342 results about "Centrifugal compressor" patented technology

The invention discloses a method for calculating the strength of an end face tooth coupling of an energy storage centrifugal compressor, relates to a method for calculating the strength of an end face tooth coupling, and aims to solve the problem that a method for accurately judging whether the strength of the end face tooth coupling of the compressor is qualified or not by a conventional end face tooth calculation and checking method does not exist at present. The method is implemented according to the following steps that firstly, axial component force generated when the end face teeth transmit torque is obtained; 2, the axial expansion difference of the end face teeth, the main shaft and the screw at the working temperature is calculated, and the actual pre-tightening force of the screw during unit operation is calculated; 3, impeller thrust generated by the front and back pressure difference of the impeller is calculated, the effective tooth surface area of the end face teeth is calculated, and the end face tooth root bending stress, the end face tooth maximum extrusion stress and the end face tooth axial tensioning force safety coefficient of the centrifugal compressor are calculated; and 4, judging the strength of the end face tooth coupling of the energy storage centrifugal compressor. The invention belongs to the field of end face tooth coupling checking.

The invention relates to a centrifugal compressor high-altitude environment dynamic simulation test system. The system comprises a compressor test module; the high-altitude environment simulation module comprises an air inlet surge tank, an air inlet assembly and a first air exhaust assembly which are arranged at the upstream of the air inlet pipeline, and an air exhaust surge tank and a second air exhaust assembly which are arranged at the downstream of the air exhaust pipeline; a measurement module; the control module is used for comparing the first actually-measured pressure value with a target altitude pressure value of the air inlet end and controlling the air inlet amount of the air inlet assembly and the air suction amount of the first air suction assembly according to a comparison result, so that the pressure of the air inlet pressure stabilizing tank is stabilized at the target altitude pressure of the air inlet end; and the control module compares the second actually measured pressure value with the target altitude pressure value of the exhaust end, and controls the air suction amount of the second air suction assembly according to the comparison result, so that the pressure of the exhaust surge tank is stabilized at the target altitude pressure value of the exhaust end. It is ensured that test data can truly reflect the actual plateau working condition performance of the gas compressor.

The invention discloses an intelligent load distribution system and method for a centrifugal compressor unit. The system comprises a data sensing module, an intelligent decision-making module, an instruction execution module and a model updating module. The method comprises the steps that operation parameters of multiple parallel centrifugal compressors are synchronously collected in a high-precision mode through an industrial real-time network supporting hardware timestamps, and time-aligned system state observation data are obtained; constructing a state vector based on the data and a load prediction result, inputting a deep reinforcement learning agent fused with compressor physical characteristic constraints, and generating a load distribution instruction and a unit start-stop suggestion; after safety boundary verification is conducted on the original action, the guide vane opening degree is adjusted through a feedforward speed planning and fuzzy self-adaption PID composite servo control algorithm, and starting and stopping operation is executed; meanwhile, empirical data are collected online, and model parameters are periodically and finely adjusted. According to the invention, efficient, safe, accurate and self-evolution compressor group control is realized.

A turbocharger heat management structure relates to the technical field of internal combustion engine supercharging devices and comprises a radial flow turbine, a centrifugal compressor and a bearing system which are connected, and the heat management structure is arranged between the radial flow turbine and the bearing system. The heat management structure comprises a first heat insulation cover, a second heat insulation cover and a third heat insulation cover which are in a revolving body metal sheet shape and arranged at the turbine back disc, a first heat insulation cavity is formed between the first heat insulation cover and the second heat insulation cover, a second heat insulation cavity is formed between the second heat insulation cover and the third heat insulation cover, and a third heat insulation cavity is formed between the third heat insulation cover and the annular cooling groove. The first heat insulation cavity communicates with a gap in the turbine back disc, and the third heat insulation cavity is connected with a cold air hole. The third heat insulation cavity, the second heat insulation cavity and the first heat insulation cavity are sequentially communicated through an air guide structure. On the premise that the weight and the size are not greatly increased, the heat insulation efficiency is greatly improved, and the purpose of actively and efficiently cooling a key area is achieved.

A steam compressor, specifically a multistage centrifugal compressor which could have an operating pressure between 0.2 bar and 12 bar and be used in industrial processes with heat pumps or for the mechanical compression of steam in general.The present invention is to improve the state of the art for steam compressors by means of an optimized architecture that minimizes the manufacturing cost, such that it makes it comparable to that of a fan, without compromising its typical performance.

This utility model discloses a centrifugal compressor main shaft structure, including an impeller with a central through-hole mounting hole. A main shaft body is fitted inside the mounting hole. The end face of the impeller has a coaxial mounting groove. A flange is fixedly connected to the mounting groove by a first bolt. The flange is fixedly fitted onto the outer edge of the main shaft body. A cavity is provided inside the main shaft body, and a fastener is slidably connected within the cavity. The outer edge of the fastener abuts against a fixing member, which slidably passes through the cavity and is inserted into the mounting hole. This utility model replaces the traditional spline connection with a composite fixing method of flange bolt connection and insert-slot locking, significantly reducing the requirements for the machining accuracy of the main shaft and impeller inner holes, while avoiding the stringent limitations of heat treatment processes, thus significantly reducing processing difficulty and manufacturing costs.

The invention discloses a full-dynamic-pressure turbine type low-temperature refrigerating device and method. The device comprises a two-stage centrifugal compressor, a heat exchanger, a low-temperature turbine expander, a gas storage tank, a filter, a valve, a water cooling machine and a cold using device. Closed circulation is adopted in the device, and the whole device is integrated into a skid-mounted device to output cooling capacity outwards. The device adopts a full-dynamic-pressure turbine type structure and is supported by a gas bearing; the low-temperature turbine expander and the low-temperature heat exchanger are in a heat insulation environment; the low-temperature turbo expander adopts pressurization braking or fan braking; a three-stage integrated heat exchanger or a separated heat exchanger is adopted for skid-mounting; the skid-mounted system comprises a charging mode and a non-charging mode. The whole device runs without oil, and is clean and environment-friendly; the integration level of the system is greatly improved through the three-stage integrated heat exchanger and the skid-mounted structure; different braking modes are set, so that the applicability of the device is improved; the refrigerating temperature and the refrigerating capacity can be accurately controlled through the full-pressurization mode, the partial-pressurization mode and the bypass valve.

The utility model discloses a centrifugal compressor cylinder body boring device with fixed establishment, specifically related to boring device technical field, including the bed and the processing platform, the front end of bed top is installed with processing platform, the back of processing platform top is provided with fixed subassembly, the fixed subassembly includes the clamping station, screw rod, second motor, screw sleeve, sliding slot, sliding block, movable platform and the clamping plate, the back of processing platform top is installed with the clamping station. The utility model discloses be provided with the clamping station and the clamping plate, two sets of clamping station, the clamping station symmetrical distribution is in the back position of processing platform top, when starting second motor drive screw rod and rotating, screw rod and screw sleeve cooperation, can drive the clamping plate of front end and each other close, along with compressor casing and place on the processing platform and place, two sets of clamping plate are clamped in the both sides of compressor casing, can assist to the fixed processing of compressor casing, has realized the supplementary clamping function of this boring device when using.

Integrally geared centrifugal compressor systems are described that include eccentric cartridges that house bearings and seals to maintain rotor concentricity for a variety of pinons integrated in a fixed gearbox design to provide multiple impeller speeds with a single gearbox design. In an aspect, a system includes, but is not limited to, a pinion configured to be rotated by a bull gear about a rotational axis; a rotor coupled to the pinion; and an eccentric cartridge configured to house a bearing assembly through which the rotor extends to support rotation of the rotor, the eccentric cartridge having an outer surface and an inner surface, wherein the inner surface is eccentric relative to the outer surface to align the rotational axis with a center axis of the bearing assembly.

The invention discloses a supercritical CO2 centrifugal compressor and turbine performance test combined test bench system and method. The device is mainly composed of a compressor, a turbine, an electric heater, a cooler, a surge tank, a CO2 storage tank, valves and pipelines, a motor drives the compressor through a gearbox and is connected with a rotating shaft of the turbine through a clutch, and a main circulation loop is sequentially connected with the compressor, the turbine, the cooler, the surge tank and the electric heater in series. Through cooperation of bypass valve switching, clutch separation and reunion and a system control strategy, seamless switching of five test modes can be achieved without shutdown or pipeline disassembly and assembly, and the five test modes comprise a turbine connection and independent compressor performance test, a turbine performance test and a key component performance test. And a complete supercritical CO2 Brayton cycle system stable operation and control strategy verification test is carried out. The system has the characteristics of high efficiency and high test continuity, and provides a multifunctional and low-cost comprehensive test platform for research and development of a supercritical CO2 power device.

A housing 1 for a centrifugal compressor 40 with a centrifugal impeller 42 has a front cover 2. The front cover 2 defines a central axis 6 and has an axially oriented inlet 8, a diffuser 10 in fluid connection with the inlet 8, a collector 12 in fluid connection with the diffuser 10, and a rear cover opening which is opposite of the inlet 8 and designed to sealingly receive a rear cover 4. The diffuser has a first diffuser wall 30 and the collector has a collector wall 15. The front cover 2 is made of a three-dimensionally shaped base 22 and a separate disk-shaped diffuser wall part 24 which is attached to the three-dimensionally shaped base 22 for forming the diffuser 10 and the collector 12.

The invention relates to a centrifugal compressor energy-saving operation optimization method, in particular to a centrifugal compressor energy-saving operation optimization method based on multi-factor contribution degree analysis. The technical problems that in existing energy-saving operation optimization, the energy-saving effect is not stable, influence factors cannot be accurately adjusted, and efficiency is low are mainly solved. The method comprises the following steps: step 1, data preparation; 2, establishing an energy consumption prediction model; 3, real-time data acquisition and residual calculation are carried out; 4, performing quantitative analysis on the contribution degree of the influence factors; and 5, generating optimization guidance. According to the method, simple energy efficiency judgment is exceeded, quantitative traceability of the energy efficiency deviation source is achieved, and the fuzzy problem of high energy consumption is converted into the specific and operable problem of which parameter is not effective.

The invention relates to the technical field of mixed refrigerant centrifugal compressors, and discloses a recovery system for primary leakage gas of sealing gas of a mixed refrigerant compressor, which comprises a compressor, a leaked gas collecting device and a leaked gas recycling device, the leaked gas collecting device comprises a low-pressure end sealing gas collecting device, a high-pressure end sealing gas collecting device, a valve pipeline system and a gas storage tank; the leaked gas recycling device comprises an ejector. According to the scheme, high-pressure leaked gas at the high-pressure end of the compressor drives low-pressure leaked gas at the low-pressure end of the compressor to enter the gas storage tank, high-pressure gas at the high-pressure side of the compressor drives leaked gas of the gas storage tank through the ejector to enter a pipeline at the low-pressure side of the compressor for recycling, so that environmental pollution is reduced, and the use safety is improved; and the maintenance and operation cost of enterprises is reduced.

A centrifugal compressor (10, 50) for a fuel cell system, comprising: a compressor housing (11, 51, 105), a compressor shaft (12), and a bearing arrangement comprising an axial foil bearing (15), wherein the compressor shaft (12) is axially mounted in the compressor housing (11, 51, 105) via the axial foil bearing (15), wherein the compressor housing (11, 51, 105) comprises at least one integrally formed first cooling channel (25, 53, 102) and wherein the axial foil bearing (15) comprises a bearing disk (17, 52, 108) having at least one integrally formed second cooling channel (28, 54, 103, 104) for supplying cooling air for the axial foil bearing (15), wherein the first cooling channel (25, 53, 102) is in fluidic contact with the second cooling channel (28, 54, 103, 104) such that cooling air flows from the first cooling channel (25, 53, 102) to the second cooling channel (28, 54, 103, 104).

Embodiments of the present disclosure provide a centrifugal compressor fault diagnosis method, device and equipment. The method comprises: acquiring a current vibration signal of a centrifugal compressor to be diagnosed; extracting a current fault characteristic parameter of the current vibration signal based on a linear transformation time-frequency analysis method; acquiring a pre-stored fault characteristic sample library; and performing analogy analysis on the current fault characteristic parameter and the fault characteristic sample library to determine a fault type of the centrifugal compressor. In this way, the current fault characteristic parameter and the fault characteristic sample library can be automatically subjected to analogy analysis, so as to accurately and quickly locate the fault type of the centrifugal compressor. Since this fault analysis method does not require model training, the fault analysis result is not affected by the model precision, and the algorithm is simple to use, so the identification accuracy of the fault type of the centrifugal compressor can be ensured.

This utility model discloses an energy-saving compressed air supply system, including a centrifugal compressor unit with a first flow rate adjustment range; a variable frequency screw compressor unit with a second flow rate adjustment range; a compression heat regeneration adsorption drying system, the inlet of which is connected to the outlet of the centrifugal compressor unit; a freeze drying system, the inlet of which is connected to the outlet of the variable frequency screw compressor unit; a main air supply pipe, the outlets of the compression heat regeneration adsorption drying system and the freeze drying system are both connected to the main air supply pipe; and a monitoring and control system, including a pressure sensor, a flow meter, and a controller. Its advantages include the ability to achieve wide-range continuous air supply adjustment, full utilization of compression waste heat, significant reduction in system energy consumption, and provision of high-quality compressed air with stable pressure.

A stator-core fixing structure fixes a stator core to a housing. The stator-core fixing structure includes a plurality of outer peripheral surface portions, and a plurality of inner peripheral surface portions. The plurality of outer peripheral surface portions are included in an outer peripheral surface of the stator core and have outer diameters different from each other. The plurality of inner peripheral surface portions are included in an inner peripheral surface of the housing and have inner diameters different from each other. Each of the plurality of outer peripheral surface portions corresponds to a corresponding one of the plurality of inner peripheral surface portions. Each of the plurality of outer peripheral surface portions contacts the corresponding one of the plurality of inner peripheral surface portions.

The invention relates to the technical field of centrifugal compressors, and discloses a centrifugal compressor system which comprises a compressor assembly and a centrifugal compressor, the compressor assembly comprises an impeller, an impeller housing, a diffuser and a volute, the impeller is arranged on the impeller housing, the diffuser is arranged at an outlet of the impeller, and the volute is connected with the impeller housing and arranged on the outlet side of the diffuser; and the ultrasonic generator is fixed on at least one of the impeller housing and the diffuser. Therefore, the centrifugal compressor system utilizes the ultrasonic waves to slightly vibrate and mix the working medium gas in the system, so that the low-energy fluid in the boundary layer can continuously obtain energy injection of the fluid in the main flow area, the kinetic energy of the boundary layer and the turbulent kinetic energy of the main flow area are improved, separation is delayed, surge is delayed, the surge allowance is increased, and the separation efficiency is improved. In addition, the maximum bearing load of the blades can be increased, the efficiency of the centrifugal machine is improved, and the gas compressor assembly can keep stable operation under wider working conditions.

The utility model discloses a frequency conversion centrifugal water chilling unit which comprises a frequency conversion centrifugal compressor, a condenser, an expansion valve, an evaporator, a refrigerant circulation loop, a cooling tower, a data center server, a cooling water circulation loop and a chilled water circulation loop. The cooling water circulation loop comprises a first cooling water circulation loop and a second cooling water circulation loop which are connected between the condenser and the cooling tower in parallel. The chilled water circulation loop comprises a first chilled water circulation loop and a second chilled water circulation loop which are connected between the evaporator and the data center server in parallel. According to the utility model, the two chilled water circulation loops which are connected in parallel and the two cooling water circulation loops which are connected in parallel are adopted, so that the circulation loops can be respectively controlled according to the temperature condition of the data center server in a one-main and one-standby mode, and meanwhile, any circulation loop can be independently overhauled under the condition of no shutdown; and the cold demand of the data center is ensured.

The present application relates to the field of centrifugal compressor, especially to a wide frequency conversion operation magnetic suspension centrifugal heat pump compressor. The compressor is internally provided with a cooling channel, the cooling channel comprises a motor cooling channel, a turning channel and a discharge channel, the motor cooling channel, the turning channel and the discharge channel are sequentially communicated; when the refrigerant flows from the motor cooling channel, then passes through the turning channel and the discharge channel, finally the refrigerant flows out from the suction port channel and mixes with the low-temperature and low-pressure refrigerant gas in the first gas inlet to form superheated steam, the superheated steam enters the gas circulation structure through the first gas inlet to actively participate in the circulation process of the compressor. The compressor is communicated with the gas circulation structure of the compressor through the cooling channel, so that the structure of the compressor is more compact, the external connection is reduced, and the cost is reduced.

The utility model relates to the technical field of internal combustion engines, and discloses a direct-driven centrifugal compressor of an internal combustion engine, which comprises a V-shaped cylinder body, the top end of the V-shaped cylinder body is fixedly connected with a fuel cylinder, the middle side of the fuel cylinder is communicated with a plurality of feed pipes, the inner wall of the V-shaped cylinder body is provided with a plurality of cavities, the inner walls of the cavities are connected with pistons in a sliding manner, and the pistons are communicated with the feed pipes. The bottom ends of the pistons are rotationally connected with driving shafts, the bottom end of the inner wall of the V-shaped cylinder body is rotationally connected with a crankshaft, the bottom ends of the multiple driving shafts are rotationally connected with the outer wall of the crankshaft, the left side of the outer wall of the V-shaped cylinder body communicates with an air pipe, and the front sides and the rear sides of the top ends of the multiple cavities on the left side are slidably connected with conical nozzles. The pistons are pushed through combustion of mixed gas, the crankshaft is driven to rotate, the piston on the right side drives the hollow strip and the rack to move and be meshed with the special-shaped gear in the hollow shell, the centrifugal impeller is driven to compress gas entering the gas pipe, and therefore efficient transmission of kinetic energy is achieved.

Aircraft turbomachine (11) comprising: - a centrifugal compressor (12), - an annular combustion chamber (24), - an annular casing (29) extending around the chamber and delimiting an annular space (E) in which the chamber is located, and - a heat exchanger (38) comprising: a first circuit (38a) supplied with exhaust gases from the turbomachine, and a second circuit (38b) connected by volutes (40a, 40b) to an outlet (34b) of the compressor (12) and to the space (E) respectively, characterized in that the volutes (40a, 40b) are spaced apart from each other by an axial distance, and in that the second volute (40b) is connected to the space (E) by a rectifier (42) which is at least partially located outside the casing (29) and which is integrated into an annular connection duct (44) connecting the second volute (40b) to the casing (29).

The invention provides a high-speed direct-driven double-cantilever multi-stage cylindrical centrifugal compressor, and relates to the technical field of centrifugal compressors, the compressor is directly driven by a high-speed motor, and multi-stage impellers are serially connected on two sides of a driving spindle in a double-cantilever manner to form a first compression section and a second compression section which are serially connected to work; unification of a high pressure ratio and an extremely compact structure is realized, a transient protection device integrated at the tail end of a stay bolt is provided aiming at specific transient safety risks of the long cantilever rotor, a bearing mounting part of the stay bolt is in clearance fit with an auxiliary bearing, and the stay bolt is kept in non-contact with a rotating part when the compressor operates stably, so that the safety of the compressor is ensured. Unnecessary friction and loss are avoided, the auxiliary bearing can be in contact with the stay bolt before any static runner component only when transient overlarge deflection of the rotor occurs, so that effective mechanical limiting is provided, and collision and abrasion of dynamic and static parts are prevented.

This application relates to the field of centrifugal compressor technology, specifically disclosing a flow channel hole machining method that can automatically and accurately machine shell openings based on the actual contour of the air duct flow channel, achieving high-precision and smooth connection of the flow channel. The flow channel hole machining method includes: making a rough cut hole at a preset position where the shell and the air duct meet, based on the theoretical design dimensions of the air duct flow channel; pre-assembling and positioning the welded air duct and the shell with the rough cut hole; scanning and measuring the actual contour of the air duct flow channel to acquire contour surface data; processing the contour surface data to generate extended surface data of the air duct flow channel surface facing the direction of the shell rough cut hole; and automatically cutting and grinding the shell rough cut hole based on the extended surface data.

The invention relates to an annealing optimization algorithm during impeller parameter sensitivity analysis and response surface mismatch. The algorithm specifically comprises the following steps: 1) analyzing the sensitivity of impeller parameter change to compressor performance change; 2) analyzing the construction reliability of the impeller optimization response surface; 3) an annealing algorithm optimization method of impeller parameters; s11, determining geometric characteristic parameters of the centrifugal compressor impeller to be optimized, and constructing a parameterized model; s12, determining output parameters of the optimized impeller; s13, determining the upper and lower limits of the optimization process of the geometric characteristic parameters of the centrifugal compressor impeller to be optimized; s14, constructing a sensitivity analysis test sample, and adopting Box-Behnken design to construct the sensitivity analysis test sample; and S15, impeller parameter sensitivity analysis. And S16, establishing an upper and lower limit interval different from the traditional input variable in S13. On the premise that professional knowledge needs in the impeller design and optimization process are not increased as much as possible, the method for extracting effective design variables, avoiding blind optimization, improving calculation efficiency and improving optimization logic reliability is provided.

The present application relates to a kind of centrifugal compressor, including shell, rotor, inner magnetic ring and outer magnetic ring, the rotor is arranged in the shell, the inner magnetic ring is arranged on the rotor, the outer magnetic ring is arranged on the shell, the outer magnetic ring is sleeved on the inner magnetic ring and with the inner magnetic ring in the radial direction of the rotor with gap, the inner circumferential surface of the outer magnetic ring and the outer circumferential surface of the inner magnetic ring on pole opposite.The centrifugal compressor of the present application, when the rotor bears external axial force, the axial force received by the rotor is balanced by the magnetic attraction force between the inner magnetic ring and the outer magnetic ring, at least part of the axial force acting on the rotor is cancelled, to avoid dry grinding of the gas floating thrust bearing on the rotor, reduce the heating condition of the gas floating thrust bearing, ensure the stability of the rotor under different working conditions of centrifugal compressor.

An impeller is provided for a centrifugal compressor of an aircraft engine. The impeller includes an impeller hub and an impeller shroud having an inducer portion, an exducer portion and a bend portion interposed between the inducer portion and the exducer portion. The impeller shroud is swept forwardly in the exducer portion, the impeller shroud and the impeller hub define a gap extending through the inducer portion, the bend portion and the exducer portion and the gap is characterized as having a passage area that exhibits about a 34.375% increase from 10% of the shroud chord to 45% of the shroud chord and exhibits about a −31.1628% decrease from 45% of the shroud chord to 92.5% of the shroud chord.

The utility model relates to an inlet flow guide vane adjusting mechanism of centrifugal compressor, including the guide vane mounting seat that a plurality of guide vanes are rotatably connected, the rotatable drive ring of guide vane mounting seat outside is equipped with, and the drive ring is connected through linkage assembly between every guide vane, drive assembly is equipped with outside the guide vane mounting seat, drive assembly includes positive rotation towrope, reverse rotation towrope and pivot, positive rotation towrope one end is wound on pivot, the other end is fixed on drive ring after passing drive ring in reverse, reverse rotation towrope one end is wound on pivot, the other end is fixed on drive ring after passing drive ring in positive, and the winding direction of positive, reverse rotation towrope on pivot is opposite. The utility model discloses the drive mode of inlet flow guide vane adjusting mechanism of centrifugal compressor is simple, and the compact structure can reduce the cost while improving control accuracy, and the few parts can be reliable, and the failure rate is low, guarantees the stable and reliable operation of guide vane.

In the anti-surge method, device, electronic equipment, and medium for centrifugal compressor systems provided in this application, a first flow coefficient calculated based on the surge parameters of the centrifugal compressor is used as the current candidate coefficient. The first time required for the inlet flow rate of the centrifugal compressor to change from the initial flow rate value to the lower limit flow rate value under the current candidate coefficient is calculated. By comparing the first time and a predetermined second time, it is confirmed whether the candidate coefficient meets the operating condition requirements. If the requirements are met, the current candidate coefficient is determined as the flow coefficient of the anti-surge valve. If the requirements are not met, the current candidate coefficient is adjusted until the requirements are met. In this way, the rationality of the determined anti-surge valve flow coefficient is ensured, thereby ensuring the anti-surge effect of the centrifugal compressor.