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.

Abstract: An aircraft with aturbofan engine assembly having at least one compressor, a nacelle surrounding the turbine engine and defimng an annular bypass duct between the nacelle and the turbine engine, a thrust reverser having at least one moveable control surface, a thrust reverser locking system configured to selectively lock the thrust reverserand an injection cooling system.

Abstract: A gas turbine includes at least one rotor assembly and at least one compressor casing. The compressor casing has at least one inner compressor casing chamber for arranging the rotor assembly and at least one outer compressor casing chamber for tempering the compressor casing. The inner and outer compressor casing chambers are separated from each other by a separating casing wall. The outer compressor casing chamber has at least one boundary casing wall. The boundary casing wall and the separating casing wall are oppositely spaced such that the outer compressor casing chamber is formed. The boundary casing wall has at least one inlet opening for leading in an inlet tempering gas flow with tempering gas into the outer compressor casing chamber such that a tangential material temperature variation of the compressor casing is reduced in comparison to a non tempered compressor casing.

Abstract: An aeronautical propulsion system includes a fan having a plurality of fan blades rotatable about a central axis and defining a fan pressure ratio, FPR. The propulsion system also includes an electric motor mechanically coupled to the fan for driving the fan, the electric motor including a number of poles, npoles, and defining a maximum power, P. The relationship between the fan pressure ratio, FPR, of the fan, the number of poles, npoles, of the electric motor, and the maximum power, P, of the electric motor is defined by an equation: n pole p = C 1 · e - 9.062 · FPR + C 2 · e - 1.2604 · FPR ; wherein C1 is a constant having a value between 22,000 and 52,000, wherein C2 is a constant having a value between 4.0 and 9.8, and wherein e is Euler's number.

Abstract: An apparatus can include a first curved blade for use in a centrifuge. The centrifuge can be for collecting debris particles in a fluid flowing through the centrifuge. The first curved blade can include a plurality of eccentric slots. The first curved blade can include a groove positioned at an outer edge of the curved blade. The first curved blade can also include a first mating element and a second mating element. The first and second mating elements can be for coupling the first curved blade to a second curved blade about a central axis.

Abstract: A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.

Abstract: A hydrostatic seal and vibration damping apparatus for a gas turbine engine adapted to reduce vibrations during cold engine start-ups is disclosed. In one disclosed configuration, the vibration damping apparatus is comprised of a temperature sensitive control ring having a relatively high coefficient of thermal expansion adapted to expand quickly at relatively low temperatures to protect the hydrostatic seal during such gas turbine engine startups. At operational temperatures, the control ring is adapted to become separated from the hydrostatic sea.

Abstract: An example method of reducing a vibratory response of airfoils that support a shroud includes circumferentially misaligning some of the airfoils in a radially inner array of airfoils with all airfoils of a radially outer array of airfoils, and circumferentially aligning at least one of the airfoils in the radially inner array of airfoils with all airfoils of the radially outer array of airfoils.

Abstract: A centrifugal compressor assembly for use in a turbine engine is provided. The assembly includes an impeller that includes a plurality of rotor blades. The assembly also includes a stationary assembly circumscribing the impeller such that a clearance is defined therebetween. The stationary assembly includes at least one articulating seal member positioned adjacent the plurality of rotor blades, and a biasing mechanism configured to cause the at least one articulating seal member to selectively translate relative to the plurality of rotor blades based on an operating condition of the turbine engine.

Abstract: A centrifugal compressor for a chiller includes a casing, an inlet guide vane, an impeller downstream of the inlet guide vane, a motor and a diffuser. The casing has inlet and outlet portions with the inlet guide vane disposed in the inlet portion. The impeller is rotatable about a rotation axis defining an axial direction. The motor rotates the impeller. The diffuser is disposed in the outlet portion downstream from the impeller with an outlet port of the outlet portion being disposed between the impeller and the diffuser. A hot gas injection passage is provided to inject hot gas refrigerant between the inlet guide vane and the impeller. A controller is programmed to control an amount of the hot gas refrigerant.

Abstract: A turbocharger unit for an internal combustion engine having at least one exhaust line for the evacuation of exhaust gases from the combustion chamber of the engine and at least one inlet line for the supply of air to the combustion chamber is provided. The turbocharger unit includes a turbine which interacts with a compressor in order to extract energy from the exhaust-gas flow of the engine and pressurize the inlet air of the engine. The compressor is of the radial type and is provided with an impeller having backswept blades in which the blade angle between an imaginary extension of the center line of the blade between root section and tip section in the direction of the outlet tangent and a line connecting the center axis of the impeller to the outer tip of the blade is at least about 40 degrees. The ratio between the inlet diameter of the impeller and its outlet diameter lies within the range 0.50-0.62.

Abstract: A system has an electric motor having a stator and a rotor. The rotor rotates with a shaft and the shaft drives a fluid rotor. A control senses a fault condition on the electric motor. The control actuates a speed reduction feature when a fault is detected to bring rotation of the motor rotor and the fluid rotor to a stop more rapidly than if the speed reduction feature had not been actuated.

Abstract: An outer diffuser case of a diffuser case assembly for use in a gas turbine engine may have a housing orientated about an engine axis, a forward flange projecting radially outward from the housing, a mid-flange spaced axially aft of the forward flange and projecting radially inward from the housing, and an aft flange projecting radially outward from the housing. The mid flange is spaced axially between the forward and aft flanges and is configured to detachably engage an inner diffuser case of the case assembly. The forward flange is configured to detachably engage a high pressure compressor and the aft flange is configured to detachably engage a high pressure turbine of the engine.

Abstract: A method for heating up a steam turbine or for keeping a steam turbine hot, which steam turbine has at least one pressure stage working at an initial pressure or intermediate pressure, at least one final pressure stage which is fluidically connected downstream of the pressure stage and works at a final pressure which is lower than the initial pressure or intermediate pressure, and at least one condenser which is connected downstream of the final pressure stage, wherein steam generated outside the steam turbine is introduced into the pressure stage. After flowing through the pressure stage and bypassing the final pressure stage, the steam is supplied directly to the condenser.

Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.

Abstract: A grill assembly for attachment to a vehicle front end including a base grill portion, having a front surface, a back surface, a perimeter portion, and cross-rail portions. The cross-rail portions define a plurality of grill openings therebetween. A plurality of louvers are configured to communicate with the plurality of grill openings. The assembly is in communication with a controller to effectuate generally linearly reciprocal movement of at least one of the base grill portion or the plurality of louvers in a direction generally defined by a direction of travel of the vehicle to vary an amount of air flow through the plurality of grill openings.

Abstract: A flow volume measurement device for a turbo compressor includes a first pressure guide tube communicating with an intake pipe connected to a second compression stage having a compressor impeller that compresses a gas; and a second pressure guide tube communicating with an intake port of the second compression stage, which has a smaller internal diameter than an internal diameter of the intake pipe, and measures the flow volume of the gas on the basis of a difference in pressure between the first pressure guide tube and the second pressure guide tube.

Abstract: A pre-diffuser may include a plurality of struts, and each strut may have a leading edge. An upper contour of the leading edge may have a forward end and an aft end, and may include a first radius and a second radius. The first and second radii may be associated with the forward end and the aft end, respectively. The first radius may also be located farther forward than the second radius, and may be larger than the second radius.

Abstract: Disclosed herein are a surge prevention apparatus and method for a centrifugal compressor. The surge prevention apparatus includes a control unit for controlling a gas provision operation based on a flow rate and pressure on an inlet side of a compressor and pressure on an outlet side of the compressor, and a gas provision unit for storing a part of gas flowing into the inlet side of the compressor and providing the stored gas to the inlet side in response to a control signal from the control unit.

Abstract: Aircraft turbomachine comprising at least one heat exchanger (40) and a gearbox (10) in a V-shaped overall configuration and comprising two lateral arms (20) joined together by a central joining piece, the heat exchanger being mounted between the arms of the gearbox.

Abstract: A life consumption of a component in a machine may be predicted. Load data may be received from a load session of the machine. A plurality of parameter sets may be accessed, each associated with a critical point of the component, which point is considered to have critical life consumption. For each critical point, life consumption may be calculated using a life consumption calculation model receiving the load data and the parameter sets as input. By selecting a plurality of critical points on the component, a more complete view is presented of how the different parts of the component are affected by the load session.

Abstract: A pulse width modulation control is provided for a suction valve located on a suction line. When the flow rate through a refrigerant system needs to be reduced, the suction valve is rapidly cycled from an open position to a closed position. A bypass line connecting compressor discharge to compressor suction with a bypass valve and a discharge valve positioned on the discharge side of the compressor are also provided. When the control closes the suction valve, it also closes the discharge valve to prevent the refrigerant to backflow into the bypass line, and, at the same time, the control opens the bypass valve. Opening of the bypass valve reduces discharge pressure, leading to reduction in compressor power consumption and subsequent operating efficiency gain.

Abstract: An energy production plant has a drive train including a differential gear (14) with three drive and power take-off assemblies, a first drive assembly being connected to a drive shaft, a power take-off assembly being connected to a generator (13) and a second drive assembly being connected to a differential drive assembly (16). The differential gear (14) is a planetary gear. Both an emergency brake (4) and a service brake (20) are located in the drive train. In the event of a power failure, grid fault or an emergency shutdown, the service brake (20) is activated such that the torque acting on the rotor (1) supplied by the drive train remains substantially constant for a period of at least 0.5 seconds.

Abstract: A two-sided turbocharger compressor wheel and a housing forming a diffuser for the compressor. A first side and a second side of the compressor wheel are characterized by different values of a trim and of an annulus area. A first side of the diffuser surrounds the first side of the compressor wheel, and a second side of the diffuser surrounds the second side of the compressor wheel. The first and second sides of the diffuser are characterized by different annulus area ratios. The blades of the first and second sides of the compressor wheel are angularly offset from one another. The compressor wheel is configured for greater flow through the side of the compressor wheel that faces away from a related turbine wheel.

Abstract: A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W1) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W2) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (DF) of the fan to a maximum blade diameter (DL) of the second turbine is at least 3.5, in particular at least 4.

Abstract: A method for controlling a wind farm includes: receiving temperature data associated with a plurality of locations along a sound path between the wind farm and a sound immission point from one or more sensors; estimating a propagation characteristic of the sound path based at least in part on the temperature data; predicting a noise level at the sound immission point based at least in part on the propagation characteristic; determining a control signal for one or more wind turbines in the wind farm based at least in part on the noise level; and using the control signal to control the one or more wind turbines.

Abstract: A torque converter is provided. The torque converter includes a front cover, an impeller shell and a turbine axially movable to frictionally engage the impeller shell such that the turbine forms a piston of a lockup clutch. A first pressure chamber is defined axially between the turbine and the impeller shell. The torque converter further includes a reaction plate positioned axially between the front cover and the turbine. A second pressure chamber is defined axially between the reaction plate and the turbine and a third pressure chamber is defined axially between the reaction plate and the front cover. A method of forming a torque converter is also provided.

Abstract: A method of predicting the condition of a compressor with respect to rotating stall is disclosed. The method comprises the steps of: i) comparing the difference between the largest and smallest values of a variable occurring during a time period with a difference threshold, the variable at any given time being dependent on the compressor exit pressure at that time, and ii) predicting either that the compressor is in rotating stall or that the compressor is not in rotating stall in dependence upon the result of the comparison.

Abstract: A rotating liquid ring rotating casing gas turbine (10) has at least one liquid ring rotating casing (13) having an eccentrically mounted impeller (11) adapted to rotate within a surrounding liquid ring (14) so as to form chambers (15) of successively increasing volume between adjacent vanes of the impeller. A working fluid formed by high pressure gas is injected into the impeller where the chambers are narrow via a fluid inlet (19) within a static axial bore (23) of the impeller so as to rotate the impeller and in so doing the gas expands isentropically. A fluid outlet (20) within the static axial bore of the impeller and fluidly separated from the fluid inlet allows the working fluid to escape at low pressure and low temperature.

Abstract: A compressor housing may include a shroud portion which is axially spaced from an inlet portion and configured to at least partially surround the compressor wheel. The compressor housing may be further configured to include a recirculation cavity which is formed between an exterior surface of the shroud portion and an interior surface of the compressor housing. Furthermore, a recirculation slot may define an airflow pathway between the recirculation cavity and the compressor wheel. Additionally, the compressor housing may include an angled shroud support extending radially through the recirculation cavity from the exterior surface of the shroud portion to the interior surface of the compressor housing. The angled shroud support may be spaced an axial distance away from the recirculation slot to reduce turbulence in the airflow as the airflow moves from the recirculation cavity to the compressor wheel.

Abstract: A washing machine including a cabinet having an inlet port formed at a front panel for laundry insertion thereinto and a door to open or close the inlet port; a tub within the cabinet for storing wash water; a drum in communication with the inlet port, and rotatably provided within the tub; and a detergent dispenser provided below the inlet. The detergent dispenser includes a dispenser case having an opening portion on an upper surface thereof; and at least one of an automatic detergent supply unit and a manual detergent supply unit mounted at the dispenser case. The automatic detergent supply unit includes a container provided with an inlet port and an outlet port for storing liquid detergent; a container receiving portion to receive the container; and a pumping device to selectively discharge liquid detergent discharged from the outlet port of the container by a predetermined amount.

Abstract: A seal segment of a shroud arrangement for bounding a hot gas flow path within a gas turbine engine is described. The seal segment is upstream of a second component of the gas turbine engine relative to the hot gas flow path. The seal segment comprises: a plate having: a downstream trailing edge; an inboard side which faces the hot gas flow path when in use; an outboard side; and a first part of a two part seal attached on the outboard side, wherein a second part of the two part seal is attached to the second component such that in an assembled gas turbine engine the two part seal provides an isolation chamber which is in fluid communication with the hot gas flow path via the trailing edge of the plate. A gas turbine having the seal segment is also described.

Abstract: A shroud assembly for a turbine engine includes a shroud having a front side confronting the blades of a turbine and a back side opposite the front side, a hanger configured to couple the shroud to with casing of the turbine, a cooling conduit extending through the hanger to supply a cooling fluid stream to the back side of the shroud, and a particle separator having a through passage forming part of the cooling conduit and a scavenge conduit branching from the through passage.

Abstract: A fluid supply system for providing a turbomachine fluid to a component of a gas turbine engine is disclosed. The fluid supply system includes a fluid container, a moveable barrier, and an airbag. The moveable barrier fluidly divides the fluid container into a first portion and a second portion. The moveable barrier is moveable between a flow-permitting position and a flow-restricting position. The turbomachine fluid experiences a circulating flow between the component and the second portion of fluid container when the moveable barrier is in the flow-permitting position. The circulating flow is at least partially impeded by the moveable barrier when the moveable barrier is in the flow-restricting position. The airbag is positioned within the first portion of the fluid container. The airbag is selectively operable to move the moveable barrier from the flow-permitting position to the flow-restricting position.

Abstract: A method for controlling a power consumption of a group of a plurality of wind turbines, in particular of a wind park. The wind turbines are prepared for feeding electrical energy into an electrical supply network and an energy supply is offered to the wind turbines for consumption in a recurring cycle, in predetermined order successively, and subject to a total park energy supply available to the wind turbines for consumption, and the respective wind turbine reserves this or a smaller energy supply as a reference power, and subsequent wind turbines in the cycle are provided with, at most, the energy supply available to the wind park, reduced by the reference energy supply already reserved, as energy supply.

Abstract: A control system to optimize response time of a plurality of engines of a machine is provided. The control system includes a controller configured to determine a first engine group and a second engine group based on data regarding response time characteristics of the plurality of engines, control the first engine group to increase output power of the machine when the output power of the machine is below a predetermined power output threshold, and control the second engine group to increase output power of the machine responsive to the output power of the machine reaching the predetermined power output threshold. A response time of the first engine group is faster than a response time of the second engine group when the output power of the machine is below the predetermined power output threshold.

Abstract: A multi-stage radial turbine for usage in energy capture from fluid streams with low to moderate relative speed.

Abstract: Provided is a compressor control device configured to control a flow rate of a compressor having a plurality of impellers connected to an outlet port-side flow path in parallel and a flow rate regulation unit configured to regulate a flow rate of each of the impellers, the compressor control device including a pressure detection unit configured to detect a pressure of the outlet port-side flow path, a flow rate detection unit configured to detect the flow rate of each of the impellers, and a control unit configured to output a flow rate regulation command of each of the impellers to the flow rate regulation unit and control the flow rate regulation unit based on the detection result of the pressure detection unit.

Abstract: An apparatus for driving a load is provided. The apparatus comprises a multiple-shaft gas turbine comprising a high pressure compressor and a high pressure turbine drivingly connected to one another by a first gas turbine shaft and a low pressure compressor and a power turbine drivingly connected to one another by a second gas turbine shaft extending coaxial with the first gas turbine shaft, the high pressure compressor and the high pressure turbine. The apparatus also comprises a load coupling drivingly connecting the power turbine to the load and a dual-speed turning gear with an output shaft drivingly engageable to and disengageable from the load, the dual-speed turning gear comprising a low speed turning motor and a high speed turning motor, wherein the low speed turning motor and the high speed turning motor are configured to selectively drive the load.

Abstract: An operation control system for a wind farm having wind turbines includes: a remaining-lifetime estimation unit for estimating remaining lifetime of a component of each wind turbine; a sales-income estimation unit for estimating, for each wind turbine, an income from sales of electric power under a plurality of output control conditions; a maintenance-cost estimation unit for estimating, for each wind turbine, maintenance cost based on the remaining lifetime of the component under each of the plurality of power limit conditions; a power-limit-condition selection unit for selecting, for each wind turbine, a power limit condition that maximizes income obtained from the wind farm, based on the income from sales of electric power and the maintenance cost estimated for each wind turbine under each of the power limit conditions; and an operation command unit for sending an operation command to each wind turbine based on the selected power limit condition.

Abstract: The centrifugal compressor (1) includes: an impeller (3); and a casing (2) accommodating the impeller (3). The casing (2) includes: an inlet (6); an impeller-accommodating portion (14) in which the impeller (3) is disposed; an annular chamber (11) formed around the inlet (6); a downstream groove (13) communicating a downstream end portion of the annular chamber (11) with the impeller-accommodating portion (14); and an upstream groove (12) communicating an upstream end portion of the annular chamber (11) with the inlet (6). In addition, the downstream groove (13) is provided in a predetermined range in a circumferential direction of the impeller (3) so as to communicate with a high-pressure part to occur in part of the impeller-accommodating portion (14), and the upstream groove (12) is provided over the entire circumference of the inlet (6).

Abstract: A blade outer air seal (BOAS) assembly for an engine case of a gas turbine engine includes a multiple of supported air seal segments and a multiple of floating air seal segments circumferentially alternate with the multiple of supported air seal segments.

Abstract: A steam turbine includes a boiler unit, first supply pipes, a second supply pipe, a plurality of valve units, a drain valve unit, and a controller. The controller is configured to control, before rotation of the turbine starts, an operation time and temperature of the auxiliary boiler so that the temperatures of the high-pressure turbine and the intermediate-pressure turbine are increased to the first setting temperature. The controller is configured to control, when the temperatures of the high-pressure turbine and the intermediate-pressure turbine are maintained at the first setting temperature, operation of the main boiler such that the temperature of the intermediate-pressure turbine reaches a second setting temperature while operation of the auxiliary boiler is interrupted, and control, when the temperature of the intermediate-pressure turbine is maintained at the second setting temperature, the operation of the main boiler such that steam is supplied only to the high-pressure turbine.