Abstract: Automatic testing for control valves is provided for diagnosing of actuators, including actuators not equipped with analog or discrete position transmitters. A valve controller confirms steady-state conditions for a turbo-compressor system that includes a control valve in a first position and sends, to an actuator for the control valve, a signal to initiate a partial valve stroke to move the control valve away from the first position. The valve controller receives feedback signals from sensors in the turbo-compressor system and monitors the feedback signals for a change from the steady-state conditions. When the monitoring detects a change from the steady-state conditions within a defined time period, the valve controller sends, to the actuator, a signal to return the control valve to the first position. When the monitoring does not detect a change from the steady-state conditions within the defined time period, the valve controller generates an alarm signal.

Abstract: An anti-icing system at least includes: a precooler that exchanges heat between bleed air and outside air; and an anti-icing unit that receives the bleed air passed through the precooler. A bleed air flow rate adjusting section that adjusts a flow rate of the bleed air supplied to the anti-icing unit adjusts the flow rate of the bleed air to suppress pressure of the bleed air to a pressure upper limit or lower by using relationship r1 and relationship r2. The relationship r1 is a relationship between an altitude and a pressure upper limit of the bleed air. The relationship r2 is a relationship between the pressure upper limit and outside air temperature at which the temperature of the bleed air reaches allowable temperature of ducts and other members through which the bleed air flows. The relationship r2 is provided based on the altitude.

Abstract: A gas turbine includes a compressor, a combustor, a turbine, a generator, and a control apparatus, the compressor being provided with an air extraction valves, a plurality of inlet guide vanes, and a plurality of casing air extraction valves at its last stage, in which the control is carried out on at least one of the opening of the air extraction valve, the opening of the inlet guide vanes, and the number of openings of the casing air extraction valves which are defined as control parameters taking blade vibration stress values as indexes based on a compressor metal temperature included in behavior parameters of the gas turbine.

Abstract: A stator vane angle system includes an engine case, a plurality of stator vanes located at an interior of the engine case. Each stator vane is rotatable about a stator vane axis. A synchronization ring is located at an exterior of the engine case. The synchronization ring is operably connected to each stator vane of the plurality of stator vanes such that movement of the synchronization ring urges rotation of each stator vane of the plurality of stator vanes about their respective stator vane axes. A plurality of impingement openings extend through the engine case from the interior of the engine case to the exterior of the engine case. The plurality of impingement openings are configured to direct flowpath gases from the interior of the engine case to impinge on the synchronization ring, thereby reducing a thermal mismatch between the engine case and the synchronization ring.

Abstract: A bleed valve for an air plenum includes a valve body which defines a valve seat. A poppet is movable relative to the valve seat between an open position and a closed position. A spring biases the poppet to the open position and toward the air plenum.

Abstract: A device for regulating the flow rate of air feeding a turbine ventilation cavity of a turbomachine turbine section is disclosed. The device includes at least one tubular duct opening into a take-off cavity and leading into a turbine ventilation cavity, the pressure inside the take-off cavity being higher than the pressure inside the turbine ventilation cavity; an air flow rate regulation valve disposed in the tubular duct, the valve being suitable for moving under the effect of the pressure difference between the take-off cavity and the turbine ventilation cavity; and a mechanical return device for holding the valve in a maximum closure position for the duct so long as the pressure difference between the take-off cavity and the turbine ventilation cavity remains below a predetermined threshold pressure.

Abstract: The invention is directed to a turbine (3) for generating power in a drill string (2), including a turbine rotor (10) drivable by a fluid and a bypass device having a first bypass channel bypassing the turbine rotor (10). For varying the volumetric flow through the bypass channel, provision is made for a valve (28) and a control device driven by the fluid and having a drive element (24) by means of which the valve (28) is movable anywhere between a first and a second position. The drive element (24) produces a flow resistance in the fluid flow path downstream from the turbine rotor (10) and downstream from the valve (28) and in the flow direction takes support upon a spring (26).

Abstract: To provide a method of controlling a turbine equipment and a turbine equipment capable of carrying out a starting operation of controlling a load applied to a speed reducing portion while complying with a restriction imposed on an apparatus provided at a turbine equipment. The invention is characterized in including a temperature elevating step (S1) of elevating a temperature of a working fluid flowing to the turbine portion, a flow rate increasing step (S2) of increasing a flow rate of a working fluid bypassed from a delivery side to a suction side of the compressing portion when a temperature of the working fluid flowing to the turbine portion is elevated by a heat source portion, and a flow rate reducing step (S3) of reducing the flow rate of the bypassing working fluid after an elapse of a predetermined time period after increasing the flow rate of the bypassing working fluid.

Abstract: In a method of modifying a turbocompressor, the compressor blades are replaced by new compressor blades in such a way that the delivered mass flow of the compressor increases. At the same time, the capacities for blowing off during the start-up are increased.

Abstract: A turbo chiller that can accurately determine the existence of surging occurring in a centrifugal compressor is provided. In a centrifugal compressor of a turbo chiller, which includes an impeller for compressing refrigerant, a resistance temperature sensor for detecting the refrigerant temperature is provided at the upstream side of the impeller. Accordingly, a temperature rise caused by surging can be detected and the existence of surging can be accurately determined.

Abstract: A bleed valve for use in a gas turbine engine is provided; the bleed valve may be used to relieve air pressure from a compressor stage of the engine. At normal pressure and when the engine is off, the bleed valve is in the open position. However once the engine starts, air pressure provided by the compressor closes the bleed valve. During engine operation, the bleed valve is opened to relieve air pressure by providing pressurized fluid, such as compressor air, to a valve chamber. The bleed valve is designed so that moveable parts of the valve, including contact seals and a sliding shaft, are protected by the valve structure from debris and contaminants carried in the engine's air stream.

Abstract: Apparatus (10) controls net thrust in a steam turbine (T) in response to changes in the operating condition of the turbine. The turbine includes a thrust bearing (B) positioned between low and intermediate pressure sections (LP, IP) of the turbine and a high pressure section (HP) thereof. Sensors (14) for sense thrust loads on the thrust bearing. A number of control valve (CV1-CV4) are used to balance pressures occurring at locations within the high pressure section of the turbine. A controller (16) is responsive to the sensors sensing a change within the turbine indicative of a significant change in net thrust to energize one or more of the control valves and to adjust the pressure within the high pressure section of the turbine so to maintain net thrust within an acceptable range of thrust values.

Abstract: A compressor assembly comprises a compressor having a rotor comprising a shaft with fan blades for compressing air. An air bearing serves to cool the shaft of the rotor. A compressor air inlet receives air for the fan blades, which is then exhausted from the fan blades out a compressor air outlet. An air flow path communicates air from the compressor air inlet to the air bearing. A valve controls the flow of air through the air flow path and has an open position permitting air through the air flow path and a closed position restricting air to the path.

Abstract: Disclosed is a system for operating gas turbine engine bleed valves in response to pressure values within the engine, wherein the engine pressure values are sensed electronically and routed to a programmable logic device, and wherein the programmable logic device control the opening and closing of the bleed valves in a manner that allows for reduced engine vibration with minimal loss of engine efficiency.

Abstract: A turbo-compressor comprises a compressor main body for compressing an operation fluid, an inlet guide vane apparatus being provided on a suction side of the compressor main body and having guide vanes, and a blow-off valve being provided in a discharge said compressor main body. An opening of the blow-off valve is variable. A pressure detector is provided on the discharge side of the compressor. At least any one of a time-period and a number of times of operations of the inlet guide vane apparatus is memorized in a memory, when it is operated at an inlet guide vane opening, being equal or less than a setting limit. A controller controls the blow-off valve and the guide vanes based on the values which are memorized in the memory.

Abstract: A turbo-compressor comprises a compressor main body for compressing an operation fluid, an inlet guide vane apparatus being provided on a suction side of the compressor main body and having guide vanes, and a blow-off valve being provided in a discharge said compressor main body. An opening of the blow-off valve is variable. A pressure detector is provided on the discharge side of the compressor. At least any one of a time-period and a number of times of operations of the inlet guide vane apparatus is memorized in a memory, when it is operated at an inlet guide vane opening, being equal or less than a setting limit. A controller controls the blow-off valve and the guide vanes based on the values which are memorized in the memory.

Abstract: Disclosed is a system for operating gas turbine engine bleed valves in response to pressure values within the engine, wherein the engine pressure values are sensed electronically and routed to a programmable logic device, and wherein the programmable logic device control the opening and closing of the bleed valves in a manner that allows for reduced engine vibration with minimal loss of engine efficiency.

Abstract: Accurate and effective antisurge control for turbocompressor stages is augmented by measuring the flow rate of fluid entering or leaving the stage of compression. On the other hand, turbocompressors with sidestreams, such as ethylene, propylene, and propane refrigeration compressors, pose unique antisurge control challenges; in particular, measurements for the flow rate entering (or leaving) the compressors' middle stages are not available in most cases. Furthermore, the methods used to cope with this lack of flow measurements are prone to introducing errors and producing false transients, as well as being cumbersome and difficult to implement. For these reasons, this disclosure relates to a method for protecting turbocompressors with sidestreams from the damaging effects of surge.

Abstract: Nozzle control apparatus for an axial flow air turbine having an inlet nozzle for air entering the turbine and an associated turbine inlet housing for channeling air flowing to the inlet nozzle for at least partially blocking air flow from the turbine inlet housing to the turbine inlet nozzle. The nozzle control apparatus uses an axially movable annular slider member that is biased to its open position by an annular spring and is moved axially by bleed air pressure exerted on a portion of the annular slider member.

Abstract: A process for operating multistage turbocompressors (2, 22, 42) with a plurality of controllers (15, 35, 55) which interact one with each other, in which each compressor stage has anti-surge control valves (5, 25, 45) of its own, which recycle into the suction lines (1, 21, 41) of their respective own compressor stage (2, 22, 42). The control is performed by flow computers (6,26,46) for calculating the suction flow and computers (7,27,47) for determining the minimum acceptable flow from the delivery head. A comparison unit (12, 32, 52) determines the difference between the set point (derived from delivery head) minus the actual value (flow) and whenever the actual value is too low compared with the set point, it brings about a gradual opening of the corresponding surge line control valves (5, 25 and 45) until the actual flow exactly corresponds to the flow set point, which depends on the particular delivery head.

Abstract: The operation of quickly taking a turbocompressor off-line from a parallel configuration, of a gas pipeline compressor station, may encounter increased mechanical action (in particular, vibration) upon recycle piping and the additional risk of compressor surge. For these reasons, this invention relates to a method and apparatus for decreasing vibratory loads and for increasing surge prevention effectiveness, while initiating an off-line operation, by (1) altering the surge control line's location, at a preset rate, from its initial location to a predetermined new location; and (2) decreasing the turbocompressor's deceleration rate when the operating point intercepts the surge control line before the control line reaches its new location. Upon completion of the off-line activity, the control line returns to its initial location; and the reduction of compressor speed will cease on reaching a preset value.

Abstract: The stroking speed of an antisurge control valve is impeded by the combined damping effects of signal dead time and the inherent lag of ancillary pneumatic components within a primary control loop. Furthermore, as control valve actuator size increases, the negative influence of these two impediments (dead time and lag) is amplified. As a result, control valve response times are adversely affected; and the possibilities of surge-induced compressor damage and process upsets are heightened. For these reasons, this disclosure relates to a method for protecting turbocompressors from impending surge, and for preventing subsequent process upsets, by improving antisurge control. But more specifically, it describes a technique for decreasing damping effects by evacuating control valve actuators (diaphragm or piston) through restrictions having a lower resistance to compressible-fluid flow rather than through volume boosters--consequently, increasing a control valve's opening speed to that of an emergency shutdown.

Abstract: The present invention relates to a control system for controlling injection and extraction of steam in a steam turbine (1), the same valves (5,6) being used both for injection of steam to the turbine (1) and for extraction of steam from the turbine (1) . The valves (5, 6) commonly used for injection and extraction are controlled to be timely opened and closed in dependence on the pressure conditions at injection points (2,3) and extraction points (2,3), respectively, in the turbine and on the pressure (P3) prevailing in a process network connected to the valves (5, 6) such that injected or extracted steam is utilized in an optimal manner.

Abstract: A novel centrifugal pumping system is disclosed for supplying fuel to aircraft gas turbines. The system has a common rotor with two different sets of impeller blades on opposite sides. A regenerative/liquid-ring starting pump is located on one side of the rotor, and a centrifugal impeller is located on the other. During engine start-up, the regenerative/liquid-ring pump is capable of priming itself and supplies engine fluid and pressure. The starting pump delivers fuel until the main pump reaches a speed sufficient to provide adequate pressure for fuel delivery. At that time, the starting pump is switched off, via a valving system.

Abstract: An anti-surge valve (11) equipped with a servomotor and connected between the outlet of the compressor (12) and its inlet, the servomotor being controlled from a regulating system (13) which receives at the input a parameter (m) representing the flow of the compressor and a nominal value (c) determined from the inlet pressure and outlet pressure of the latter, for the purpose of injecting some of the outlet flow of the compressor at the inlet of this, in order to keep it above its breakaway point. The device comprises a quick-emptying solenoid valve (16) of the servomotor of the anti-surge valve and means (17, 18) for controlling this as a function of the amount of deviation between the parameter and the nominal value.

Abstract: In a compressor station for boosting the pressure of gas stream being transported in a pipeline wherein the act of recompressing the gas stream to a desired pressure results in a gas temperature sufficiently high to stimulate cracking activity in the pipeline when the compressed stream gas is reinjected into the pipeline, method and apparatus are disclosed for cooling a portion of the warm compressed gas to form a cool gas stream and then controlling a division of the cooled stream to supply both a cooled recycle stream for anti-surge control and a cooled stream for mixing with the warm compressed gas for temperature control.

Abstract: An axial thrust limiting system for a steam turbine including a rotor having a shaft, the turbine containing a plurality of chambers each defining a pressure zone containing a fluid which, during operation of the turbine, is at a pressure which influences the axial thrust load on the shaft, the turbine being constructed such that at least during rapid shut down a pressure differential can develop between two of the chambers to create an excessive axial thrust load on the shaft. The axial thrust limiting system includes controllable valve connected in a fluid flow path between the two chambers, and valve operating components connected for operating the valves during rapid shut down of the turbine in order to reduce the pressure differential between the two chambers.

Abstract: A ring of an annular valve assembly is movable in the direction of its longitudinal axis and is intended for an axial compressor blow-off arrangement. The ring takes the form of an axially orientated channel-section member having a first annular skin of concave section nested in a second annular skin also of concave section. A cavity filled with a synthetic resin filler is defined by the two skins. The blow-off arrangement for an axial-flow compressor of a turbo-jet engine, which incorporates this ring, comprises an annular opening with which the ring cooperates to re-form the wall of the air flow when the blow-off arrangement is inoperative.

Abstract: A device is provided for indicating a fluid pressure and flow reversal. The device comprises a float tube in which a float is slideably disposed. An accumulator is disposed in communication with the float tube. The float tube is further in communication with a fluid pressure line. Pressure and flow reversals in the pressure line cause a noticeable movement of the float within the float tube.

Abstract: A turbocharged engine is provided with a turbine housing which has an inlet, an outlet located radially interiorally from the inlet, a centrally located turbine wheel cavity, and an internal scroll passageway which diminishes in cross section as it leads from the inlet around the turbine wheel cavity. The scroll passageway means is bifurcated from the inlet through an arc of between 180.degree. and 300.degree. to divide the incoming exhaust gas from different sets of cylinders of an internal combustion engine into identical, but separate, flow paths to minimize feedback of pulsations of exhaust gases from one set of cylinders to the other. The separate flow paths within the turbine housing are combined into a single flow pathway near the end of the scroll passageway, and a single wastegate valve is in communication with the single flow pathway.

Abstract: A centrifugal main fuel pump (10') for a gas turbine engine has a housing (12') in which a centrifugal impeller (16') is mounted for rotation. The centrifugal impeller includes a disc (24') which carries starting flow impeller elements (34) which are positioned in a radially outer location on the disc and also carries main flow impeller elements (26') positioned in a radially inner location on the disc. The starting flow impeller elements discharge to a starting flow collector (38) and diffuser (44) and the main flow impeller elements discharge to a separate collector (30') and diffuser (32'). The starting flow impeller elements produce adequate fuel flow at the pressure necessary for engine lightoff while the main flow impeller elements are adapted to supply engine fuel flow demand in the normal range of operation. A check valve (46) prevents starting flow from returning to the centrifugal impeller.

Abstract: A centrifugal vapor compressor having a two-position, pressure controlled diffuser throttle ring is disclosed. The throttle ring is positively maintained in a minimum or a maximum throttling position by supplying either a relatively low pressure or a relatively high pressure, respectively, to a cavity behind the throttle ring. The throttle ring may be one of any of a variety or types of throttle rings including a new, improved throttle ring having a back portion with a sealing means which facilitates sliding movements of the throttle ring and which prevents vapor flow between the cavity behind the throttle ring and the diffuser passageway.

Abstract: Temperature regulation of an air cycle refrigeration system is achieved by selectively adjusting the turbine stator geometry in response to the temperature of turbine airflow at a desired location. Such adjustment in stator geometry includes the selective positioning of a portion of the stator adjacent the turbine blades thereby controlling the amount of cooling produced by the turbine or the selective opening and closing of bypass ports provided in the turbine stator to control the flow of air through the turbine. Both of these adjustments in stator geometry are effected by an actuator comprising at least two members of differing coefficients of thermal expansion such as a bimetallic element.

Abstract: To provide reduction in temporary conditions of excess load on the thrust bearing, a labyrinth positioned contiguous to a leakage aperture in the high pressure side of a single stage overhung compressor rotor affords controlled leakage to a venting circuit in communication with a lower pressure system. A pressure switch responsive to pressure levels in the venting circuit prevents compressor start at pressures above the set point of the switch while a backpressure valve in the venting circuit when operative maintains a predetermined pressure level therein. When the thrust bearing is operating at speeds sufficient to enable acceptance of the load imposed by compressor pressure, an override solenoid valve serves to close the backpressure valve and operably shut the venting circuit.

Abstract: The invention comprises incorporating in the wall of a typical unloader valve for a compressor, a normally-closed, pressure-responsive valve for admitting product compressed air therethrough, into the valve chamber, for re-circulation of the admitted air through the compressor. In the first embodiment illustrated, a pilot air pressure, which modulates the unloader valve throttling piston, is also addressed to a passageway which opens onto the normally-closed valve. When the pilot air pressure is substantially elevated, the normally-closed valve opens.

Abstract: An arrangement for operating shut-off members in gas turbine engines, particularly turbojet engines. Circumferential rotation of an actuating ring is converted into axial opening or closing movement by transmission element. These transmission elements are in the form of bellcranks which are pivotally supported in their elbow area on a fixed casing of the engine. A free arm end of each bellcrank is hinged to the actuating ring. Another free end of each bellcrank is hinged to a pull rod engaging at least one axially moveable shut-off member, or an axially adjustable shut-off element thereon. Two pull rods associated with respective shut-off members, are each pivotally connected on a side opposite the associated shut-off members at various points of an arm of the bellcrank. The arrangement is such that co-directional movement of the shut-off members produces different travels or strokes of the shut-off members.

Abstract: The proposed method for automatic control of a power plant is as follows. A control signal of the electric generator's electric load is applied to a first control element which controls the flow of gas supplied from the gas line to the high-pressure section of an expansion engine. This controls the amount of gas directed from the take-off chamber of the expansion engine to the gas pipeline. A control signal to control the pressure downstream of the expansion engine is applied to a second control element to control the flow rate of the gas flow directed from the low-pressure section of the expansion engine to the controlled counter-pressure line. A control signal to control the pressure downstream of the expansion engine is applied to a third control element to control the gas flow rate, which is installed in the line that bypasses the low-pressure section of the expansion engine, whereby the rest of the gas flow is directed to the controlled counterpressure line.

Abstract: The disclosure illustrates a turbocharger wastegate valve comprising a cylindrical chamber connected through a radial inlet to the gas stream upstream of the turbine. High pressure air is selectively directed across the inlet through a nozzle to prevent or permit flow into the chamber which is connected to a point downstream of the turbine. The pressure of the air delivered to the nozzle may be varied to proportion the gases bypassed around the turbine.

Abstract: An impeller having an axle with radial vanes is mounted within a housing. The housing includes a funnel to direct a large amount of wind into the impeller. Air fins on top of the housing maintain the funnel pointed into the wind. A flap upon the top of the housing will fold downward as the wind increases and this will raise a throttle valve at the throat of the funnel. In addition, the flap will close exhaust openings from the housing, also reducing the wind on the vanes. Two additional flaps act as pressure relief valves in the funnel which open to dump wind at excessive velocity. Furthermore, a leeward flap on the side of the funnel is blown out to an extended position at high winds which causes the housing to rotate upon its circular tracks to bring the funnel opening away from the wind. The air fins on top of the housing are blown down from the vertical position as the wind strikes the housing sideways.The housing is mounted upon a frame which extends horizontally outward from the housing.

Abstract: An inducer for a high speed centrifugal pump includes a shaft located upstream of the inlet eye of the centrifugal pump concentrically within an inlet bore; and further includes a plurality of axial blades on an inducer shaft for producing a boost pressure to the inlet of the centrifugal pump and wherein means are included to direct a spray of fuel in a direction radially of the longitudinal axis of the shaft immediately upstream of the blades to reduce the amount of fuel flow across the inducer with a resultant lowered pressure rise than would otherwise occur.

Abstract: The opening of variable bleed doors is scheduled as a function of both booster and compressor speed so as to better maintain the desired booster stall margin and increase efficiency during certain periods of engine operation. The schedule based on core speed is modified in response to changes in fan speed to increase or decrease the amount of bleed, thereby increasing stall margin or improving the steady-state performance, respectively.

Abstract: Provided is a method of controlling a by-pass valve in which the discharge valve is opened or closed in an interlocked relation woth a turbine flow regulating means such as wicket gates of a water-turbine in order to bypass a stream of water with respect to the turbine in synchronism with the movement of wicket gates, thereby decreasing pressure fluctuation in a penstock of the turbine during transient conditions of operation, and is eventually closed when the wicket gates are held in an equilibrium state, thereby eliminating prolonged wasting of the available water.

Abstract: Control apparatus for programmed control of a plurality of gas turbine engine compressor air bleed valves in response to a plurality of control input signals representing engine operating conditions including variable conditions related to engine power output. The control inputs are sensed and/or computed and scheduled to provide accurate and reliable control over a plurality of compressor air bleed valves by means including a hydraulic programmer with a three dimensional compressor rise scheduling cam and adjustable hydraulic timers.

Abstract: Control apparatus for programmed control of a plurality of gas turbine engine compressor air bleed valves in response to a plurality of control input signals representing engine operating conditions including variable conditions related to engine power output. The control inputs are sensed and/or computed and scheduled to provide accurate and reliable control over a plurality of compressor air bleed valves by means including a hydraulic programmer with a three dimensional compressor rise scheduling cam and adjustable hydraulic timers.

Abstract: This invention relates to an improved surge control for a gas turbine type of power plant that bleeds the compressor to avoid surge and serves to isolate the effect that the engine area change has on the compressor discharge pressure rate signal to effectuate a viable signal indicative solely of acceleration and deceleration.

Abstract: A boost and bleed device for a gas turbine engine comprising a primary duct hrough which a primary gas flow passes, and containing a low-pressure compressor and a high-pressure compressor which are independent of one another, and a secondary duct through which a secondary airflow passes. A main duct places in communication with the secondary duct that primary duct section which is comprised between the low-pressure compressor and the high-pressure compressor. This duct may be closed off by two flaps each of which contains an opening which itself may be closed off by a plate. Thus, even when said flaps are closed, an auxiliary duct exists which places the primary duct in communication with the secondary duct. The main duct makes it possible to boost the high-pressure compressor during the starting phase. The auxiliary duct makes it possible to bleed the low-pressure compressor during the acceleration phase.

Abstract: The disclosure of this invention relates to means for detecting compressor surge by sensing the pressure downstream of the compressor of a turbine type power plant for rapidly opening the compressor bleeds and holding the bleeds open for brief interval after surge disappears. The sensed pressure is admitted to one side of the diaphragm through a laminar flow restrictor for obtaining a lag time constant which increases as pressure decreases.