve operatively coupled to the compressor to enable an additional derivative process value of the compressor determined by the transmitter to satisfy the threshold value.

Abstract: An object is to provide a structure and a method of joining a nozzle vane and a lever, and a variable geometry turbocharger, capable of reducing breakage of a welded part between a shaft portion of the nozzle vane and the lever during usage of the same by reducing generation of a hot crack in weld metal at the welded part. A joint structure includes: a nozzle vane 2 disposed in an exhaust passage for guiding exhaust gas to a turbine wheel 34 of a variable geometry turbocharger 500, and including a shaft portion 2a; and a lever 1 including a fitting surface 42a fitted with a peripheral surface 72 on one end side of the shaft portion, for transmitting torque to the shaft portion to adjust a vane angle of the nozzle vane. Weld metal 50 at a welded part 40 between the lever and the nozzle vane is formed so that a center position 64 of the weld metal is disposed inside a position 17 of the fitting surface with respect to a radial direction of the shaft portion.

Abstract: The invention relates to a run-in coating (10) for an outer air seal of a turbomachine, especially of an aero engine, comprising a substrate (12) of segmented form which carries a honeycomb structure (14) with an run-in surface (15) to face rotor blades of a rotor of the turbomachine, wherein a radial thickness of the honeycomb structure (14) varies in the circumferential direction. The invention furthermore relates to an outer air seal for a turbomachine and also to a turbomachine with an outer air seal.

Abstract: The compressor system comprises a compressor having first compressor stage and a second compressor stage in a back-to-back arrangement. A first gas flow is provided at the suction side of the compressor. A seal arrangement is provided between the first compressor stage and the second compressor stage. A side stream line is in fluid communication with the suction side of the second compressor stage. A side stream valve on the side stream line and a side stream controller are provided, for adjusting the flow of the second gas. An antisurge arrangement comprised of a bypass line and an antisurge valve is arranged at the first compressor stage for preventing surge of the first compressor stage. The side stream controller is configured for reducing the flow of the second gas when an alteration of the pressure ratio across the first compress stag is detected.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and at least one rib that protrudes from the wall and extends to a rib end, the rib end having a curved transition portion near a location where the at least one rib meets the wall.

Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, a bleed duct configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet, and a delta-pressure valve located at each bleed port of the two or more bleed ports configured to move between an opened position and a closed position in response to a difference between a first pressure upstream of the delta-pressure valve and a second pressure downstream of the delta pressure valve. The bleed airflow is selectably conveyed through a bleed port of the two or more bleed ports depending on the operation of the associated delta-pressure valve.

Abstract: A turbine engine includes two rotary shafts and a lubrication unit. The lubrication unit has at least one pump which a casing inside of which a rotor is mounted and driven by one of the rotary shafts. The pump casing is rotated by the other rotary shaft such that the actuation of the pump depends on the difference between rotational speeds of the shafts. The shafts are a drive shaft and a fan shaft, respectively, wherein the fan shaft is driven by the drive shaft by means of a reduction gear which is lubricated by the lubrication unit. The reduction gear is annular and the pump passes axially therethrough.

Abstract: The present disclosure relates to a compressor control system that detects the pressure (or flow rate) at the rear end of a compressor and performs proportional control in mechanical manner to uniformly control the pressure (or flow rate) of the compressor while preventing a compressor suction valve from being fully closed. To this end, the present disclosure includes a cylinder including a first piston and a second piston therein, a pressure control valve which supplies fluid to operate the second piston to an area above the second piston, a control valve which supplies fluid to operate the first piston to an area above the first piston, and supplies fluid to the pressure control valve, a fluid condition transmission unit which detects fluid condition (pressure or flow rate) at a rear end of a compressor, and converts the detected fluid condition value to an electrical signal and outputs it.

Abstract: A wind turbine includes a hub configured to rotate about an axis at a first rotation speed and at least one blade coupled to the hub. The wind turbine also includes a sensor assembly configured to detect at least one characteristic of wind flowing through the wind turbine. The sensor assembly is mounted to the hub. The sensor assembly includes a laser device configured to emit a laser beam and at least one optical element configured to direct the laser beam. The sensor assembly also includes a non-motorized mechanism configured to rotate the at least one optical element at a second rotation speed when the hub rotates at the first rotation speed. The second rotation speed is greater than the first rotation speed.

Abstract: The present disclosure describes a load/unload control method for a compressor system with a rotating compressor connected to a pressure vessel. In the method, the present operating state can be monitored on the basis of a monitored/estimated electrical quantity of the compressor system. The method comprises an identification phase and an operational phase. In the identification phase, the compressor is operated at a constant rotational speed to generate two known pressures to the pressure vessel. At least one electrical quantity is monitored, and values of the electrical quantity corresponding to the pressure limits are stored. In the operational phase, reaching of a pressure limit may then be detected by comparing the present value of the monitored electrical quantity to the stored values.

Abstract: A turbine casing includes: a shroud of a cylindrical shape defining an operational flow path between the shroud and a hub of a turbine rotor; a scroll outer peripheral wall continuing from an end side of the shroud and extending along a circumferential direction of the shroud; and a partition wall disposed inside the scroll outer peripheral wall and dividing an inside of the scroll outer peripheral wall into a first scroll flow path and a second scroll flow path disposed adjacent to each other in an axial direction of the shroud. The shroud, the scroll outer peripheral wall, and the partition wall are formed integrally by casting. The partition wall has a widening section which partially increases a communication area between at least two of the first scroll flow path, the second scroll flow path, and the operational flow path, in the circumferential direction of the shroud.

Abstract: A turbine control unit and method for controlling a turbine, in particular for controlling the start-up of a turbine, the unit being designed as a cascade controller having a master controller and an inner controller, the master controller being a thermal stress controller for the components subjected to thermal stress.

Abstract: An automation system that determines the theoretical maximum rate of cooling of a steam turbine and operates a steam generator in such a way that the thermal energy of the steam does not exceed nor drop below the predefined rate of cooling.

Abstract: A wind turbine blade device includes a rotating unit including a blade module concentrically connected to a rotating shaft thereof and having a plurality of radially curved channels each having inlet and outlet ends. The inlet and outlet ends of the radially curved channels are configured to respectively permit flow of the flow body into and out thereof. An outer tube includes a tube body surrounding the rotating unit, and a plurality of rib plates provided in the tube body. The outlet end of each radially curved channel corresponds to one of the rib plates, and each radially curved channel forms an included angle with a corresponding rib plate such that the flow body flowing out of the outlet end can impact upon the corresponding rib plate.

Abstract: A centrifugal fan includes a frame and an impeller. The impeller is disposed within the frame. The impeller includes a hub, a first blade group and a second blade group. The hub includes a center part, an inclined part and a connection part. The first blade group is connected with the connection part of the hub. The second blade group is disposed on the inclined part of the hub. There is a first distance between the second blade group and the first blade group. There is a second distance between the second blade group and the center part of the hub.

Abstract: A cooling-air supply device for a gas turbine, in particular an aircraft gas turbine, including a cooling air chamber, that is disposed about a turbine shaft of the gas turbine, at least one cooling-air inlet opening, and at least one cooling-air outlet orifice; the cooling-air supply device having a first and a second axial bounding wall, and a peripheral wall that joins the two axial bounding walls, which, together, form the cooling air chamber; in at least one of the axial bounding walls, a plurality of cooling-air outlet orifices being provided, which are circumferentially distributed about the turbine shaft and are adapted to allow the cooling air to essentially be discharged from the individual cooling-air outlet orifices in the direction of rotation of the gas turbine.

Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.

Abstract: A grille shutter unit which is provided with shutters and a frame which pivotally supports shutter shafts provided at the shutters is attached to a frame-shaped shroud which supports heat exchangers. The grille shutter unit is configured to be attached to the shroud from a back-face side of the shroud at a position located in front of the heat exchangers.

Abstract: Aspects of the disclosure are directed to systems and methods for receiving operating state parameters associated with an operative state of an aircraft, determining a clearance value between a first structure of the engine and a second structure of the engine, where the clearance value is determined based on the operating state parameters and a passive clearance model that includes a specification of an uncertainty in the clearance value, determining that the clearance value deviates from a clearance target in an amount that is greater than a threshold, and engaging an active clearance control (ACC) mechanism based on the deviation.

Abstract: A steam power installation has a steam turbine and a valve-stem leakage steam line. A fitting is arranged in the valve-stem leakage steam line, which fitting is used to conduct the valve-stem leakage steam into a suitable valve-stem leakage steam collector, such as into a condenser.

Abstract: A centrifugal compressor includes: a compressor housing; an impeller wheel for compressing intake air, disposed inside the compressor housing; a parallel flow generating unit for rectifying the intake air flowing in via an intake port to be parallel to the direction of a rotation shaft; and a recirculation channel for returning a part of the intake air in an outer circumferential section of the impeller wheel to an upstream side of the impeller wheel. The parallel flow generating unit includes a parallel flow generating part including a plurality of guide vanes and a central intake-air flowing section which is a space surrounded by the parallel flow generating part. An intake-air outflow direction from an upstream opening is oriented toward the parallel flow generating part.

Abstract: The invention discloses a centrifugal compressor. The centrifugal compressor includes multiple stages of compression units which are communicated in sequence. Each stage of compression unit includes a diffusion cavity (1) and a diffusion adjustment device, wherein the diffusion adjustment device includes a movable member (21) configured to change a radial flow area of the diffusion cavity (1) provided in correspondence thereto, the movable member (21) being movably provided in an axial direction of the centrifugal compressor. The invention also discloses a centrifugal unit having the centrifugal compressor. The movable member of each stage of compression unit of the centrifugal compressor changes the radial flow area of the diffusion cavity of this stage of compression unit, thereby effectively reducing the possibility of surging.

Abstract: Said hydraulic turbine includes a wheel which is made to rotate about a rotational axis (X2) by a main water stream (F1) going from a penstock to a suction tube along a flow path that passes through the wheel. Said turbine also includes first means that are placed outside the flow path of the main water stream (F1) and enable the mixing of a secondary water stream (F2), taken from the flow path and located upstream from the wheel, and an oxygen-containing gas (A2). Said turbine also includes second means for injection, downstream from the wheel of the turbine, a water/gas mixture (F3) produced in the first means.

Abstract: A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.

Abstract: A method for monitoring for a surge condition includes detecting a surge condition through vibration signals measured at at least one location in a turbomachine. Detecting a surge condition includes determining a ratio-metric indicator RBR by comparing a blade frequency band ?B to a reference frequency band ?R. Detecting a surge condition includes calculating a surge score SS with the following equation: SS = R BR - R ? R ? wherein R? is a sample mean of a set of ratio-metric indicators and R? is a sample standard deviation of a set of ratio-metric indicators. Detecting a surge condition includes determining whether a surge condition exists based on the surge score.

Abstract: A rotary plant growing apparatus is disclosed having a light emitting source operable to emit light. The apparatus also has at least one retaining component and a support operable to support the at least one retaining component in spaced relation to the light emitting source. A rotation mechanism is operable to rotate the at least one retaining component in a path around the light emitting source. A position adjustment mechanism is operable to move the at least one retaining component along a path extending between the at least one retaining component and the light emitting source so to adjust the distance between the at least one retaining component and the light emitting source.

Abstract: The invention discloses a centrifugal compressor. The centrifugal compressor comprises: a housing (10), provided with a mounting chamber (11), a thread section (12) being provided on a side wall of the mounting chamber (11); an adjusting piece (20), mounted in the mounting chamber (11), the adjusting piece (20) being provided with threads adapting to the thread section (12); a driving piece (30), mounted in the mounting chamber (11) and configured to drive the adjusting piece (20) to move forwards or backwards along the thread section (12); and an adjustable diffuser (40), fixedly connected to the adjusting piece (20). The invention also discloses a centrifugal water chilling unit having the centrifugal compressor. The centrifugal compressor and the centrifugal water chilling unit can solve the problem that the adjustable diffuser easily inclines and is stuck, thereby greatly improving the reliability of the centrifugal compressor.

Abstract: Systems and methods for monitoring rotating machinery are disclosed. Transmitter and receiver antennas can be provided with access to the rotating machinery. At least one receiver signal resulting from at least one transmitter signal that has propagated through a portion of the rotating machinery can be obtained. A first signal pair can be formed from a first receiver signal and a first transmitter signal, or from first and second receiver signals obtained from spatially-separated receiver antennas, or from first and second receiver signals which are attributable to different transmitter signals. Amplitude and phase information of a plurality of frequency components for each signal in the first signal pair can be determined. A set of comparison values for the first signal pair can be determined by comparing respective frequency component phases or respective frequency component amplitudes. A characteristic of the rotating machinery can then be analyzed using the comparison values.

Abstract: An airfoil of a gas turbine engine is provided. The airfoil includes an airfoil body having at least one internal flow passage, the body having a first surface and a second surface, the first surface defining a wall of the at least one internal flow passage and a bleed port fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice extending from the second surface toward the internal flow passage and a bleed port cavity extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.

Abstract: A turbine stator vane assembly comprises a plurality of circumferentially arranged struts and a plurality of circumferentially arranged stator vanes. Each stator vane has a leading edge, a trailing edge and a chord length. Each strut has a leading edge, a trailing edge, a chord length, a pressure surface and a suction surface. The chord length of the struts is greater than the chord length of the stator vanes. The stator vanes are arranged in groups between adjacent pairs of struts and each group of stator vanes comprises a plurality of stator vanes. The circumferential spacing between adjacent struts is substantially the same and each stator vane in a group of stator vanes has a different chord length to the other stator vanes in that group of stator vanes.

Abstract: A pump for delivering fluid has a pump housing and a pump chamber having a pump chamber cover and a pump chamber base in said pump housing, an inlet and an outlet. In the pump chamber, an impeller rotates on a rotor shaft which is connected to a drive motor. The inlet is arranged in the pump chamber cover and the outlet is arranged below the impeller in the axial direction of the pump at that end region of the pump chamber which is remote from the inlet close to the outlet. The distance from the inlet to the outlet with the impeller therebetween can correspond approximately to the diameter of the pump chamber.

Abstract: A compressor control system includes a compressor compressing a fluid, an anti-surge valve preventing backflow in the compressor, the anti-surge valve being arranged on a line connecting an inlet and an outlet of the compressor and operated by a first signal, an inlet guide vane controlling an opening area of the inlet, the inlet guide vane being arranged at the inlet and operated by a second signal, and a controller connected to the anti-surge valve and the inlet guide vane and generating the first signal to control the anti-surge valve, a vane control signal to control the inlet guide vane, a pressure compensation signal to control the inlet guide vane to compensate for a change in pressure at the outlet of the compressor according to the first signal, and the second signal by combining the pressure compensation signal with the vane control signal.

Abstract: A method and apparatus for surge prevention control for multistage compressors with at least two stages, at least one flow measuring device, and one overall surge recycle valve is disclosed. Furthermore, a method of accurate calculation of surge limit line for overall multistage compressor using one available flow measuring device is also disclosed. The method of surge prevention calculates multistage compressor's surge limit line as a product of individual stages surge limit lines that differs from those revealed in the prior art. This method allows accurate calculation of the distance of operating point to surge limit line that takes in account surge lines of all stages and allows reliable surge prevention control.

Abstract: A device and a method for converting low temperature thermal energy into high temperature thermal energy using mechanical energy with a rotor for a working medium passing through a closed cycle. The rotor has a compressor unit with compression channels and an expansion unit with expansion channels, and has heat exchangers for exchanging heat between the working medium and a heat exchange medium. The device has an impeller which can be rotated relative to the rotor. The impeller is arranged between supply channels which conduct the flow of the working medium in the heat pump and at least one rotor discharge channel which discharges the flow of the working medium in the heat pump. The supply channels have outlet sections which extend up to a point directly upstream of an inlet opening of the impeller such that flows of the working medium are conducted out of the supply channels.

Abstract: A stepwise operating parallel-type hydro power generation system having a fixed flow path includes a parallel pipe, a first power generation facility, a second power facility generation facility, first and second flow regulators, and a controller. The parallel pipe includes an inlet pipe, an outlet pipe, and a first straight pipe and a second straight pipe. The first and second straight pipes connected between the inlet pipe and the outlet pipe. Each of the first and second power generation facilities includes a water turbine rotating with the water introduced thereinto and a power generator operating according to the rotation of the water turbine. The controller is configured to open and close either or both of the first and second flow rate regulators at the same time.

Abstract: A gas turbine engine includes a rotor hub which includes a substantially axially extending projection and a substantially radially extending projection. A seal ring includes a body portion and at least one knife edge that extends outward from the body portion. A recess is in the body portion for accepting the axially extending portion of the rotor hub. The seal ring includes at least one cooling passage that extends through the seal ring. A lock ring is in abutting contact with the seal ring and the radially extending projection on the rotor hub for securing the seal ring to the rotor hub.

Abstract: A compressor assembly for a turbomachine includes a compressor wall including circumferentially spaced stator vanes defining at least one row of stator vanes. The at least one row of stator vanes defines at least one stator passage therein. Each stator vane includes a leading edge, an opposite trailing edge defining an axial chord distance, and a pressure side. The compressor assembly also includes, at least one bleed opening defined within the compressor wall and disposed adjacent the pressure side in the at least one stator passage within a range from approximately 20% the axial chord distance upstream of the leading edge to approximately 20% the axial chord distance downstream of the trailing edge. The compressor assembly further includes at least one bleed arm extending from the at least one bleed opening with at least a portion of compressor airflow extractable through the at least one bleed arm.

Abstract: Discloses is a turbine power generation system having an emergency operation means and an emergency operation method therefor that are capable of controlling excess heat accumulated during emergency operation, and recycling the accumulated heat. A turbine power generation system includes: an inlet sensor part including a thermometer, a pressure gauge, and a flowmeter that are installed between the heater and the inlet valve and; an emergency discharge part including a branch pipe connected to the steam, and a heat control means installed on the branch pipe. Accordingly, the system and the method are capable of reducing a heat overload during an emergency operation by transferring a heat amount exchanged in the heat storage device to the heat consuming facility, minimizing thermal consumption by recycling the same, and preventing various problems caused by stopping an operation of the turbine power generation system.

Abstract: The disclosure includes controlling a pressure ratio for a compressing system, comprising introducing a quantity of liquid into an input stream to create a multiphase input stream, compressing the multiphase input stream with a centrifugal compressor to create a discharge stream, measuring a parameter of the discharge stream, wherein the discharge parameter corresponds to a pressure ratio for the centrifugal compressor, when the parameter exceeds a first predetermined point, increasing a pressure ratio of the centrifugal compressor by increasing the quantity of liquid introduced, and when the parameter exceeds a second predetermined point, decreasing the pressure ratio by decreasing the quantity of liquid introduced.

Abstract: A radial turbine includes a housing, a rotor mounted on a shaft, an inlet channel for supplying a defined working medium, and an outlet channel. The rotor includes working cavities, with a generally spiral shape, which conduct the defined working medium from the inlet channel to the outlet channel, located near the center of the rotor. The working cavities have a generally rectangular cross-section, with a width (W), parallel to an axis of rotation of the rotor, and a height (H), parallel to a radius of the rotor. The width (W) is greater than the height (H), and the height (H) is not greater than six times a thickness of a boundary layer of the defined working medium.

Abstract: A turbine engine assembly and methods involving a turbine engine assembly are provided. In one method, the turbine engine assembly is received. The turbine engine assembly includes an annular stator vane structure disposed at a first orientation. The stator vane structure is reconfigured with the turbine engine assembly to be disposed at a second orientation.

Abstract: There is provided a centrifugal compressor apparatus including a centrifugal compressor that centrifugally compresses a gas, an electric motor that rotatably drives the centrifugal compressor, a current detector that detects a drive current I of the electric motor, and an exhaust valve that discharges a compressed gas to a lower pressure section. The centrifugal compressor apparatus (A) detects the drive current I at a sampling cycle ts, (B) updates, as a current threshold, in real time, a value “(moving average)?n×(standard deviation)” for which a plurality of drive currents measured in a sampling period tp serves as a population, where n is a positive number in the range of 3 to 4 and, (C) determines that surging has occurred when the exhaust valve is closed and the drive current I is below the current threshold X, and (D) further opens the exhaust valve to discharge the compressed gas when determining that surging has occurred.

Abstract: An outlet housing for an aircraft cabin air compressor includes a volute comprising radially inner and outer portions, and having first, second, third, and fourth circumferential regions. The first circumferential region is between the fourth and second circumferential region. The second circumferential region is between the first circumferential region and the third circumferential region. The third circumferential region is between the second circumferential region and the fourth circumferential region. A portion of the volute in the first circumferential region has a first wall thickness. A portion of the volute in the second circumferential region has a second wall thickness. A portion of the volute in the third circumferential region has a third wall thickness. A portion of the volute in the fourth circumferential region has a fourth wall thickness.

Abstract: A high efficiency induced-flow wind power system engages and converts both potential (to-pull) and kinetic (to-push) wind energies to effective airflow power, delivering induced (accelerated) airflow power in a controlled flow field to a turbine/rotor, impelling a 360-degree torque on the turbine/rotor and, as a result, extracting (converting) more than 80% of the combined effective wind power to mechanical power. The induced push-pull effect results in higher efficiency wind-to-mechanical power extraction (conversion). The induced-flow wind power system can be coupled with (i) an electrical generator, inverter/converter for generating AC and DC power, (ii) pressurized vessel for effective energy storage (iii) a pressurized structure, such as an air supported structure, to ensure its structural integrity.