38results about "Supersonic fluid pumps" patented technology

The invention provides a supercritical carbon dioxide compressor performance evaluation method which can be applied to the technical field of compressors. The method comprises the following steps: acquiring total enthalpy and theoretical sound velocity from a physical property database according to total temperature and total pressure under the condition that the compressor operates in an inlet working condition; according to the total temperature, the total pressure, the total enthalpy, the theoretical sound velocity and a given axial Mach number, determining an iterative sound velocity from a physical property database; under the condition that a first error between the iteration sound velocity and the theoretical sound velocity is larger than a first preset threshold value, the theoretical sound velocity is updated to the iteration sound velocity, the steps are executed repeatedly till the first error is smaller than the first preset threshold value, and the target sound velocity is obtained; based on the target sound velocity, determining mass flow and rotating speed; fluid simulation is conducted on the compressor through the mass flow and the rotating speed, and performance parameters are obtained; and the performance of the compressor is evaluated through the incidence relations corresponding to the multiple sets of different inlet working condition parameters.

A rotary apparatus for inputting thermal energy into fluidic medium is provided, the apparatus is being configured to impart an amount of thermal energy to a stream of fluidic medium directed along a flow path formed inside the casing between the inlet and the outlet by virtue of a series of energy transformations occurring when said stream of fluidic medium successively passes through the blade / vane rows formed by the nozzle guide vanes, the rotor blades and the diffuser vanes, respectively. A space formed between an exit from the at least one row of diffuser vanes and an entrance to the at least one row of nozzle guide vanes in a direction of the flow path formed inside the casing between the inlet and the outlet is made variable to regulate the amount of thermal energy input to the stream of fluidic medium propagating through the apparatus.

The invention relates to a stator component (20) comprising: a platform (22); a blade (24, 26) having a maximum radian (526); a fin (28) extending from a root (44) to a head (46), the head (46) extending from a leading edge (31) to a trailing edge (37), the fin (28) and the blades (24, 26) being designed such that:-a maximum radian (526) is located between the leading edge (31) and the trailing edge (37),-a ratio of a distance between the maximum radian (526) and the leading edge (31) to a chord length (54) is between 5% and 95%, and-the fin head defining a recess (45), the recess extends on both sides of the maximum radian (526) with a recess length (47) that is less than or equal to 20% of the chord length (54).

A turbomachine is provided that is configured for using a fluid for cooling and sealing functions conducted by a fluid transport pipe (216) with a hollow wall portion sealed to maintain a vacuum therein for thermally isolating the sealing fluid flowing though the fluid transport pipe (216) from an environment external to the fluid transport pipe (216).

A supersonic diffuser for use in turbomachinery adapted to impart thermal energy to a process fluid is provided. The diffuser includes a vaned zone configured to define a passageway having a flow area to pass a flow of a process fluid at supersonic velocity. The vaned zone is configured to define a step-change to the flow area of the passageway at a given location, such as where the flow of the process fluid exits the vaned zone. The diffuser further includes a shock zone coupled to the vaned zone to pass the flow of the process fluid that exits the vaned zone. The shock zone is configured to support a system of shock waves that increases static temperature of the process fluid downstream of the system of shock waves. A mixing and subsonic diffusion is configured to decelerate process fluid from the shock zone to a reduced subsonic speed prior to discharge of the process fluid through an exit of the diffuser.

The invention discloses a high-vacuum supersonic turbine vacuum pump and relates to the technical field of vacuum pumps, the high-vacuum supersonic turbine vacuum pump comprises a pump shell, a motor and a third frame component, a first plate is mounted at the top of the pump shell, a controller component is mounted on the front face of the first plate, the motor is mounted on one side of the pump shell, and a rotating rod is mounted at the output end of the motor; and a rotating pipe is installed on the outer side of the rotating rod, a plurality of impellers are installed on the outer side of the rotating pipe, a third frame component is installed on the front face of the pump shell, the third frame component communicates with the pump shell, a plurality of fourth electric telescopic rod components are installed on the front face of the third frame component, and second brushes are installed at the output ends of the fourth electric telescopic rod components. An annular brush moves rightwards to scrape off dust on the inner wall of the pump shell part and push the dust to a waste opening, then a second baffle moves upwards, a second brush moves backwards to make contact with an impeller, then the impeller rotates slowly, and therefore the second brush brushes off dust on the impeller.

The present disclosure concerns a rotary apparatus (100) configured for inputting thermal energy (heat) into fluids by having fluidic stream repeatedly propagated through rotating and stationary components arranged inside said rotary apparatus in accordance with essentially helical trajectory. The rotary apparatus (100) comprises two or more rotor blade cascades (R1, R2) coaxially arranged on one or more rotor shaft(s), and at least two stationary vane cascades arranged upstream of a first rotor blade cascade (R1) and downstream of a rearmost rotor blade cascade (R2), respectively. In operation, fluid, such as gas, is heated inside the rotary apparatus while repeatedly passing through cascades S1-R1-R2-S2 in accordance with essentially helical trajectory. The rotor blade cascades can be configured to rotate in co- and counter directions and / or with the same or different speed. In some configurations the apparatus further comprises a flow turn cascade (FTC) configured as a stationary vane cascade arranged between successive coaxial rotor blade cascades (R1, R2). Related method for thermally treating fluids is further provided.

A rotary apparatus (100) for inputting thermal energy into fluids and for recycling thus heated fluids is provided, comprising: a rotor with at least one row of rotor blades arranged over a circumference of a rotor hub mounted on a rotor shaft and forming at least one rotor blade cascade, respectively, and a plurality of stationary vanes arranged into at least one stationary vane cascade adjacent to said at least one rotor blade cascade, wherein the rotor and the plurality of stationary vanes are enclosed in a duct formed in a casing between at least one inlet and at least one outlet. The rotary apparatus is configured to heat fluids flowing in the duct between at least one inlet and at least one outlet by virtue of series of energy transformations occurring when said fluid successively passes through rotating and stationary blades / vanes, whereby a stream of heated fluid is generated, and to recycle at least a part of thus heated fluid by means of a fluid circulation arrangement (10) configured to return a part of heated fluid into a duct region between at least one inlet and at least one rotor blade cascade. Recycling may be internal (Recycle route I) or external (Recycle route II).

A compressor (1000) for processing a CO2 flow; a first compressor stage (200) having a first row of blades (250) with a first number of blades and a second compressor stage (300) downstream of the first compressor stage (200) having a second row of blades (350) with a second number of blades; the number of blades of the first compressor stage (200) being smaller than the number of blades of the second compressor stage (300); there being an annular gap (400) between the first row of blades (250) and the second row of blades (350); the first compression stage (200) being designed to ensure that the CO2 flow is in a supercritical state at its outlet, preferably close to the critical point of CO2, and such that the second compressor stage (200) processes CO2 in a supercritical state.

A supersonic diffuser for use in turbomachinery adapted to impart thermal energy to a process fluid is provided. The diffuser includes a vaned zone configured to define a passageway having a flow area to pass a flow of a process fluid at supersonic velocity. The vaned zone is configured to define a step-change to the flow area of the passageway at a given location, such as where the flow of the process fluid exits the vaned zone. The diffuser further includes a shock zone coupled to the vaned zone to pass the flow of the process fluid that exits the vaned zone. The shock zone is configured to support a system of shock waves that increases static temperature of the process fluid downstream of the system of shock waves. A mixing and subsonic diffusion is configured to decelerate process fluid from the shock zone to a reduced subsonic speed prior to discharge of the process fluid through an exit of the diffuser.

A rotary apparatus for inputting thermal energy into fluids and for recycling thus heated fluids is provided, comprising: a rotor with at least one row of rotor blades arranged over a circumference of a rotor hub mounted on a rotor shaft and forming at least one rotor blade cascade, respectively, and a plurality of stationary vanes arranged into at least one stationary vane cascade adjacent to said at least one rotor blade cascade, wherein the rotor and the plurality of stationary vanes are enclosed in a duct formed in a casing between at least one inlet and at least one outlet. The rotary apparatus is configured to heat fluids flowing in the duct between at least one inlet and at least one outlet by virtue of series of energy transformations occurring when said fluid successively passes through rotating and stationary blades / vanes, whereby a stream of heated fluid is generated, and to recycle at least a part of thus heated fluid by means of a fluid circulation arrangement configured to return a part of heated fluid into a duct region between at least one inlet and at least one rotor blade cascade. Recycling may be internal or external.

The compressor is used for processing a CO2 flow; a first compressor stage has a first row of blades with a first number of blades and a second compressor stage, downstream the first compressor stage, has a second row of blades with a second number of blades; the number of blades of the first compressor stage is less than the number of blades of the second compressor stage; there is an annular gap between the first row of blades and the second row of blades; the first compression stage (200) is designed so to assure that the CO2 flow is in supercritical condition, preferably close to CO2 critical point, at its outlet, and so that the second compressor stage process CO2 in supercritical condition.

A rotary apparatus (100) for inputting thermal energy into fluids and for recycling thus heated fluids is provided, comprising: a rotor with at least one row of rotor blades arranged over a circumference of a rotor hub mounted on a rotor shaft and forming at least one rotor blade cascade, respectively, and a plurality of stationary vanes arranged into at least one stationary vane cascade adjacent to said at least one rotor blade cascade, wherein the rotor and the plurality of stationary vanes are enclosed in a duct formed in a casing between at least one inlet and at least one outlet. The rotary apparatus is configured to heat fluids flowing in the duct between at least one inlet and at least one outlet by virtue of series of energy transformations occurring when said fluid successively passes through rotating and stationary blades / vanes, whereby a stream of heated fluid is generated, and to recycle at least a part of thus heated fluid by means of a fluid circulation arrangement (10) configured to return a part of heated fluid into a duct region between at least one inlet and at least one rotor blade cascade. Recycling may be internal (Recycle route I) or external (Recycle route II).

There is provided a method of inputting thermal energy into a fluid medium in a manufacturing process by at least one rotating apparatus, the rotating apparatus comprising: a housing having at least one inlet and at least one outlet; a rotor comprising at least one row of rotor blades arranged on the circumference of a rotor hub mounted to a rotor shaft; and a stator configured as an assembly of fixed vanes disposed at least upstream of the at least one row of rotor blades. In the method, an amount of thermal energy is imparted to a flow of fluid medium directed along a flow path formed inside a housing between an inlet and an outlet by means of a series of energy conversions occurring when the flow of fluid medium passes through a fixed guide vane and at least one row of rotor blades, respectively. The method further comprises integrating the at least one rotating device into a production facility configured to perform a material production process, such as the production of titanium oxide, mineral wool, gypsum, wood pulp and paper, cathodes and anodes, or flash drying of chemicals at temperatures substantially equal to or exceeding 500 degrees Celsius (DEG C), such as the production of titanium oxide, mineral wool, gypsum, wood pulp and paper, cathodes and anodes. And conducting an amount of input energy into at least one rotating device integrated into the heat consuming process facility, the input energy including electrical energy. A rotating apparatus and related uses thereof are also provided.

A stator assembly including an upstream blade and a downstream blade axially overlapping and defining between them a channel. The inlet surface of the channel is greater than or equal to the outlet surface of the channel, preferably with a factor of 2. A turbomachine provided with such an assembly, arranged upstream of a high-pressure compressor.

The present disclosure relates to a transonic compressor (24) of a turbine (2), comprising exactly two or exactly three annular rows of rotor blades (40, 44) and exactly one or exactly two annular rows of intermediate stator blades (41) between the respective two rows of rotor blades (40, 44), wherein the flow velocity of the rotor (44) downstream of the intermediate stator blades (41) is less than or equal to Mach number 0.9 over a radial portion of the blade (44) extending over the radially inner 40% of the blade (44), less than or equal to Mach number 1 over a radial portion extending over the radially inner 80% of the blade (44), and less than or equal to Mach number 1.05 over a radial portion extending over the radially outer 20% of the blade (44).

The compressor (1000) is used for processing a CO2 flow; a first compressor stage (200) has a first row of blades (250) with a first number of blades and a second compressor stage (300), downstream the first compressor stage (200), has a second row of blades (350) with a second number of blades; the number of blades of the first compressor stage (200) is less than the number of blades of the second compressor stage (300); there is an annular gap (400) between the first row of blades (250) and the second row of blades (350); the first compression stage (200) is designed so to assure that the CO2 flow is in supercritical condition, preferably close to CO2 critical point, at its outlet, and so that the second compressor stage (200) process CO2 in supercritical condition.

The application provides a compressor impeller assembly and a shock wave compressor, and belongs to the technical field of gas compression. The compressor impeller assembly comprises a compression impeller, a centrifugal impeller and a main shaft. The compression impeller is provided with a speed reduction air channel, the speed reduction air channel extends from the outer edge of the compression impeller to the shaft hole, the airflow direction of the speed reduction air channel is opposite to the rotation direction of the compression impeller, the speed reduction air channel is used for supplying the high-speed airflow after shock wave compression to enter the speed reduction air channel from the outer edge of the compression impeller to slow down, and high-pressure airflow is formed at the shaft hole of the compression impeller. The centrifugal impeller is coaxial with the compression impeller and abuts against the compression impeller. The centrifugal impeller is provided with a speed increase air channel, the speed increase air channel extends from the shaft hole of the centrifugal impeller to the outer edge, and is used for supplying the high-pressure airflow to enter the speed increase air channel from the shaft hole of the centrifugal impeller and to be thrown out from the outer edge of the centrifugal impeller. The application realizes two-stage compression through the compression impeller and the centrifugal impeller, so that the industrial gas demand is met.

An ABMP compressor is introduced, which is a tip axial flow compressor technology, and aims to reform gas turbine jet engines and be applied in various fields. The innovation focuses on optimization of the compression ratio and maximization of energy extraction, and efficient operation under various conditions is ensured. The ABMP compressor is adaptive, allowing strategic adjustments to peak performance. The system adheres to environmental responsibility and supports sustainable fuel and clean energy advocation. Seamless integration of it with a turbofan engine enhances performance and reduces vibrations in gas turbine jet engines and other applications. To prevent operation interruption, the compressor reduces compression stall and surge, and improves stable combustion efficiency through uniform fuel distribution and stable flame front. With extended operational limits, reduced wear, and enhanced overall system performance, the ABMP compressor marks a revolutionary solution to the continual development of the propulsion system.

The present disclosure concerns a rotary apparatus (100) configured for inputting thermal energy (heat) into fluids by having fluidic stream repeatedly propagated through rotating and stationary components arranged inside said rotary apparatus in accordance with essentially helical trajectory. The rotary apparatus (100) comprises two or more rotor blade cascades (R1, R2) coaxially arranged on one or more rotor shaft(s), and at least two stationary vane cascades arranged upstream of a first rotor blade cascade (R1) and downstream of a rearmost rotor blade cascade (R2), respectively. In operation, fluid, such as gas, is heated inside the rotary apparatus while repeatedly passing through cascades S1-R1-R2-S2 in accordance with essentially helical trajectory. The rotor blade cascades can be configured to rotate in co- and counter directions and / or with the same or different speed. In some configurations the apparatus further comprises a flow turn cascade (FTC) configured as a stationary vane cascade arranged between successive coaxial rotor blade cascades (R1, R2). Related method for thermally treating fluids is further provided.

A rotary device (100) for inputting thermal energy to a fluid medium is provided, the device comprising: a casing (20) with at least one inlet (11) and at least one outlet (12); a rotor including at least one row of rotor blades (3) configured as impulse impeller blades arranged around the entire circumference of a rotor hub (3a) assembled on a rotor shaft (1); at least one stationary nozzle guide vane (2), each disposed upstream of the at least one row of rotor blades; and at least one stationary diffuser vane row (4), each disposed downstream of the at least one row of rotor blades. The device is configured to impart a quantity of thermal energy to a fluid medium flow guided along a flow path formed inside a casing between an inlet and an outlet by a series of energy transformations occurring as said fluid medium flow passes successively through the blade / vane rows formed by the nozzle guide vanes (2), the rotor blades (3) and the diffuser vanes (4), respectively, in which a space (5) formed between an outlet from at least one diffuser vane row (4) and an inlet to at least one nozzle guide vane row (2) in the direction of the flow path formed inside a casing (20) between an inlet (11) and an outlet (12) is variable to adjust the input of thermal energy to the fluid medium flow propagating through the device. Related uses and methods for inputting thermal energy into a fluid medium are further provided.

A rotary apparatus (100) for inputting thermal energy into fluidic medium is provided, the apparatus comprises: a casing (20) with at least one inlet (11) and at least one outlet (12); a rotor comprising at least one row of rotor blades (3) configured as impulse impeller blades arranged over a circumference of a rotor hub (3a) mounted onto a rotor shaft (1); at least one row of stationary nozzle guide vanes (2) arranged upstream of the at least one row of the rotor blades, respectively; and at least one row of stationary diffuser vanes (4) arranged downstream of the at least one row of the rotor blades, respectively. The apparatus is configured to impart an amount of thermal energy to a stream of fluidic medium directed along a flow path formed inside the casing between the inlet and the outlet by virtue of a series of energy transformations occurring when said stream of fluidic medium successively passes through the blade / vane rows formed by the nozzle guide vanes (2), the rotor blades (3) and the diffuser vanes (4), respectively, wherein, in said apparatus, a space (5) formed between an exit from the at least one row of diffuser vanes (4) and an entrance to the at least one row of nozzle guide vanes (2) in a direction of the flow path formed inside the casing (20) between the inlet (11) and the outlet (12) is made variable to regulate the amount of thermal energy input to the stream of fluidic medium propagating through the apparatus. Related uses and a method for inputting thermal energy into a fluidic medium are further provided.

A supersonic diffuser is provided for a turbine adapted to transfer thermal energy to a process fluid. The diffuser includes a vane region configured to define a channel having a flow area through which the process fluid flow passes at supersonic velocities. The vane region is configured to define a step change in the flow area of the channel at a given location, such as at a location where the process fluid flow exits the vane region. The diffuser further includes an impingement region coupled to the vane region to pass the process fluid stream exiting the vane region. The shockwave zone is configured to support a shockwave system that increases a static temperature of the process fluid downstream of the shockwave system. The mixing and subsonic diffusion zone is configured to decelerate the process fluid from the impingement zone to a reduced subsonic velocity before the process fluid is discharged through the outlet of the diffuser.

A stator assembly including an upstream blade and a downstream blade axially overlapping and defining between them a channel. The inlet surface of the channel is greater than or equal to the outlet surface of the channel, preferably with a factor of 2. A turbomachine provided with such an assembly, arranged upstream of a high-pressure compressor.

The present disclosure concerns a rotary apparatus (100) configured for inputting thermal energy (heat) into fluids by having fluidic stream repeatedly propagated through rotating and stationary components arranged inside said rotary apparatus in accordance with essentially helical trajectory. The rotary apparatus (100) comprises two or more rotor blade cascades (R1, R2) coaxially arranged on one or more rotor shaft(s), and at least two stationary vane cascades arranged upstream of a first rotor blade cascade (R1) and downstream of a rearmost rotor blade cascade (R2), respectively. In operation, fluid, such as gas, is heated inside the rotary apparatus while repeatedly passing through cascades S1-R1-R2-S2 in accordance with essentially helical trajectory. The rotor blade cascades can be configured to rotate in co- and counter directions and / or with the same or different speed. In some configurations the apparatus further comprises a flow turn cascade (FTC) configured as a stationary vane cascade arranged between successive coaxial rotor blade cascades (R1, R2). Related method for thermally treating fluids is further provided.

To provide a non-sealed vacuum pump with a supersonically rotatable bladeless gas impingement surface.SOLUTION: A vacuum pump 10 generally comprises low-pressure and high-pressure portions separated by a gas impermeable partition. Gas molecules exit the low-pressure portion through an opening in the partition and passively impinge on a featureless rotatable surface 15 in the high-pressure portion. A driver 16 rotates the rotatable surface with tangential velocity in the supersonic range at multiple times the most probable velocity of the impinging gas molecules. The impinging gas molecules are ejected outwardly from the periphery of the rotatable surface generating a substantial net outward flow of gas and reducing the pressure in the low-pressure portion.SELECTED DRAWING: Figure 4

A method for thermal or thermochemical conversion of ammonia or methanol feedstocks into hydrogen (gas) in a related feedstock conversion facility (1000) is provided. The method comprises generating heated fluidic medium by at least one rotary apparatus (100), supplying a stream of thus generated heated fluidic medium into the feedstock conversion facility (1000), and operating said at least one rotary apparatus (100) and said feedstock conversion facility (1000) to carry out thermal or thermochemical conversion of the ammonia or methanol feedstocks into hydrogen at temperatures essentially equal to or exceeding about 500 degrees Celsius (°C). Facility (1000, 1000A) for production of hydrogen from ammonia or methanol feedstocks is further provided.

Introducing the ABMP Compressor, a cutting-edge axial flow compressor technology set to transform gas turbine jet engines and find applications across various domains. Our innovation focuses on optimizing compression ratios and maximizing energy extraction, ensuring efficient operation in diverse conditions. The ABMP Compressor offers adaptability, allowing strategic adjustments for peak performance. Embracing environmental responsibility, it supports sustainable fuels and cleaner energy initiatives. Its seamless integration with turbofans enhances performance and reduces vibrations in gas turbine jet engines and other applications. Engineered to prevent operational disruptions, the compressor mitigates compression stall and surge, promoting stable combustion efficiency with uniform fuel distribution and stable flame fronts. With extended operational limits, reduced wear and tear, and overall system-wide performance enhancement, the ABMP Compressor signifies a transformative solution in the evolving landscape of propulsion systems.

The present disclosure relates to a rotating apparatus (100) configured for inputting thermal energy (heat) into a fluid by repeatedly flowing a fluid flow according to a substantially helical trajectory through a rotating part and a stationary part arranged inside the rotating apparatus. The rotating device (100) comprises two or more rotor blade cascades (R1, R2) arranged coaxially on one or more rotor shafts and at least two fixed guide vane cascades arranged upstream of a first rotor blade cascade (R1) and downstream of a last rotor blade cascade (R2), respectively. In operation, a fluid, such as a gas, is heated inside the rotating apparatus while repeatedly passing through the cascade S1-R1-R2-S2 according to a substantially helical trajectory. The rotor blade cascade may be configured to rotate in the same and opposite directions and / or at the same or different speeds. In some configurations, the apparatus further includes a flow diverting cascade (FTC) configured as a fixed guide vane cascade disposed between coaxial rotor blade cascades (R1, R2) disposed in succession. Related methods for thermally treating fluids are also provided.