EP0686773B1 - Gear driven multi-shaft compressor and multi-shaft expander - Google Patents
Gear driven multi-shaft compressor and multi-shaft expander Download PDFInfo
- Publication number
- EP0686773B1 EP0686773B1 EP95102549A EP95102549A EP0686773B1 EP 0686773 B1 EP0686773 B1 EP 0686773B1 EP 95102549 A EP95102549 A EP 95102549A EP 95102549 A EP95102549 A EP 95102549A EP 0686773 B1 EP0686773 B1 EP 0686773B1
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- EP
- European Patent Office
- Prior art keywords
- wave
- turbocompressor
- housing
- outlet
- geared
- 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.)
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- ZZUFCTLCJUWOSV-UHFFFAOYSA-N furosemide Chemical compound C1=C(Cl)C(S(=O)(=O)N)=CC(C(O)=O)=C1NCC1=CC=CO1 ZZUFCTLCJUWOSV-UHFFFAOYSA-N 0.000 claims 1
- 230000005540 biological transmission Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000010276 construction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 238000005057 refrigeration Methods 0.000 description 1
- 238000003303 reheating Methods 0.000 description 1
- 230000009747 swallowing Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
-
- 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
- F01D15/08—Adaptations for driving, or combinations with, pumps
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- 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
- 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
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- 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
- F04D29/58—Cooling; Heating; Diminishing heat transfer
- F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
- F04D29/5826—Cooling at least part of the working fluid in a heat exchanger
Definitions
- the invention relates to a multi-stage gear multi-shaft turbo compressor with flow connected in series Impellers, being on one or several pinion shafts arranged parallel to each other two or more compressor impellers are attached, which, based on the pinion shafts, directly over a Central wheel or indirectly via pinion shafts on the circumference the central wheel are driven, with the Low pressure levels (first or first and second Pinion shaft) following high pressure stages several Impellers in the same direction of flow from Intake at the pinion shaft end in the direction Gearbox cascaded in series a disc diffuser are arranged.
- the power transmission to the compressor impellers can in the latter case via the pinion shaft of Drive via central wheel via pinion shaft of the Compressor impeller or central wheel via intermediate gears via the pinion shaft of the compressor impeller respectively.
- turbo compressor consisting of multi-stage compressor units, known.
- the compressor unit is mounted on both sides Compressor shafts arranged and flying over the Compressor shafts arranged pinions of a common gear driven. Between those in the same flow direction impellers arranged one behind the other are intercoolers intended. Via outlet housing to the intercoolers nothing done.
- This turbo compressor shows as a result of high-mechanical bearings on both sides of the compressor shafts Loss of friction and design disadvantages.
- US-A-3 809 493 is a geared single shaft turbo compressor known. This type of construction is mainly used at low Circumferential speeds used as a refrigeration compressor.
- the one with the gear shaft coupled rotor carries three flying arranged impellers, each with the interposition Intermediate cooler are flowed through in succession.
- the Flow direction of the successive impellers is opposite each other.
- arranged radially Intake manifold is the distance from the center of gravity of the overhanging shaft part enlarged to the bearing.
- the object of the invention is to provide a multi-shaft turbo compressor to create the said Avoids disadvantages of the prior art and in which the Overall efficiency at constant speed and that Total pressure ratio can be increased without have to accept rotor dynamic disadvantages.
- the center of gravity distance of the overhanging remains Part of the shaft in the same order of magnitude as for the solution DE-C-4 234 739, especially when training the Spiral casing with asymmetrical position of the spiral cross sections the impeller outlets at the intermediate outlet housing asymmetrical towards the end of the pinion shaft and with the outlet housing in the direction of the gear housing.
- the low pressure stages can be conventional Individual stages with great swallowing ability and high Peripheral speed, mostly with Semi-open wheels without a cover disc.
- the High pressure levels in the level groups are usually included Running wheels with a cover disc, but can be used the first stage of the high pressure stage group also on the Cover plate can be dispensed with.
- the inner casing can also be used horizontally undivided outer housing is horizontally undivided become.
- a Multi-shaft radial expander By reversing the direction of flow, a Multi-shaft radial expander, by inserting of the intermediate outlet housing and the Possibility of an intermediate entry housing Reheating the gas can be used.
- Fig. 1 shows a section through a horizontal Joint of a known multi-shaft gear compressor
- the turbocompressor with the intake (7) and Outlet housing (2) is with a low pressure shaft (6) with individual stages I and II with wheels (8) semi-open design without cover plate and one High pressure wave (6) with the stage groups III, IV as well as V, VI equipped.
- Fig. 2 shows a section through a horizontal Partial joint of a turbo compressor according to the invention.
- the low pressure part is here with a conventional low pressure shaft (6) with the individual stages I and II with impellers (8) half-open Type without cover plate and a high pressure shaft (6) with levels III and IV as well as V and VI with impellers (25) equipped with cover plate.
- the gas joins Stage III axially over the intake manifold (7) in the Impeller (25) enters and passes through an intermediate outlet housing (13) out of the compressor.
- To Intercooling (intercooler 24) occurs Gas back into the through the intermediate intake (4) Step group III - IV of this pinion shaft end (6) and leaves stage III - IV after Flow through the impeller (25) of stage IV Outlet housing (2).
- Fig. 3 shows a vertical longitudinal section through a Level group III - IV or V - VI one Multi-shaft turbo compressor according to the invention.
- level group III - IV or V - VI in a horizontally undivided outer housing (18) housed.
- the suction for the first Impeller (25) takes place axially via a suction nozzle (7), in the horizontally undivided inner housing (15) is arranged.
- the intermediate outlet housing (13) and that Outlet housing (2) are with respect to their Flow cross-section asymmetrical to the Impeller outlets (23) of the upstream impellers (25) arranged, namely at the Intermediate outlet housing (13) of the first stage Step group in the direction of the axial intake (7) and in the outlet housing (2) of the second stage in Direction of gearbox housing (1a, 1b).
- connection socket (20) interconnected impellers (25) are on the Spur gear teeth (11) and the central fastening screw (12) attached to the pinion shaft.
- the connection the wheels with each other are done here Shrink the impellers (25) into the connecting bush (20).
- FIG. 4 shows a step arrangement according to FIG. 3 as Multi-shaft radial expander. This occurs Gas on a nozzle not shown here Outer housing (18) and via the inlet housing (2a) of the gear housing (upper part of the gear housing 1a, Gear housing lower part 1b) adjacent stage in the Step group on and after flowing through the impeller (25a) via the inner housing with the outlet space (16) and the nozzle (4a) arranged on the outer housing (18) from the tier group.
- the gas emerges via a (not shown here) on the outer housing (18) arranged nozzle and over the Between the inlet housing (13a) at the end of the pinion shaft arranged impeller (25a) and over guide vanes (21) into the impeller (25a).
- FIG. 5 shows a combination of one Multi-shaft turbo compressor according to the invention (left half of the picture) and one according to the invention Multi-wave radial expanders (right half of the picture), the on a common gear housing (1) common pinion shafts (6) are arranged.
- the low pressure stage I of the multi-shaft turbo compressor corresponds to low pressure stage IIIa of the multiwave radial expander in the lower part of Fig. 5.
- the Intermediate outlet housing (13) Intermediate inlet housing (13a)
- the Intermediate intake (4) corresponds to the Intermediate outlet connection (4a).
- the axial Intake socket (7) applies here to the axial outlet socket (7a), which is designed as an outlet diffuser, and for the disc diffuser (9) at Multi-shaft radial expander the disc annulus (9a).
- the impellers (8, 25) of the compressor correspond to Radial expanders the impellers (8a, 25a).
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Description
Die Erfindung betrifft einen mehrstufigen Getriebe-Mehrwellenturbokompressor mit strömungsmäßig hintereinandergeschalteten Laufrädern, wobei auf einer oder mehreren parallel zueinander angeordneten Ritzelwellen zwei oder mehr Kompressor-Laufräder befestigt sind, die, bezogen auf die Ritzelwellen, direkt über ein Zentralrad oder indirekt über Ritzelwellen am Umfang des Zentralrades angetrieben werden, wobei bei den den Niederdruckstufen (erste oder erste und zweite Ritzelwelle) folgenden Hochdruckstufen mehrere Laufräder in gleicher Durchströmungsrichtung vom Ansaugstutzen am Ritzelwellenende in Richtung Getriebegehäuse hintereinander unter Zwischenschaltung eines Scheibendiffusors angeordnet sind.The invention relates to a multi-stage gear multi-shaft turbo compressor with flow connected in series Impellers, being on one or several pinion shafts arranged parallel to each other two or more compressor impellers are attached, which, based on the pinion shafts, directly over a Central wheel or indirectly via pinion shafts on the circumference the central wheel are driven, with the Low pressure levels (first or first and second Pinion shaft) following high pressure stages several Impellers in the same direction of flow from Intake at the pinion shaft end in the direction Gearbox cascaded in series a disc diffuser are arranged.
Die Leistungsübertragung auf die Kompressor-Laufräder kann im letztgenannten Fall über die Ritzelwelle des Antriebes via Zentralrad via Ritzelwelle des Kompressor-Laufrades oder zentralrad via Zwischenzahnräder via Ritzelwelle des Kompressor-Laufrades erfolgen.The power transmission to the compressor impellers can in the latter case via the pinion shaft of Drive via central wheel via pinion shaft of the Compressor impeller or central wheel via intermediate gears via the pinion shaft of the compressor impeller respectively.
Zur Lösung der bei hohen Gesamtdruckverhältnissen bezüglich der hohen Ritzelwellendrehzahlen auftretenden Probleme werden nach der DE 42 34 739 bei den den Niederdruckstufen (erste oder zweite Ritzelwelle) folgenden Stufen ab zweite oder dritte Ritzelwelle mehrere Laufräder hintereinander unter Zwischenschaltung eines Scheibendiffusors und eines Rückführringes auf wenigstens eine Ritzelwelle angeordnet.To solve the problem with high total pressure ratios occurring with regard to the high pinion shaft speeds Problems are according to DE 42 34 739 in the Low pressure stages (first or second pinion shaft) following stages from the second or third pinion shaft several wheels in a row with interposition a disc diffuser and one Return ring on at least one pinion shaft arranged.
Nachteilig ist bei dieser Ausführung, daß bei höheren Druckverhältnissen der Stufengruppen keine Zwischenkühlung nach jedem Laufrad stattfindet. The disadvantage of this version is that at higher Pressure ratios of the stage groups none Intercooling takes place after each impeller.
Die in der DE-OS 25 18 628 dargestellte Lösung, bei der jeweils ein Paar Laufräder auf der Ritzelwelle Rücken an Rücken angeordnet sind, erlaubt eine solche Zwischenkühlung, bietet jedoch rotordynamisch eher Verschlechterungen, da hier durch den zwischen Getriebegehäuse und Laufrad angeordneten radialen Ansaugstutzen ein großer Schwerpunktabstand des überhängenden Rotorteils zum Ritzelwellenlager entsteht.The solution shown in DE-OS 25 18 628, in each case a pair of wheels on the pinion shaft back to back are arranged, allows such intermediate cooling, offers however rotor dynamics rather deteriorations, since here by radial arranged between the gear housing and impeller Intake manifold a large center of gravity distance of the overhanging Rotor part to the pinion shaft bearing is created.
Aus der DE-A-1 813 335 ist ein Turboverdichter, bestehend aus mehrstufigen Verdichtereinheiten, bekannt. Die Laufräder jeder Verdichtereinheit sind auf beidseitig gelagerten Verdichterwellen angeordnet und über fliegend auf den Verdichterwellen angeordnete Ritzel eines gemeinsamen Getriebes angetrieben. Zwischen den in gleicher Strömungsrichtung hintereinander angeordneten Laufrädern sind Zwischenkühler vorgesehen. Über Austrittsgehäuse zu den Zwischenkühlern ist nichts ausgeführt. Dieser Turboverdichter weist infolge der beidseitigen Lagerung der Verdichterwellen hohe mechanische Reibungsverluste und konstruktive Nachteile auf.From DE-A-1 813 335 is a turbo compressor consisting of multi-stage compressor units, known. Everyone's wheels The compressor unit is mounted on both sides Compressor shafts arranged and flying over the Compressor shafts arranged pinions of a common gear driven. Between those in the same flow direction impellers arranged one behind the other are intercoolers intended. Via outlet housing to the intercoolers nothing done. This turbo compressor shows as a result of high-mechanical bearings on both sides of the compressor shafts Loss of friction and design disadvantages.
Aus der US-A-3 809 493 ist ein Getriebe-Einwellenturbokompressor bekannt. Diese Bauart wird hauptsächlich bei niedrigen Umfangsgeschwindigkeiten als Kältekompressor eingesetzt. Der mit der Getriebewelle gekoppelte Rotor trägt drei fliegend angeordnete Laufräder, die unter Zwischenschaltung jeweils eines Zwischenkühlers hintereinander durchströmt sind. Die Durchströmungsrichtung der aufeinander folgenden Laufräder ist jeweils entgegengesetzt. Durch den zwischen dem Getriebegehäuse und dem zweiten Laufrad vorgesehenen, radial angeordneten Ansaugstutzen wird der Abstand des Schwerpunktes des überhängenden Wellenteiles zum Lager vergrößert.US-A-3 809 493 is a geared single shaft turbo compressor known. This type of construction is mainly used at low Circumferential speeds used as a refrigeration compressor. The one with the gear shaft coupled rotor carries three flying arranged impellers, each with the interposition Intermediate cooler are flowed through in succession. The Flow direction of the successive impellers is opposite each other. By between the gearbox and the second impeller provided, arranged radially Intake manifold is the distance from the center of gravity of the overhanging shaft part enlarged to the bearing.
Die Aufgabe der Erfindung besteht darin, einen Getriebe-Mehrwellenturbokompressor zu schaffen, der die genannten Nachteile des Standes der Technik vermeidet und bei dem der Gesamtwirkungsgrad bei gleichbleibender Drehzahl und das Gesamtdruckverhältnis gesteigert werden können, ohne rotordynamische Nachteile in Kauf nehmen zu müssen.The object of the invention is to provide a multi-shaft turbo compressor to create the said Avoids disadvantages of the prior art and in which the Overall efficiency at constant speed and that Total pressure ratio can be increased without have to accept rotor dynamic disadvantages.
Die Lösung der Aufgabe erfolgt in der Weise, wie es in dem Hauptanspruch angegeben ist. Die Unteransprüche dienen der vorteilhaften Ausgestaltung der Erfindung. Dies wird erfindungsgemäß dadurch erreicht, daß bei den den Niederdruckstufen (erste oder erste und zweite Ritzelwelle) folgenden Stufen mehrere Laufräder in gleicher Durchströmungsrichtung vom Ritzelwellenende in Richtung Getriebegehäuse hintereinander, unter Zwischenschaltung eines Zwischen-Austrittsgehäuses, eines Zwischenkühlers sowie eines Zwischen-Eintrittsgehäuses zur Folgestufe angeordnet sind.The task is solved in the manner in which Main claim is specified. The subclaims serve advantageous embodiment of the invention. this will achieved according to the invention in that the Low pressure stages (first or first and second pinion shaft) following stages several impellers in the same Flow direction from the pinion shaft end in the direction Transmission housing one behind the other, with the interposition of a Intermediate outlet housing, an intercooler and one Intermediate entry housing are arranged to the next stage.
Dabei bleibt der Schwerpunktabstand des überhängenden Wellenteils in gleicher Größenordnung wie bei der Lösung nach der DE-C-4 234 739, insbesondere bei Ausbildung der Spiralgehäuse mit asymmetrischer Lage der Spiralquerschnitte zu den Laufradaustritten, und zwar bei dem Zwischen-Austrittsgehäuse asymmetrisch in Richtung Ritzelwellenende und bei dem Austrittsgehäuse in Richtung Getriebegehäuse. The center of gravity distance of the overhanging remains Part of the shaft in the same order of magnitude as for the solution DE-C-4 234 739, especially when training the Spiral casing with asymmetrical position of the spiral cross sections the impeller outlets at the intermediate outlet housing asymmetrical towards the end of the pinion shaft and with the outlet housing in the direction of the gear housing.
Die Niederdruckstufen können hierbei als konventionelle Einzelstufen mit großem Schluckvermögen und hoher Umfangsgeschwindigkeit ausgeführt werden, meistens mit Laufrädern in halboffener Bauart ohne Deckscheibe. Die Hochdruckstufen in den Stufengruppen werden meist mit Laufrädern mit Deckscheibe ausgeführt, jedoch kann bei der ersten Stufe der Hochdruckstufengruppe auch auf die Deckscheibe verzichtet werden.The low pressure stages can be conventional Individual stages with great swallowing ability and high Peripheral speed, mostly with Semi-open wheels without a cover disc. The High pressure levels in the level groups are usually included Running wheels with a cover disc, but can be used the first stage of the high pressure stage group also on the Cover plate can be dispensed with.
Werden die Laufräder der Hochdruckstufengruppen durch Stirnverzahnungen und Zentralbolzen miteinander verbunden, können die Innengehäuse auch bei horizontal ungeteiltem Außengehäuse horizontal ungeteilt ausgeführt werden.Are the impellers of the high pressure stage groups through Spur gears and central bolts connected to each other, the inner casing can also be used horizontally undivided outer housing is horizontally undivided become.
Werden die Laufräder aus rotordynamischen Gründen miteinander fest verbunden, erfordert dies eine horizontale Teilung mindestens des Innengehäuses des Zwischen-Eintrittsgehäuses.Are the wheels together for rotor dynamic reasons firmly connected, this requires one horizontal division of at least the inner casing of the Intermediate inlet housing.
Durch Umkehrung der Durchströmungsrichtung entsteht ein Mehrwellenradialexpander, bei dem durch das Einfügen des Zwischen-Austrittsgehäuses und des Zwischen-Eintrittsgehäuses die Möglichkeit einer Zwischenüberhitzung des Gases genutzt werden kann.By reversing the direction of flow, a Multi-shaft radial expander, by inserting of the intermediate outlet housing and the Possibility of an intermediate entry housing Reheating the gas can be used.
Durch die gemeinsame Anordnung von Kompressor- und Radialexpander-Stufengruppen auf einer Ritzelwelle und entsprechend von hochschluckfähigen Kompressor- und Radialexpanderstufen im Niederdruckteil lassen sich maximale Gesamtdruckverhältnisse von Turbokompressoren und Radialexpandern mit nur einem Getriebe realisieren.Due to the common arrangement of compressor and Radial expander stage groups on a pinion shaft and accordingly of highly swallowable compressor and Radial expander stages in the low pressure section can be maximum total pressure ratios of turbo compressors and radial expanders with just one gear.
Ausführungsbeispiele der Erfindung werden anhand von schematischen Zeichnungen dargestellt. Es zeigen:
- Fig. 1
- einen Schnitt durch die Teilfuge eines Turbokompressors nach dem Stand der Technik,
- Fig. 2
- einen Schnitt durch die Teilfuge eines erfindungsgemäßen Getriebe-Mehrwellenturbokompressors mit einer konventionellen Niederdruckwelle und einer neuartigen Hochdruckwelle,
- Fig. 3
- einen Schnitt durch eine erfindungsgemäße Stufengruppe mit horizontal ungeteilten Innengehäusen,
- Fig. 4
- einen Schnitt durch eine erfindungsgemäße Stufengruppe mit horizontal geteiltem Zwischengehäuse und
- Fig. 5
- eine erfindungsgemäße Kombination von Mehrwellenturbokompressor- (links) und Radialexpander-Stufengruppen (rechts).
- Fig. 1
- 3 shows a section through the parting line of a turbo compressor according to the prior art,
- Fig. 2
- 3 shows a section through the parting line of a multi-shaft turbo compressor according to the invention with a conventional low-pressure shaft and a novel high-pressure shaft,
- Fig. 3
- 2 shows a section through a step group according to the invention with horizontally undivided inner housings,
- Fig. 4
- a section through a step group according to the invention with horizontally divided intermediate housing and
- Fig. 5
- an inventive combination of multi-shaft turbo compressor (left) and radial expander stage groups (right).
Fig. 1 stellt einen Schnitt durch eine horizontale Teilfuge eines bekannten Getriebe-Mehrwellenkompressors dar. Der Turbokompressor mit dem Ansaugstutzen (7) und Austrittsgehäuse (2) ist mit einer Niederdruckwelle (6) mit den Einzelstufen I und II mit Laufrädern (8) halboffener Bauart ohne Deckscheibe sowie einer Hochdruckwelle (6) mit den Stufengruppen III, IV sowie V, VI ausgerüstet.Fig. 1 shows a section through a horizontal Joint of a known multi-shaft gear compressor The turbocompressor with the intake (7) and Outlet housing (2) is with a low pressure shaft (6) with individual stages I and II with wheels (8) semi-open design without cover plate and one High pressure wave (6) with the stage groups III, IV as well as V, VI equipped.
Auf der Hochdruckwelle sind jeweils zwei Kompressor-Laufräder (25) mit Deckscheibe in gleicher Strömungsrichtung angeordnet. Zwischengeschaltet sind Scheibendiffusoren (9) und Rückführringe (10).There are two compressor impellers on the high pressure shaft (25) with cover plate in the same direction of flow arranged. Disc diffusers are interposed (9) and return rings (10).
Fig. 2 zeigt einen Schnitt durch eine horizontale Teilfuge eines erfindungsgemäßen Turbokompressors. Fig. 2 shows a section through a horizontal Partial joint of a turbo compressor according to the invention.
Der Niederdruckteil ist hierbei mit einer konventionellen Niederdruck-Welle (6) mit den Einzelstufen I und II mit Laufrädern (8) halboffener Bauart ohne Deckscheibe und einer Hochdruck-Welle (6) mit den Stufen III und IV sowie V und VI mit Laufrädern (25) mit Deckscheibe ausgerüstet. Das Gas tritt bei Stufe III axial über den Ansaugstutzen (7) in das Laufrad (25) ein und tritt über ein Zwischen-Austrittsgehäuse (13) wieder aus dem Kompressor aus. Nach erfolgter Zwischenkühlung (Zwischenkühler 24) tritt das Gas über den Zwischen-Ansaugstutzen (4) wieder in die Stufengruppe III - IV dieses Ritzelwellenendes (6) ein und verläßt die Stufengruppe III - IV nach Durchströmung des Laufrades (25) der Stufe IV über das Austrittsgehäuse (2).The low pressure part is here with a conventional low pressure shaft (6) with the individual stages I and II with impellers (8) half-open Type without cover plate and a high pressure shaft (6) with levels III and IV as well as V and VI with impellers (25) equipped with cover plate. The gas joins Stage III axially over the intake manifold (7) in the Impeller (25) enters and passes through an intermediate outlet housing (13) out of the compressor. To Intercooling (intercooler 24) occurs Gas back into the through the intermediate intake (4) Step group III - IV of this pinion shaft end (6) and leaves stage III - IV after Flow through the impeller (25) of stage IV Outlet housing (2).
Entsprechendes gilt für die Stufengruppe V - VI.The same applies to the level groups V - VI.
Fig. 3 zeigt einen vertikalen Längsschnitt durch eine Stufengruppe III - IV bzw. V - VI eines erfindungsgemäßen Getriebe-Mehrwellenturbokompressors.Fig. 3 shows a vertical longitudinal section through a Level group III - IV or V - VI one Multi-shaft turbo compressor according to the invention.
Hierbei sind die beiden Stufen der Stufengruppe III - IV bzw. V - VI in einem horizontal ungeteilten Außengehäuse (18) untergebracht. Die Ansaugung zum ersten Laufrad (25) erfolgt axial über einen Saugstutzen (7), der in dem horizontal ungeteilten Innengehäuse (15) angeordnet ist.Here are the two levels of level group III - IV or V - VI in a horizontally undivided outer housing (18) housed. The suction for the first Impeller (25) takes place axially via a suction nozzle (7), in the horizontally undivided inner housing (15) is arranged.
In diesem Innengehäuse (15) ist auch das Zwischen-Austrittsgehäuse (13) nach dem Laufrad (25) angeordnet, über dessen Anschlußstutzen (hier nicht dargestellt) im Außengehäuse (18) das Gas zum (hier nicht dargestellten) Zwischenkühler austritt. Über den Zwischen-Ansaugstutzen (4) tritt das Gas wieder in die Stufengruppe ein. Da beide Laufräder (25) durch die Verbindungsbuchse (20) vor der Montage auf der Ritzelwelle (6) fest miteinander verbunden sind, muß das Innengehäuse (17, 17b) mit dem Ansaugraum horizontal geteilt ausgeführt sein. Nach Verlassen des zweiten Laufrades (25) tritt das Gas durch das Austrittsgehäuse (2) über einen (hier nicht sichtbaren) Stutzen am Außengehäuse (18) aus der Stufengruppe aus. Das Zwischen-Austrittsgehäuse (13) und das Austrittsgehäuse (2) sind bezüglich ihres Strömungsquerschnittes asymmetrisch zu den Laufradaustritten (23) der vorgeschalteten Laufräder (25) angeordnet, und zwar bei dem Zwischen-Austrittsgehäuse (13) der ersten Stufe der Stufengruppe in Richtung des axialen Ansaugstutzens (7) und bei dem Austrittsgehäuse (2) der zweiten Stufe in Richtung Getriebegehäuse (1a, 1b). Dadurch ergibt sich der erforderliche Platz für das Innengehäuse (17a, 17b) mit dem Ansaugraum, ohne das Ritzelwellenende gegenüber der bekannten Lösung (Fig. 1) zu verlängern.This is also in this inner housing (15) Intermediate outlet housing (13) after the impeller (25) arranged, over its connecting piece (not here shown) in the outer housing (18) the gas for (here Intercooler (not shown) emerges. On the The gas enters the intake manifold (4) again Level group. Since both impellers (25) through the Connection socket (20) before mounting on the Pinion shaft (6) are firmly connected the inner housing (17, 17b) with the suction space horizontally divided. After leaving the second impeller (25) passes through the gas Outlet housing (2) over a (not visible here) Out of the step group on the outer casing (18). The intermediate outlet housing (13) and that Outlet housing (2) are with respect to their Flow cross-section asymmetrical to the Impeller outlets (23) of the upstream impellers (25) arranged, namely at the Intermediate outlet housing (13) of the first stage Step group in the direction of the axial intake (7) and in the outlet housing (2) of the second stage in Direction of gearbox housing (1a, 1b). This results in the space required for the inner housing (17a, 17b) with the intake chamber without the pinion shaft end opposite to extend the known solution (Fig. 1).
Die beiden durch eine Verbindungsbuchse (20) fest miteinander verbundenen Laufräder (25) sind über die Stirnverzahnungen (11) und die zentrale Befestigungsschraube (12) an der Ritzelwelle befestigt. Die Verbindung der Laufräder miteinander erfolgt hier durch Einschrumpfen der Laufräder (25) in die Verbindungsbuchse (20).The two are fixed by a connection socket (20) interconnected impellers (25) are on the Spur gear teeth (11) and the central fastening screw (12) attached to the pinion shaft. The connection the wheels with each other are done here Shrink the impellers (25) into the connecting bush (20).
Fig. 4 zeigt eine Stufenanordnung gemäß Fig. 3 als
Mehrwellen-Radialexpander ausgeführt. Hierbei tritt das
Gas über einen hier nicht dargestellten Stutzen am
Außengehäuse (18) und über das Eintrittsgehäuse (2a)
der dem Getriebegehäuse (Getriebegehäuse-Oberteil 1a,
Getriebegehäuse-Unterteil 1b) benachbarten Stufe in die
Stufengruppe ein und nach Durchströmen des Laufrades
(25a) über das Innengehäuse mit dem Austrittsraum (16)
und dem am Außengehäuse (18) angeordneten Stutzen (4a)
aus der Stufengruppe aus.FIG. 4 shows a step arrangement according to FIG. 3 as
Multi-shaft radial expander. This occurs
Gas on a nozzle not shown here
Outer housing (18) and via the inlet housing (2a)
of the gear housing (upper part of the gear housing 1a,
Gear housing
Nach einer äußeren Zwischenüberhitzung tritt das Gas über einen (hier nicht dargestellten) am Außengehäuse (18) angeordneten Stutzen und über das Zwischen-Eintrittsgehäuse (13a) des am Ritzelwellenende angeordneten Laufrades (25a) und über Leitschaufeln (21) in das Laufrad (25a) ein.After an external reheat, the gas emerges via a (not shown here) on the outer housing (18) arranged nozzle and over the Between the inlet housing (13a) at the end of the pinion shaft arranged impeller (25a) and over guide vanes (21) into the impeller (25a).
Nach Verlassen des Laufrades (25a) strömt das Gas über den axialen Austrittsstutzen (7a) ab.After leaving the impeller (25a), the gas overflows the axial outlet connection (7a).
Da hier beide Laufräder (25a) über eine Stirnverzahnung (11) miteinander verbunden sind, braucht das Innengehäuse (16) mit dem Austrittsraum nicht für die Montage horizontal geteilt zu werden.Since both impellers (25a) have spur gear teeth here (11) are interconnected, that needs Inner housing (16) with the outlet space not for the Montage to be divided horizontally.
Fig. 5 zeigt schließlich eine Kombination eines erfindungsgemäßen Getriebe-Mehrwellenturbokompressors (linke Bildhälfte) und eines erfindungsgemäßen Mehrwellenradialexpanders (rechte Bildhälfte), die an einem gemeinsamen Getriebegehäuse (1) auf gemeinsamen Ritzelwellen (6) angeordnet sind.5 shows a combination of one Multi-shaft turbo compressor according to the invention (left half of the picture) and one according to the invention Multi-wave radial expanders (right half of the picture), the on a common gear housing (1) common pinion shafts (6) are arranged.
Der Niederdruckstufe I des Getriebe-Mehrwellenturbokompressors entspricht die Niederdruckstufe IIIa des Mehrwellenradialexpanders im unteren Teil von Fig. 5.The low pressure stage I of the multi-shaft turbo compressor corresponds to low pressure stage IIIa of the multiwave radial expander in the lower part of Fig. 5.
Die Hochdruckstufen II, III des Getriebe-Mehrwellenturbokompressors und die Hochdruckstufen Ia, IIa des Mehrwellenradialexpanders sind im oberen Teil von Fig. 5 erkennbar.The high pressure stages II, III of the multi-shaft turbo compressor and the high pressure stages Ia, IIa des Multi-wave radial expanders are shown in the upper part of Fig. 5 recognizable.
Den Austrittsgehäusen (2) auf der Kompressorseite entsprechen die Eintrittsgehäuse (2a) des Radialexpanders. Correspond to the outlet housings (2) on the compressor side the inlet casing (2a) of the radial expander.
Dem Zwischen-Austrittsgehäuse (13) entspricht das Zwischen-Eintrittsgehäuse (13a), dem Zwischenansaugstutzen (4) entspricht der Zwischenaustrittsstutzen (4a). Für den axialen Ansaugstutzen (7) gilt hier der axiale Austrittsstutzen (7a), der als Austrittsdiffusor ausgebildet ist, und für den Scheibendiffusor (9) beim Mehrwellen-Radialexpander der Scheibenringraum (9a).This corresponds to the intermediate outlet housing (13) Intermediate inlet housing (13a), the Intermediate intake (4) corresponds to the Intermediate outlet connection (4a). For the axial Intake socket (7) applies here to the axial outlet socket (7a), which is designed as an outlet diffuser, and for the disc diffuser (9) at Multi-shaft radial expander the disc annulus (9a).
Den Laufrädern (8, 25) des Kompressors entsprechen beim Radialexpander die Laufräder (8a, 25a). The impellers (8, 25) of the compressor correspond to Radial expanders the impellers (8a, 25a).
- 1
- Getriebegehäuse
- 1a
- Getriebegehäuse-Oberteil
- 1b
- Getriebegehäuse-Unterteil
- 2
- Austrittsgehäuse bei Kompressoren
- 2a
- Eintrittsgehäuse bei Radialexpandern
- 3
- Antriebswelle des Zentralrades
- 4
- Zwischenansaugstutzen des Kompressors
- 4a
- Zwischenaustrittsstutzen des Radialexpanders
- 5
- Zentralrad
- 6
- Ritzelwelle mit Kompressor- und/oder Radialexpanderstufen
- 7
- Axialer Ansaugstutzen für Kompressorstufen
- 7a
- Axialer Austrittsstutzen für Radialexpander-Stufen
- 8
- Laufrad Niederdruck-Stufe Kompressor
- 8a
- Laufrad Niederdruck-Stufe Expander
- 9
- Scheibendiffusor bei Kompressor, beschaufelt oder unbeschaufelt
- 9a
- Scheibenringraum bei Radialexpander, beschaufelt oder unbeschaufelt
- 10
- Rückführring des Kompressors
- 11
- Stirnverzahnung (nach Hirth)
- 12
- zentrale Befestigungsschraube für Stirnverzahnung
- 13
- Zwischen-Austrittsgehäuse bei Kompressoren
- 13a
- Zwischen-Eintrittsgehäuse bei Radialexpandern
- 14
- Wellendichtung
- 14a
- Horizontal geteiltes Wellendichtungs-Oberteil
- 14b
- Horizontal geteiltes Wellendichtungs-Unterteil
- 15
- Horizontal ungeteiltes Innengehäuse mit Spirale
- 16
- Horizontal ungeteiltes Innengehäuse mit Austrittsraum
- 17
- Horizontal geteiltes Innengehäuse mit Ansaugraum
- 17a
Oberteil von 17- 17b
Unterteil von 17- 18
- Horizontal ungeteiltes Außengehäuse
- 19
- Laufraddichtung
- 19a
- Horizontal geteilte Laufraddichtung Oberteil
- 19b
- Horizontal geteilte Laufraddichtung Unterteil
- 20
- Verbindungsbuchse
- 21
- Leitschaufeln im Scheibenringraum
- 22
- Leitschaufeln im Ansaugraum
- 22a
- Leitschaufeln im Austrittsraum
- 23
- Laufradaustritt Kompressor
- 23a
- Laufradeintritt Radialexpander
- 24
- Zwischenkühler
- 24a
- Zwischenerhitzer
- 25
- Laufrad Hochdruckstufengruppen Kompressor
- 25a
- Laufrad Hochdruck-Stufengruppen Radialexpander
Ia, IIa, IIIa, IVa, Va, VIa: Reihenfolge der Laufräder in Strömungsrichtung beim Radialexpander
- 1
- gearbox
- 1a
- Gearbox housing top
- 1b
- Transmission Housing base
- 2
- Outlet housing for compressors
- 2a
- Entry housing for radial expanders
- 3
- Central shaft drive shaft
- 4
- Intermediate intake of the compressor
- 4a
- Intermediate outlet of the radial expander
- 5
- central wheel
- 6
- Pinion shaft with compressor and / or radial expander stages
- 7
- Axial intake manifold for compressor stages
- 7a
- Axial outlet nozzle for radial expander stages
- 8th
- Impeller low pressure stage compressor
- 8a
- Impeller low pressure stage expander
- 9
- Disc diffuser for compressor, bladed or unspread
- 9a
- Disc ring space in the case of radial expanders, bladed or not bladed
- 10
- Return ring of the compressor
- 11
- Spur toothing (according to Hirth)
- 12
- central fastening screw for spur gearing
- 13
- Intermediate outlet housing for compressors
- 13a
- Intermediate inlet housing for radial expanders
- 14
- shaft seal
- 14a
- Horizontally split shaft seal upper part
- 14b
- Horizontally divided shaft seal lower part
- 15
- Horizontal undivided inner casing with spiral
- 16
- Horizontal undivided inner housing with outlet space
- 17
- Horizontally divided inner housing with suction space
- 17a
- Top of 17
- 17b
- Lower part of 17
- 18
- Horizontal undivided outer casing
- 19
- impeller seal
- 19a
- Horizontally split impeller upper part
- 19b
- Horizontal split impeller lower part
- 20
- connection socket
- 21
- Guide vanes in the disc annulus
- 22
- Guide vanes in the intake space
- 22a
- Guide vanes in the outlet space
- 23
- Impeller outlet compressor
- 23a
- Radial expander impeller inlet
- 24
- intercooler
- 24a
- reheater
- 25
- Impeller high pressure stage group compressor
- 25a
- Impeller high pressure stage groups radial expander
Ia, IIa, IIIa, IVa, Va, VIa: Order of the impellers in the direction of flow in the radial expander
Claims (6)
- Multi-stage geared multi-wave turbocompressor with impellers (25) arranged in succession in terms of flow, wherein two or more compressor impellers (25) are mounted on one or more mutually parallelly arranged pinion shafts (6) and with respect to the pinion shafts (6) are driven directly by way of a central wheel (5) or indirectly by way of pinion shafts at the circumference of the central wheel (5), wherein for the high-pressure stages (III, IV, V, VI) following the lower-pressure stages (I, II) (first or first and second pinion shaft) several impellers (25) are arranged in succession in the same throughflow direction from the intake port (7) at the pinion shaft end in the direction of the gear casing (1) with interposition of a disc diffuser (9), characterised in that connected to the disc diffuser (9) of impeller (25) arranged at the pinion shaft end is an intermediate outlet casing (13) by way of which the gas is fed to an intermediate cooler (24) and subsequently passes into the intermediate intake port (4) to the following stage which is flowed through in the same throughflow direction in the direction of the gear casing (1) and is provided with the outlet housing (2).
- Multi-stage geared multi-wave turbocompressor according to claim 1, characterised in that the intermediate outlet housing (13) is a spiral housing.
- Multi-stage geared multi-wave turbocompressor according to claims 1 and 2, characterised in that the intermediate outlet housing (13) has, with respect to the impeller outlet (23), at the pinion shaft end an asymmetrical flow cross-section in the direction of the intake port (7) and that the outlet housing (2) of this stage group has an asymmetrical flow cross-section to its impeller outlet (23) in the direction of the gear casing (1).
- Use of a multi-stage geared multi-wave turbocompressor with the features of claims 1 to 3 as, by reversal of the flow direction, a multi-wave radial expander, characterised in that the outlet housing (2) of the multi-wave turbocompressor is connected as inlet housing (2a) of the multi-wave radial expander and the axial inlet port (7) of the multi-wave turbocompressor is connected as axial outlet diffuser (7a) of the multi-wave radial expander.
- Use of a multi-stage geared multi-wave turbocompressor according to claim 3, characterised in that the outlet housing (2) of the high-pressure stages of the geared multi-wave turbocompressor is connected as inlet housing (2a) of a multi-wave radial expander, that the disc diffuser (9) of the high-pressure stages of the geared multi-wave turbocompressor is arranged as inlet discoid annular space (9a) of the multi-wave radial expander, that the impellers (25) of the geared multi-wave turbocompressor are arranged as impellers (25a) of the multi-wave radial expander, that the intermediate intake port (4) of the geared multi-wave turbocompressor is connected as intermediate outlet port (4a) of the multi-wave radial expander, that the intermediate outlet housing (13) of the geared multi-wave turbocompressor is arranged as intermediate inlet housing (13a) of the multi-wave radial expander and that the intake port (7) of the geared multi-wave turbocompressor is connected as outlet port (7a) of the multi-wave radial expander.
- Multi-stage geared multi-wave turbocompressor according to claims 1 to 3, characterised in that high-pressure stage groups of geared multi-wave turbocompressors and multi-wave radial expanders are arranged on the same pinion shafts (6).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE4416497A DE4416497C1 (en) | 1994-05-10 | 1994-05-10 | Geared multi-shaft turbo-compressor and geared multi-shaft radial expander |
| DE4416497 | 1994-05-10 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP0686773A2 EP0686773A2 (en) | 1995-12-13 |
| EP0686773A3 EP0686773A3 (en) | 1997-06-25 |
| EP0686773B1 true EP0686773B1 (en) | 2002-05-29 |
Family
ID=6517789
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP95102549A Expired - Lifetime EP0686773B1 (en) | 1994-05-10 | 1995-02-23 | Gear driven multi-shaft compressor and multi-shaft expander |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US5611663A (en) |
| EP (1) | EP0686773B1 (en) |
| JP (1) | JPH08189494A (en) |
| DE (2) | DE4416497C1 (en) |
| RU (1) | RU2132971C1 (en) |
| UA (1) | UA32572C2 (en) |
Cited By (1)
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|---|---|---|---|---|
| WO2014180688A1 (en) | 2013-05-08 | 2014-11-13 | Voith Patent Gmbh | Transmission and compressor system for a transmission |
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| US9316228B2 (en) * | 2009-03-24 | 2016-04-19 | Concepts Nrec, Llc | High-flow-capacity centrifugal hydrogen gas compression systems, methods and components therefor |
| DE102010017061A1 (en) * | 2010-05-21 | 2011-11-24 | Bio-System Gesellschaft Für Anwendungen Biologischer Verfahren Mbh | steam turbine |
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| CN102287355A (en) * | 2011-08-02 | 2011-12-21 | 长沙赛尔机泵有限公司 | gas compression system and method |
| EP2604862A1 (en) * | 2011-12-12 | 2013-06-19 | Air Products and Chemicals, Inc. | A compressor arrangement |
| WO2014060163A1 (en) * | 2012-10-16 | 2014-04-24 | Siemens Aktiengesellschaft | Weld-free pot volute casing |
| KR20140100111A (en) | 2013-02-05 | 2014-08-14 | 삼성테크윈 주식회사 | A compressing system |
| DE102014001998A1 (en) * | 2013-12-17 | 2015-06-18 | Man Diesel & Turbo Se | compressor stage |
| DE102014218945A1 (en) * | 2014-09-19 | 2016-03-24 | Siemens Aktiengesellschaft | Housing cast model, housing series, method of producing a cast housing of a radial turbofan energy machine |
| US10329943B2 (en) | 2014-11-18 | 2019-06-25 | Rolls-Royce North American Technologies Inc. | Split axial-centrifugal compressor |
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| CN106014519B (en) * | 2016-05-20 | 2019-03-08 | 中国长江动力集团有限公司 | Steam turbine and Organic Rankine Cycle working medium turbine dual drive system |
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-
1994
- 1994-05-10 DE DE4416497A patent/DE4416497C1/en not_active Expired - Fee Related
-
1995
- 1995-02-23 DE DE59510216T patent/DE59510216D1/en not_active Expired - Fee Related
- 1995-02-23 EP EP95102549A patent/EP0686773B1/en not_active Expired - Lifetime
- 1995-04-21 RU RU95106609A patent/RU2132971C1/en not_active IP Right Cessation
- 1995-04-24 JP JP7132509A patent/JPH08189494A/en active Pending
- 1995-05-09 US US08/437,402 patent/US5611663A/en not_active Expired - Fee Related
- 1995-05-10 UA UA95058411A patent/UA32572C2/en unknown
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2014180688A1 (en) | 2013-05-08 | 2014-11-13 | Voith Patent Gmbh | Transmission and compressor system for a transmission |
Also Published As
| Publication number | Publication date |
|---|---|
| DE59510216D1 (en) | 2002-07-04 |
| DE4416497C1 (en) | 1995-01-12 |
| EP0686773A2 (en) | 1995-12-13 |
| RU95106609A (en) | 1997-02-20 |
| EP0686773A3 (en) | 1997-06-25 |
| RU2132971C1 (en) | 1999-07-10 |
| US5611663A (en) | 1997-03-18 |
| JPH08189494A (en) | 1996-07-23 |
| UA32572C2 (en) | 2001-02-15 |
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