EP0592803A1 - Compresseur à arbres multiples et transmission avec des canaux de retour et avec diffuseur radial - Google Patents

Compresseur à arbres multiples et transmission avec des canaux de retour et avec diffuseur radial Download PDF

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Publication number
EP0592803A1
EP0592803A1 EP93114214A EP93114214A EP0592803A1 EP 0592803 A1 EP0592803 A1 EP 0592803A1 EP 93114214 A EP93114214 A EP 93114214A EP 93114214 A EP93114214 A EP 93114214A EP 0592803 A1 EP0592803 A1 EP 0592803A1
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EP
European Patent Office
Prior art keywords
stage
shaft
turbo compressor
compressor according
impellers
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP93114214A
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German (de)
English (en)
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EP0592803B1 (fr
Inventor
Joachim Dr.-Ing. Kotzur
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MAN Turbo AG
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MAN Gutehoffnungshutte GmbH
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Publication of EP0592803A1 publication Critical patent/EP0592803A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
    • F04D29/056—Bearings
    • F04D29/058—Bearings magnetic; electromagnetic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/12—Combinations with mechanical gearing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/14—Multi-stage pumps with means for changing the flow-path through the stages, e.g. series-parallel, e.g. side-loads
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F04D25/163—Combinations of two or more pumps ; Producing two or more separate gas flows driven by a common gearing arrangement
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0238—Details or means for fluid reinjection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/10—Shaft sealings
    • F04D29/102—Shaft sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J3/00—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification
    • F25J3/02—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream
    • F25J3/04—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream for air
    • F25J3/04006—Providing pressurised feed air or process streams within or from the air fractionation unit
    • F25J3/04109—Arrangements of compressors and /or their drivers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J3/00—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification
    • F25J3/02—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream
    • F25J3/04—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream for air
    • F25J3/04248—Generation of cold for compensating heat leaks or liquid production, e.g. by Joule-Thompson expansion
    • F25J3/04375—Details relating to the work expansion, e.g. process parameter etc.
    • F25J3/04381—Details relating to the work expansion, e.g. process parameter etc. using work extraction by mechanical coupling of compression and expansion so-called companders
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J3/00—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification
    • F25J3/02—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream
    • F25J3/04—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream for air
    • F25J3/04248—Generation of cold for compensating heat leaks or liquid production, e.g. by Joule-Thompson expansion
    • F25J3/04375—Details relating to the work expansion, e.g. process parameter etc.
    • F25J3/04393—Details relating to the work expansion, e.g. process parameter etc. using multiple or multistage gas work expansion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J3/00—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification
    • F25J3/02—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream
    • F25J3/04—Processes or apparatus for separating the constituents of gaseous or liquefied gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream for air
    • F25J3/04763—Start-up or control of the process; Details of the apparatus used
    • F25J3/04866—Construction and layout of air fractionation equipments, e.g. valves, machines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25J—LIQUEFACTION, SOLIDIFICATION OR SEPARATION OF GASES OR GASEOUS OR LIQUEFIED GASEOUS MIXTURES BY PRESSURE AND COLD TREATMENT OR BY BRINGING THEM INTO THE SUPERCRITICAL STATE
    • F25J2230/00—Processes or apparatus involving steps for increasing the pressure of gaseous process streams
    • F25J2230/20—Integrated compressor and process expander; Gear box arrangement; Multiple compressors on a common shaft

Definitions

  • the invention relates to a multi-stage geared multi-shaft turbocompressor with flow-connected impellers which are fastened to two or more pinion shafts arranged in parallel to one another, which are driven directly via a central wheel or indirectly via pinion shafts on the circumference of the central wheel.
  • the external drive can be an electric motor, a steam or gas turbine, etc. in a known manner.
  • the power can be transferred to the compressor impellers via the pinion shaft of the drive via the central wheel via the pinion shaft of the compressor impeller or the central wheel via idler gears via the pinion shaft of the compressor impeller.
  • the gas enters the impeller axially via the intake housing and is decelerated in the volute casing.
  • the impellers in the outer diameter become smaller and smaller in order to maintain optimal volume flow numbers and the speeds of the pinion shafts to maintain the peripheral speed of the impellers required for the respective stage compression ratio. This leads to the maximum diameter of the central wheel given by its maximum peripheral speed ever smaller pinion diameters and number of pinion teeth.
  • An intermediate cooler is normally arranged between the individual compressor stages, which cools the gas back down to the initial temperature of the compression.
  • the end temperatures of the individual compressor stages are correspondingly low, corresponding to the temperature increase of the stage.
  • the process also requires a high final temperature, the final stage must run at a correspondingly high peripheral speed in order to achieve the required final temperature. This increases the pinion shaft speed even more, which means that problems mentioned above are further aggravated.
  • Another option would be to connect two stages in series with a connecting pipe without an intercooler.
  • additional flow losses due to the double energy conversion of pressure and speed energy, additional leakage losses at the exit of the pinion shaft from the spiral housing and mechanical friction losses.
  • the object of the invention is to provide a multi-shaft turbo-compressor which avoids the disadvantages of the prior art and which is characterized in that in multi-shaft turbo-compressors, in particular with high total pressure ratios, a perfect mechanical behavior with high overall efficiency and low construction costs is realized.
  • Claim 21 describes the features according to which both variants are arranged in a common machine.
  • the solution to the object is achieved in the multi-shaft turbo compressor according to the invention in that in the low pressure stages (first or first and second pinion shaft) following stages from the second or third pinion shaft, several impellers are arranged one behind the other with the interposition of a disc diffuser and a feedback ring on at least one pinion shaft end .
  • the low-pressure stages can be designed as conventional individual stages, which run in the usual way with a high peripheral speed and great swallowing capacity and thus already greatly reduce the volume flow.
  • the suction to the first impeller of the high-pressure stage group which is formed from one or more recirculation stages and an end spiral stage, takes place via an axial inlet connection.
  • the disc diffuser connected to the impeller can be designed without blades or with diffuser guide vanes.
  • the direct transfer of the outlet flow to the subsequent stages of a stage group also avoids pressure losses due to a double pressure conversion (deceleration to pipeline speed and subsequent acceleration to the impeller inlet speed of the subsequent stage).
  • This relief piston is particularly well suited to changing operating pressures of the compressor if the gas generating the axial thrust is directed from the wheel chamber behind the last stage of the high-pressure stage group arranged on the same pinion shaft to the rear of the relief piston and the gas drawn in by the high-pressure stage group the outer end of the relief piston is passed.
  • inlet or outlet connections may be necessary to attach inlet or outlet connections to the return rings of the uncooled stage groups if the inlet or outlet pressure specified by the process is between the inlet and outlet pressure of a high-pressure stage group.
  • the impellers can be connected to one another via spur gears, suitably a Hirth serration. This enables a horizontal, undivided design of the housing rings as in the conventional single stage.
  • the spur toothing consists of radial grooves that are machined into the end faces of the impellers. These interlock, are radially centered and transmit the torque.
  • the toothed components are held together axially by a central expansion screw that is screwed into the pinion shaft.
  • the spur gear elements can also be manufactured separately and attached to the impellers.
  • the spur gear can be arranged in the connected hub of the impeller group so that it is located approximately in the center of gravity of the impellers.
  • the inner housing is designed with a horizontal parting joint and surrounded by a horizontally undivided outer housing.
  • the entire rotor can be installed in the gearbox without disassembly after balancing.
  • no horizontally undivided cover on the gear unit side can seal off the casing.
  • the first impeller of the stage group is used to reduce the rotor mass and shift the center of mass with a smaller outer diameter than the impellers of the subsequent stages and / or, if necessary, without a cover plate.
  • Other variants consist of designing one or more impellers from a material with a density below that of steel, for example titanium or aluminum alloys.
  • rotor dynamic problems are solved, in particular in the case of widely overhanging rotors in the high pressure range, by the use of active magnetic bearings which hold the rotor in position by sensors and have controllable damping.
  • the known pressure combs on the gear pinions or separate axial magnetic bearings can be used.
  • the housing walls of the wheel chambers are provided with swirl breaking grooves in this case, which take the swirl out of the leakage current before it enters the labyrinth seals.
  • the labyrinth seals on the leakage current inlet side are equipped with swirl breaking ribs arranged perpendicular to the circumferential direction.
  • sealing gas is conducted without swirl or with counter-swirl from the radially outer area of the wheel chambers into the labyrinth, which prevents rotating leakage currents from entering the labyrinth seal from the wheel chamber.
  • axial guide vanes and secondary guide vanes with adjustable diffuser vanes are used in compressors.
  • step groups considered here it proves to be expedient in terms of construction and flow technology to equip the first step of a step group with an axial guide wheel and the last step with an adjustable guide wheel in front of the end spiral.
  • the geared multi-shaft turbo machine By reversing the direction of flow of the geared multiwave turbo machine designed as a geared multiwave turbo compressor, i. H. Entry of the gas on the high pressure side and exit of the gas on the low pressure side when the direction of rotation is reversed, the geared multi-shaft turbo machine works as a radial expander with the same basic design. Compared to the conventional design, the step arrangement according to the invention in the high-pressure part achieves a constant or even greater gradient per pinion shaft end with good vibration stability.
  • the outlet spiral of the compressor becomes the inlet spiral of the radial expander
  • the non-bladed or bladed disc diffuser becomes the inlet guide wheel
  • the intake manifold of the step group becomes the outlet diffuser.
  • the return ring can be carried out with or without blades.
  • the new design also offers advantages when combining compressors and radial expanders in a common gear housing.
  • the construction effort can be reduced by combining high-pressure stage groups of compressors and radial expanders on a common pinion shaft.
  • the number of compressor or radial expander stages of a pinion shaft can be varied and optimized in order to adjust the optimal speeds for a given step pressure ratio and enthalpy gradient.
  • Fig. 1 shows the front view of a known turbo compressor.
  • Three compressor stages with a spiral housing (2) are attached to a gearbox housing (1) and are driven by a central drive shaft (3) or a pinion shaft (4) arranged on the circumference of the central wheel.
  • Fig. 2 shows a section through the lower part of such a turbo compressor.
  • the gas enters the impeller (8) via the intake housing (7).
  • the gas flow is delayed in the volute casing (2).
  • the impellers of stages I to IV are dimensioned smaller and smaller due to the increasing compression in order to maintain optimal volume flow rates in the outer diameter.
  • Fig. 3 a section through the upper horizontal parting line of a turbo compressor according to Fig. 1, structural details such as gear (5, 6), impellers (8a), housing (1), etc. can be seen.
  • the low pressure part is designed according to FIG. 2.
  • FIG. 4 illustrates in a vertical section through a pinion shaft end (6) structural features of the multi-shaft turbo compressor of the prior art according to FIG. 1.
  • FIG. 5 shows the schematic structure of a turbo compressor according to the invention.
  • the turbo compressor with the volute casing (2) and the intake manifold (7) is equipped with a conventional low-pressure shaft (6) with stages I and II and a high-pressure shaft (6) according to the invention with stages III to VI.
  • Two compressor impellers (8a) are arranged on the same pinion shaft end in the same flow direction on the high-pressure shaft (6).
  • Disc diffusers (9) and return rings (10) are interposed.
  • Fig. 6 is a section through the lower horizontal parting of a turbo compressor according to the invention with the high pressure stages IV and V according to the invention, wherein two impellers (8a) are arranged on the pinion shaft (6).
  • Disc diffusers (9) and return rings (10) are also interposed here.
  • Fig. 7 a section through the upper horizontal parting line of a turbo compressor according to the invention, one can see design details of two high pressure stages (V, VI and VII, VIII) at the pinion shaft ends (6).
  • the low pressure part is in this turbo compressor in a conventional manner.
  • Fig. 2 executed.
  • the first impeller (8a) of the high-pressure stage groups has a reduced outer diameter.
  • the impeller is fastened with the help of the well-known Hirth toothing, a spur toothing (11) with a central fastening screw (12).
  • the axially opposing arrangement of the two stage groups compensates for the axial thrusts generated by each stage group due to the pressure differences before and after the impeller.
  • compressed gas is supplied from the wheel chamber (27) via the line (24a) to the inner chamber (28a) on the relief piston, while the outer chamber (28) via the relief line (24) to the suction port (7) of the first stage of the Step group is lowered in the pressure level.
  • a horizontal section through a pinion shaft end (6) shows the design with two compressor impellers with a cover plate (8a), both impellers (8a) having the same outside diameter.
  • the inner housing (17) is undivided and a relief piston (15) is integrated in the second impeller (8a).
  • Fig. 10 shows a horizontal section of a pinion shaft end (6) with an undivided inner housing of another design (17a).
  • the first impeller (8) has no cover disk and has a smaller outer diameter than the next stage with cover disk (8a).
  • FIG. 11 shows the pinion shaft end (6) of a turbo compressor according to the invention with two impellers (8a) shrunk onto the pinion shaft (6) with a shaft sleeve (29) arranged in between.
  • the compressor inner housing (18) is divided horizontally and screwed with its lower part to the gear housing.
  • the inner housing upper part (18a) is after Insert the pinion shaft (6) with the inner housing lower part (18b) screwed.
  • the undivided outer housing (19) is then pushed over and axially screwed to the gear housing middle (25a) and upper part (25), whereby an additional housing chamber (26) is formed, which can be relieved of pressure via the relief line (24).
  • a turbocompressor according to FIG. 10 additionally has gas feed channels (20) between the compressor stages, which end in the suction-side housing cover (30).
  • FIG. 13 a sectional view corresponding to Fig. 10, additional gas extraction channels (21) can be seen, which are shown between the two compressor stages shown and end in the suction-side housing cover (30).
  • Fig. 14 a section through the upper horizontal parting of a geared multi-shaft turbo compressor according to the invention with the impellers (8a), is intended to indicate the radial (22) and the axial magnetic bearing (23), which compensate for dynamic problems by the magnetic bearings over Sensors hold the rotor (6) in the desired position.
  • Fig. 15 a section through the upper horizontal parting of a geared multi-shaft turbo compressor according to the invention with the impellers (8a), shows radial magnetic bearings (22). The remaining axial thrust is absorbed in a conventional manner by pressure combs (39) via the central wheel (5) from the axial pressure bearing of the central wheel shaft (3).
  • Fig. 16 a horizontal section through a pinion shaft end (6), shows the design with two compressor impellers with a cover plate (8a), both impellers (8a) having the same outside diameter. Both impellers are firmly connected to each other, here the impeller (8a) with cover plate is shown shrunk on the extended hub of the impeller (8b). As a result, only a serration (11) is required, but the inner housing (18) must be horizontally divided (18a, 18b) for installation. A relief piston (15) is integrated in the second impeller (8b).
  • FIG. 17 shows structural details of an impeller attachment (8a, 8b).
  • the second impeller (8b) with an extended hub of the high-pressure stage group encloses with its extended hub the pinion shaft end (6), in the end face of which a Hirth toothing is milled.
  • a ring (11a) with counter-Hirth teeth is inserted on a projection (42) for manufacturing reasons.
  • the first impeller (8a) is firmly connected (shrunk, soldered, welded) to the second impeller (8b) via a centering (43).
  • Both impellers (8a, 8b) are attached to the pinion shaft end (6) together with the central fastening screw (12).
  • FIGS. 18a-18d show details of swirl breakers and the introduction of sealing gas.
  • FIG. 18 The letters A, B, C and D shown in FIG. 18 denote the enlarged sections in FIGS. 18a-18d.
  • radial swirl breaking grooves (35) are incorporated, which prevent leakage from the outer surface of the impeller to the labyrinth seals (36)
  • the impellers (8a, 8b), shaft (6) and the relief piston (15) should break.
  • Swirl breaking ribs (37) are arranged in the labyrinth seals (36) on the gas inlet side perpendicular to the circumferential direction and are intended to destroy swirl components of the flow velocity that have entered the labyrinth seal (36).
  • the labyrinth seal (36) on the intermediate sleeve (40) between the stages is supplied with sealing gas from the wheel chamber of the subsequent stage via the bores (38).
  • FIG. 19 shows a guide vane (31) with adjusting device (34) in front of the first stage of a compressor and a guide vane (32) with adjusting device (32a) after the second stage.
  • FIG. 20 shows the schematic structure of a radial expander according to the invention through the lower horizontal parting line.
  • the radial expander is equipped with a high-pressure shaft (6) according to the invention with high-pressure stages I to IV and a conventional low-pressure shaft (6) with stages V and VI.
  • Two expander impellers (8a) are arranged on the same pinion shaft end (6) in the same flow direction on the high-pressure shaft (6).
  • the gas From the inlet housing (2a), which is designed as a spiral housing, and the stator (33a) arranged in the disc annulus (9a), the gas enters the impeller (8a) and then via the return ring (10a) into the second stage, from there into the outlet cone diffuser (7a) of the radial expander.
  • FIG. 21 shows in a horizontal section a pinion shaft end (6) of a radial expander with an undivided inner housing (17a).
  • inlet guide wheels (33a) are arranged in the disk annulus (9a).
  • the return ring (10a) is designed here without a blade and serves for deflection and as a radial diffuser after the first impeller (8a).
  • FIG. 22 shows the combination of a geared multi-shaft turbomachine with a turbocompressor according to the invention (left side of the picture) with a radial expander (right side of the picture), the turbocompressor compressing a medium other than that in the radial expander.
  • the turbocompressor compressing a medium other than that in the radial expander.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Electromagnetism (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
EP93114214A 1992-10-15 1993-09-04 Compresseur à arbres multiples et transmission Expired - Lifetime EP0592803B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4234739 1992-10-15
DE4234739A DE4234739C1 (de) 1992-10-15 1992-10-15 Getriebe-Mehrwellenturbokompressor mit Rückführstufen

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EP0592803A1 true EP0592803A1 (fr) 1994-04-20
EP0592803B1 EP0592803B1 (fr) 1997-03-05

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JP (1) JPH06193585A (fr)
DE (2) DE4234739C1 (fr)
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Cited By (6)

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Publication number Priority date Publication date Assignee Title
EP0672877A1 (fr) * 1994-03-15 1995-09-20 The BOC Group plc Séparation d'air par voie cryogénique
CN105275834A (zh) * 2015-10-27 2016-01-27 上海华鼓鼓风机有限公司 一种低速多级垂直剖分筒型结构的三元流离心鼓风机
WO2018145838A1 (fr) 2017-02-10 2018-08-16 Siemens Aktiengesellschaft Étage de retour d'un compresseur à étages multiples ou détendeur doté d'aubes directrices vrillées
US11073162B2 (en) 2017-02-10 2021-07-27 Siemens Energy Global GmbH & Co. KG Return stage of a multi-staged compressor or expander with twisted guide vanes
US10995761B2 (en) 2017-02-21 2021-05-04 Siemens Energy Global GmbH & Co. KG Return stage
CN109611162A (zh) * 2018-10-25 2019-04-12 北京康吉森节能环保技术有限公司 一种利用低压饱和蒸汽发电的节能蒸汽透平发电机组

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DE59305589D1 (de) 1997-04-10
EP0592803B1 (fr) 1997-03-05
RU2111384C1 (ru) 1998-05-20
US5490760A (en) 1996-02-13
DE4234739C1 (de) 1993-11-25
JPH06193585A (ja) 1994-07-12

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