EP2321534B1 - Intermediate housing floor for a fluid kinetic machine - Google Patents

Intermediate housing floor for a fluid kinetic machine Download PDF

Info

Publication number
EP2321534B1
EP2321534B1 EP09782156.5A EP09782156A EP2321534B1 EP 2321534 B1 EP2321534 B1 EP 2321534B1 EP 09782156 A EP09782156 A EP 09782156A EP 2321534 B1 EP2321534 B1 EP 2321534B1
Authority
EP
European Patent Office
Prior art keywords
intermediate housing
housing floor
part joint
layer
joint face
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.)
Not-in-force
Application number
EP09782156.5A
Other languages
German (de)
French (fr)
Other versions
EP2321534A1 (en
Inventor
Wolfgang Zacharias
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP2321534A1 publication Critical patent/EP2321534A1/en
Application granted granted Critical
Publication of EP2321534B1 publication Critical patent/EP2321534B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F04D29/08—Sealings
    • F04D29/083—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
    • 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
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal flow wheel
    • 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
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps

Definitions

  • the invention relates to a housing intermediate bottom for a turbomachine and a turbomachine with the housing intermediate bottom.
  • a turbomachine such as a radial turbocompressor is configured as a single shaft compressor having a shaft with impellers threaded thereon and a housing surrounding the impellers.
  • the shaft is mounted radially and axially outside of the housing by means of bearings, wherein flow channels are formed from and to the wheels in the interior of the housing by the provision of housing internals.
  • the wheels are, for example, designed as radial impellers, which have, for example, an axial inflow direction and a radial outflow direction.
  • the impellers are flowed through one after the other so that process gas is gradually compressed from impeller to impeller.
  • a ring diffuser is provided, through which the process gas is guided radially outward.
  • the process gas is deflected and guided radially inward through a return channel to the next impeller.
  • the housing internals are provided with a corresponding shape, so that the ring diffuser, the deflection channel and the return channel are formed by the interaction of the housing internals in the housing.
  • the housing internals are conventionally designed as housing intermediate floors.
  • Each housing intermediate floor is formed by two halves, so that the housing intermediate floor is divisible horizontally.
  • a housing intermediate bottom by attaching the one half in the lower part of the housing (horizontally divided turbomachine) or in the lower part of Inner housing (vertically divided turbomachine) and are mounted by applying the other half in the upper part.
  • the two halves form at their contact surfaces of a parting line, which due to manufacturing inaccuracies and / or deformation of the halves caused by a compressive stress during operation of the radial turbo compressor diverge and thus can be gas permeable.
  • a leakage occurs through the parting line, which is considerable, especially in radial turbochargers with high pressure differences.
  • the leakage in Radial turbo compressors with high pressure ratio and small flow rate is disadvantageous. Due to the leakage, the efficiency of the radial turbocompressor is reduced, whereby the required power consumption is increased in the fulfillment of predefined boundary conditions by the radial turbocompressor.
  • the maximum possible prediction accuracy with respect to pressure ratio and flow rate of the radial turbocharger is subject to higher tolerances, since the actual effect of the possibly gaping parting line on the operating parameters of the radial turbocompressor is difficult to predict.
  • the object of the invention is to provide a housing intermediate bottom for a turbomachine and a turbomachine with the housing intermediate bottom, wherein the turbomachine has a high efficiency.
  • the object is achieved by a housing intermediate floor of the type mentioned, which has the additional features of the characterizing part of claim 1.
  • the housing intermediate floor in the turbomachine of the housing intermediate bottom is provided with the parting line and the two parting surfaces.
  • the recess formed in the one part of the joint surface is provided with the coating, wherein protrudes from the one part of the joint surface, the coating, so that the coating has the supernatant.
  • the two parting surfaces are placed against each other so that the coating rests against the other parting surface facing it. Once the parting surfaces are arranged touching each other, the coating is compressed at its supernatant. As a result, the coating lies tightly and flat against the parting surface facing it, so that the parting line is sealed by the coating.
  • leakage of process gas through the parting line is prevented or at least reduced, as a result of which the turbomachine has improved efficiency.
  • the intermediate housing bottom is sealed off from the coating in the assembled state at the parting line, so that such structural inaccuracies can not lead to a deterioration in the performance parameters of the turbomachine.
  • the performance parameters of the turbomachine can be better predicted by conventional methods, so that the turbomachine can be designed accurately.
  • the risk is reduced that it is determined in a possible test run the turbomachine that the turbomachine can not meet the required performance parameters.
  • corresponding rectification actions on the turbomachine would be necessary, which can be omitted according to the invention.
  • the coating is a honeycomb layer.
  • the honeycomb layer can be produced inexpensively from correspondingly shaped metal strips, with which a honeycomb structure of the honeycomb layer is formed.
  • the honeycomb structure is formed such that the sheet metal strips are compressed in the assembled state of the housing intermediate bottom of the other part of the joint surface.
  • the honeycomb layer is preferably soldered into the trough.
  • the coating is preferably a flame-sprayed or plasma-sprayed sprayed coating.
  • the sprayed layer is preferably Ni-Al-Cr-based.
  • a trough and in the other part of the joint surface is provided, in each of which one of the coatings is housed, wherein the coatings are arranged overlapping each other.
  • one partial joint surface is the honeycomb layer and for the other partial joint surface to be the sprayed layer.
  • the honeycomb layer is provided with its supernatant on one part of the joint surface and the sprayed layer on the other part of the joint surface. If the part-joint surfaces are placed against one another during assembly, the honeycomb layer is optionally pressed into the sprayed layer under its own deformation, so that the honeycomb layer forms a dense structure in the parting joint with the sprayed layer.
  • the thickness of the sprayed layer is preferably dimensioned at the other parting surface at least as large as the supernatant of the honeycomb layer, so that in the assembled state of the housing intermediate bottom, the honeycomb layer is pressed into the sprayed layer.
  • the spray layer extends in the assembled state of the housing intermediate base only in the honeycomb interstices of the honeycomb layer, since the honeycomb layer abuts the bottom of the trough - with a certain margin for manufacturing tolerances - of the other part joint surface.
  • the parting line with the honeycomb layer and the sprayed layer is stable and tightly sealed.
  • the supernatant is carried out on the sprayed layer.
  • the housing intermediate bottom is formed from a lower half and an upper half, which in the assembled state form the parting line in a plane in which the axis of rotation of the turbomachine lies.
  • the housing intermediate bottom is formed from the approximately equal halves, so that the housing intermediate floor is easy to assemble and disassemble. It is preferred that on the lower half of the one part of the joint surface with the honeycomb layer and on the upper half of the other part of the joint surface is provided with the sprayed layer. Alternatively, it is preferred that on the upper half of a parting surface with the Honeycomb layer and on the lower half of the other part of the joint surface is provided with the sprayed layer.
  • the turbomachine is a radial turbocompressor having a radial turbocompressor stage with a ring diffuser, a deflection channel and a return channel, which are formed by at least two housing intermediate floors.
  • a radial turbo compressor 1 comprises a housing 2 or a housing 2 and an inner housing 33 and a rotor 3.
  • a suction nozzle 4 and a discharge nozzle 5 is provided, wherein the suction nozzle 4 opens in the interior of the housing 2 in an inlet 6 and an opening provided in the interior of the housing 2 exit spiral 7 opens into the discharge nozzle 5.
  • each of an impeller 9 of the rotor 3 is formed.
  • Each impeller 9 has an axial inflow direction pointing in the direction of the rotation axis 24 of the rotor 3 and a radial outflow direction pointing outwards.
  • a ring diffuser 10 which extends radially outward within the housing 2 and downstream of the impeller 9 this is followed.
  • the annular diffuser 10 is followed in the flow direction by a deflection channel 11, in which process gas is deflected by the ring diffuser 10 into a return channel 12, in which the process gas flows radially inwards towards the impeller 9 of the next radial turbocompressor stage 8.
  • a first intermediate housing bottom 13 and a second housing intermediate bottom 14 is provided for the Radialturbover Whyrtre 8, which are provided with such a contour and arranged to each other such that under cooperation of the first housing intermediate bottom 13 and the second housing intermediate bottom 14 of the ring diffuser 10, the deflection channel 11 and the return channel 12 are formed in the housing 2.
  • the first housing intermediate bottom 13 has a cylindrical outer side 15 and is located on the inside of the housing 2, wherein the first housing intermediate bottom 13 is locked with an annular web 16 on the housing 2.
  • the first housing intermediate bottom 13 and the second housing intermediate bottom 14 are similar in their construction, so that in the following only the first housing intermediate bottom 13 is referred to.
  • the first housing intermediate bottom 13 has a lower half 17 and an upper half 18, so that of the lower half 17 and the upper half 18, a parting line 19 is formed.
  • the lower half 17 and the upper half 18 are formed substantially geometrically the same, so that the parting line 19 lies in a plane in which the axis of rotation 24 of the radial turbocompressor 11 is located.
  • the lower half 17 has a part-joint surface 20 and the upper half 18 has a part-joint surface 21, wherein the part-joint surfaces 20, 21 formed identically in their outline are, so that when the lower half 17 is applied to the upper half 18 to form the parting line 19, the parting surfaces 20 and 21 completely overlap.
  • a plan view of the parting surface 20 of the lower half 17 is shown.
  • a trough 22 is provided, the border of which is always arranged at a distance from the edge of the parting surface 20.
  • the trough 22 is completely surrounded by the parting surface 20.
  • a honeycomb layer 23 is housed, which completely fills the trough 22.
  • the honeycomb layer 23 is constructed of metal strips 25 which are wave-shaped and are joined together to form honeycomb.
  • a solder 27 is provided, with which the honeycomb layer 23 is secured in the trough 22.
  • the honeycomb layer 23 has a ridge height 28 which is greater than the depth of the trough 22. This results in the honeycomb layer 23, a projection 29 which projects from the parting surface 20.
  • the in the assembled state of the housing intermediate bottom 13 of the parting surface 20 of the lower half 17 facing parting surface 21 of the upper half 18 has a trough 30, the edge of which runs parallel to the border of the trough 22.
  • the trough 30 tends to be larger in its extent along the parting surface 21 than the trough 22, so that the trough 30 completely covers the trough 22. Thereby, it is prevented that the honeycomb layer 23, which is arranged in the trough 22, comes into contact with the edge of the trough 30 and the parting surface 20.
  • a spray layer 31 is provided, which completely fills the trough 30.
  • the depth of the trough 30 results in a layer thickness 32, which is formed due to production either equal to the supernatant 29 or greater.
  • the upper half 18 When mounting the housing intermediate bottom 13, the upper half 18 is set with its parting surface 21 on the parting surface 20 of the lower half 17, wherein the troughs 22 and 30 come to cover. Due to the supernatant 29 of the honeycomb layer 23 provided on the trough 22, this wears into the sprayed layer 31. As a result, a dense and stable configuration is created in the parting line 19 with the honeycomb layer 23 and the sprayed layer 31.

Description

Die Erfindung betrifft einen Gehäusezwischenboden für eine Strömungsmaschine und eine Strömungsmaschine mit dem Gehäusezwischenboden.The invention relates to a housing intermediate bottom for a turbomachine and a turbomachine with the housing intermediate bottom.

Eine Strömungsmaschine wie ein Radialturboverdichter ist beispielsweise als ein Einwellenverdichter ausgeführt, der eine Welle mit darauf aufgefädelten Laufrädern und ein Gehäuse aufweist, das die Laufräder umgibt. Die Welle ist außerhalb des Gehäuses mittels Lager radial und axial gelagert, wobei im Inneren des Gehäuses durch das Vorsehen von Gehäuseeinbauten Strömungskanäle von und zu den Laufrädern ausgebildet sind. Die Laufräder sind beispielsweise als Radiallaufräder ausgebildet, die beispielsweise eine axiale Zuströmrichtung und eine radiale Abströmrichtung haben. Die Laufräder werden nacheinander durchströmt, so dass Prozessgas stufenweise von Laufrad zu Laufrad verdichtet wird. An der Abströmseite eines jeden Laufrads ist ein Ringdiffusor vorgesehen, durch den das Prozessgas radial nach außen geführt wird. Mit Hilfe eines Umlenkkanals nach dem Ringdiffusor wird das Prozessgas umgelenkt und radial wieder nach innen durch einen Rückführkanal zu dem nächsten Laufrad geführt. In dem Gehäuse sind die Gehäuseeinbauten mit einer entsprechenden Formgebung versehen, so dass durch das Zusammenwirken der Gehäuseeinbauten in dem Gehäuse der Ringdiffusor, der Umlenkkanal und der Rückführkanal gebildet sind.For example, a turbomachine such as a radial turbocompressor is configured as a single shaft compressor having a shaft with impellers threaded thereon and a housing surrounding the impellers. The shaft is mounted radially and axially outside of the housing by means of bearings, wherein flow channels are formed from and to the wheels in the interior of the housing by the provision of housing internals. The wheels are, for example, designed as radial impellers, which have, for example, an axial inflow direction and a radial outflow direction. The impellers are flowed through one after the other so that process gas is gradually compressed from impeller to impeller. On the downstream side of each impeller, a ring diffuser is provided, through which the process gas is guided radially outward. With the help of a Umlenkkanals after the ring diffuser, the process gas is deflected and guided radially inward through a return channel to the next impeller. In the housing, the housing internals are provided with a corresponding shape, so that the ring diffuser, the deflection channel and the return channel are formed by the interaction of the housing internals in the housing.

Die Gehäuseeinbauten sind herkömmlich als Gehäusezwischenböden ausgeführt. Jeder Gehäusezwischenboden ist von zwei Hälften gebildet, so dass der Gehäusezwischenboden horizontal teilbar ist. Somit kann beispielsweise ein Gehäusezwischenboden durch Anbringen der einen Hälfte in das Unterteil des Gehäuses (horizontal geteilte Strömungsmaschine) bzw. in das Unterteil des Innengehäuses (vertikal geteilte Strömungsmaschine) und durch Anlegen der anderen Hälfte in das Oberteil montiert werden.The housing internals are conventionally designed as housing intermediate floors. Each housing intermediate floor is formed by two halves, so that the housing intermediate floor is divisible horizontally. Thus, for example, a housing intermediate bottom by attaching the one half in the lower part of the housing (horizontally divided turbomachine) or in the lower part of Inner housing (vertically divided turbomachine) and are mounted by applying the other half in the upper part.

Aus den Dokumenten WO 2005/045251 A1 und DE 3835341 A1 und DATABASE WPI Week 198051 Thomson Scientific, London sind jeweils Gehäusezwischenböden gemäß dem Oberbebriff des Anspruchs 1 bekannt.From the documents WO 2005/045251 A1 and DE 3835341 A1 and DATABASE WPI Week 198051 Thomson Scientific, London are each known housing intermediate floors according to the Oberbebriff of claim 1.

Die beiden Hälften bilden an ihren Berührflächen eine Teilfuge aus, die aufgrund von Fertigungsungenauigkeiten und/oder einer Deformation der Hälften hervorgerufen von einer Druckbeanspruchung beim Betrieb des Radialturboverdichters auseinanderklaffen und somit gasdurchlässig werden kann. Dadurch stellt sich durch die Teilfuge eine Leckage ein, die insbesondere bei Radialturboverdichtern mit hohen Druckdifferenzen beträchtlich ist. Insbesondere ist die Leckage bei Radialturboverdichtern mit hohem Druckverhältnis und kleinem Fördervolumenstrom nachteilig. Durch die Leckage ist der Wirkungsgrad des Radialturboverdichters reduziert, wodurch die erforderliche Leistungsaufnahme bei Erfüllung von vordefinierten Randbedingungen durch den Radialturboverdichter erhöht ist. Ferner ist die maximal mögliche Vorhersagegenauigkeit bezüglich Druckverhältnis und Fördervolumenstrom des Radialturboverdichters mit höheren Toleranzen behaftet, da die tatsächliche Auswirkung der gegebenenfalls klaffenden Teilfuge auf die Betriebsparameter des Radialturboverdichters nur schwer vorhersagbar ist.The two halves form at their contact surfaces of a parting line, which due to manufacturing inaccuracies and / or deformation of the halves caused by a compressive stress during operation of the radial turbo compressor diverge and thus can be gas permeable. As a result, a leakage occurs through the parting line, which is considerable, especially in radial turbochargers with high pressure differences. In particular, the leakage in Radial turbo compressors with high pressure ratio and small flow rate is disadvantageous. Due to the leakage, the efficiency of the radial turbocompressor is reduced, whereby the required power consumption is increased in the fulfillment of predefined boundary conditions by the radial turbocompressor. Furthermore, the maximum possible prediction accuracy with respect to pressure ratio and flow rate of the radial turbocharger is subject to higher tolerances, since the actual effect of the possibly gaping parting line on the operating parameters of the radial turbocompressor is difficult to predict.

Abhilfe könnte hier beispielsweise das Vorsehen eines O-Rings in der Teilfuge schaffen. Jedoch besteht hierbei der Nachteil, dass bei einer Relativbewegung der Hälften des Gehäusezwischenbodens der O-Ring zerstört werden kann. Ebenfalls sind O-Ringe nicht für alle thermischen und chemischen Belastungen geeignet. Denkbar wäre auch in der Teilfuge die Hälften des Gehäusezwischenbodens mit Nuten zu versehen, in die eine Passfeder eingesetzt ist. Die hierfür notwendigen Passungen für den Einsatz der Passfeder in den Nuten sind fertigungsbedingt nicht oder nur eingeschränkt einzuhalten. Dies hat zur Folge, dass zwischen der Passfeder und den Nuten sich Spiele einstellen, die einen Verbindungskanal zwischen den beiden Seiten des Gehäusezwischenbodens bilden, so dass die Leckage durch die Teilfuge entsprechend nachteilig erhöht wäre.Remedy could provide here, for example, the provision of an O-ring in the parting line. However, there is the disadvantage here that during a relative movement of the halves of the housing intermediate bottom, the O-ring can be destroyed. Also, O-rings are not suitable for all thermal and chemical loads. It would also be conceivable to provide the halves of the housing intermediate bottom with grooves in the parting line into which a feather key is inserted. The necessary fits for the use of the key in the Grooves are due to manufacturing or not to comply with only limited. This has the consequence that set between the feather key and the grooves games that form a connecting channel between the two sides of the housing intermediate floor, so that the leakage would be increased by the parting line correspondingly disadvantageous.

Aufgabe der Erfindung ist es, einen Gehäusezwischenboden für eine Strömungsmaschine und eine Strömungsmaschine mit dem Gehäusezwischenboden zu schaffen, wobei die Strömungsmaschine einen hohen Wirkungsgrad hat.The object of the invention is to provide a housing intermediate bottom for a turbomachine and a turbomachine with the housing intermediate bottom, wherein the turbomachine has a high efficiency.

Erfindungsgemäß wird die Aufgabe durch einen Gehäusezwischenboden der eingangs genannten Art gelöst, welcher die zusätzlichen Merkmale des kennzeichnenden Teils des Anspruchs 1 aufweist.According to the invention the object is achieved by a housing intermediate floor of the type mentioned, which has the additional features of the characterizing part of claim 1.

Bei der Erstmontage des Gehäusezwischenbodens in die Strömungsmaschine ist der Gehäusezwischenboden mit der Teilfuge und den beiden Teilfugenflächen bereitgestellt. Die in der einen Teilfugenfläche ausgebildete Mulde wird mit der Beschichtung versehen, wobei von der einen Teilfugenfläche die Beschichtung vorsteht, so dass die Beschichtung den Überstand hat. Wird der Gehäusezwischenboden in die Strömungsmaschine eingebaut, werden die beiden Teilfugenflächen aneinandergelegt, so dass die Beschichtung an der ihr zugewandten, anderen Teilfugenfläche anliegt. Sobald die Teilfugenflächen einander berührend angeordnet sind, wird die Beschichtung an ihrem Überstand zusammengedrückt. Dadurch liegt die Beschichtung an der ihr zugewandten Teilfugenfläche dicht und flächig an, so dass von der Beschichtung die Teilfuge abgedichtet ist. Somit ist beim Betrieb der Strömungsmaschine eine Leckage von Prozessgas durch die Teilfuge unterbunden oder zumindest vermindert, wodurch die Strömungsmaschine einen verbesserten Wirkungsgrad hat.During the initial assembly of the housing intermediate floor in the turbomachine of the housing intermediate bottom is provided with the parting line and the two parting surfaces. The recess formed in the one part of the joint surface is provided with the coating, wherein protrudes from the one part of the joint surface, the coating, so that the coating has the supernatant. If the intermediate housing bottom is installed in the turbomachine, the two parting surfaces are placed against each other so that the coating rests against the other parting surface facing it. Once the parting surfaces are arranged touching each other, the coating is compressed at its supernatant. As a result, the coating lies tightly and flat against the parting surface facing it, so that the parting line is sealed by the coating. Thus, during operation of the turbomachine, leakage of process gas through the parting line is prevented or at least reduced, as a result of which the turbomachine has improved efficiency.

In der Strömungsmaschine können fertigungsbedingt Bauungenauigkeiten auftreten, die in der zusammengebauten Strömungsmaschine dazu führen, dass die Teilfugenflächen nicht vollständig aneinander liegen. Dies hat zur Folge, dass an der Teilfuge ein Spalt ausgebildet ist, der beim Betrieb der Strömungsmaschine zu einer Leckage von Prozessgas führt. Dadurch, dass im Demontagezustand des Gehäusezwischenbodens die Beschichtung mit dem Überstand versehen ist, ist es möglich, dass, wenn der Gehäusezwischenboden montiert ist und die beiden Teilfugenflächen in entsprechendem bautoleranzbedingten Abstand angeordnet sind, die Beschichtung diesen Abstand überbrücken kann. Dadurch ist auch bei großen Bauungenauigkeiten der Strömungsmaschine der Gehäusezwischenboden im Montagezustand an der Teilfuge von der Beschichtung abgedichtet, so dass derartige Bauungenauigkeiten nicht zu einer Verschlechterung der Leistungsparameter der Strömungsmaschine führen können. Außerdem können die Leistungsparameter der Strömungsmaschine mit herkömmlichen Methoden besser vorhergesagt werden, so dass die Strömungsmaschine zielsicher ausgelegt werden kann. Dadurch ist das Risiko vermindert, dass bei einem eventuellen Probelauf der Strömungsmaschine festgestellt wird, dass die Strömungsmaschine die geforderten Leistungsparameter nicht erfüllen kann. Hierfür wären entsprechende Nachbesserungsaktionen an der Strömungsmaschine notwendig, die erfindungsgemäß unterbleiben können.In the turbomachine manufacturing inaccuracies due to construction can occur, which in the assembled turbomachine cause the parting surfaces are not completely together. This has the consequence that at the parting line, a gap is formed, which leads to a leakage of process gas during operation of the turbomachine. Characterized in that in the disassembled state of the housing intermediate floor the coating is provided with the supernatant, it is possible that, when the housing intermediate bottom is mounted and the two parting surfaces are arranged at a corresponding tolerances due distance, the coating can bridge this distance. As a result, even in the case of major inaccuracies in construction of the turbomachine, the intermediate housing bottom is sealed off from the coating in the assembled state at the parting line, so that such structural inaccuracies can not lead to a deterioration in the performance parameters of the turbomachine. In addition, the performance parameters of the turbomachine can be better predicted by conventional methods, so that the turbomachine can be designed accurately. As a result, the risk is reduced that it is determined in a possible test run the turbomachine that the turbomachine can not meet the required performance parameters. For this purpose, corresponding rectification actions on the turbomachine would be necessary, which can be omitted according to the invention.

Bevorzugt ist die Beschichtung eine Honeycomb-Schicht. Die Honeycomb-Schicht kann kostengünstig aus entsprechend geformten Blechstreifen hergestellt werden, mit denen eine Wabenstruktur der Honeycomb-Schicht gebildet ist. Die Wabenstruktur ist derart ausgebildet, dass die Blechstreifen im Montagezustand des Gehäusezwischenbodens von der anderen Teilfugenfläche gestaucht werden. Die Honeycomb-Schicht ist bevorzugt in die Mulde gelötet.Preferably, the coating is a honeycomb layer. The honeycomb layer can be produced inexpensively from correspondingly shaped metal strips, with which a honeycomb structure of the honeycomb layer is formed. The honeycomb structure is formed such that the sheet metal strips are compressed in the assembled state of the housing intermediate bottom of the other part of the joint surface. The honeycomb layer is preferably soldered into the trough.

Als Alternative und/oder Ergänzung ist bevorzugt die Beschichtung eine flamm- oder plasmagespritzte Spritzschicht. Die Spritzschicht ist bevorzugt auf Ni-Al-Cr-Basis.As an alternative and / or supplement, the coating is preferably a flame-sprayed or plasma-sprayed sprayed coating. The sprayed layer is preferably Ni-Al-Cr-based.

Ferner ist es bevorzugt, dass im Bereich der Überdeckung in der einen Teilfugenfläche die eine Mulde und in der anderen Teilfugenfläche die andere Mulde vorgesehen ist, in denen jeweils eine der Beschichtungen untergebracht ist, wobei die Beschichtungen sich einander überlappend angeordnet sind.Further, it is preferred that in the region of the overlap in the one part of the joint surface, a trough and in the other part of the joint surface, the other trough is provided, in each of which one of the coatings is housed, wherein the coatings are arranged overlapping each other.

Bevorzugt hierbei ist es, dass die Beschichtung der einen Teilfugenfläche die Honeycomb-Schicht ist und die Beschichtung der anderen Teilfugenfläche die Spritzschicht ist. Im Demontagezustand des Gehäusezwischenbodens ist an der einen Teilfugenfläche die Honeycomb-Schicht mit ihrem Überstand und an der anderen Teilfugenfläche die Spritzschicht vorgesehen. Werden bei der Montage die Teilfugenflächen aneinandergelegt, so drückt sich gegebenenfalls unter eigener Deformation die Honeycomb-Schicht in die Spritzschicht ein, so dass die Honeycomb-Schicht mit der Spritzschicht eine dichte Struktur in der Teilfuge bildet.It is preferred here for the coating of one partial joint surface to be the honeycomb layer and for the other partial joint surface to be the sprayed layer. In the disassembly state of the housing intermediate floor, the honeycomb layer is provided with its supernatant on one part of the joint surface and the sprayed layer on the other part of the joint surface. If the part-joint surfaces are placed against one another during assembly, the honeycomb layer is optionally pressed into the sprayed layer under its own deformation, so that the honeycomb layer forms a dense structure in the parting joint with the sprayed layer.

Die Dicke der Spritzschicht ist bevorzugt an der anderen Teilfugenfläche mindestens so groß wie der Überstand der Honeycomb-Schicht dimensioniert, so dass im Montagezustand des Gehäusezwischenbodens die Honeycomb-Schicht in die Spritzschicht eingedrückt ist. Dadurch erstreckt sich die Spritzschicht im Montagezustand des Gehäusezwischenbodens lediglich in den Wabenzwischenräumen der Honeycomb-Schicht, da die Honeycomb-Schicht an den Grund der Mulde - mit einem gewissen Abstand für Fertigungstoleranzen - der anderen Teilfugenfläche anstößt. Dadurch ist die Teilfuge mit der Honeycomb-Schicht und der Spritzschicht stabil und dicht abgedichtet. Alternativ bevorzugt ist der Überstand an der Spritzschicht ausgeführt.The thickness of the sprayed layer is preferably dimensioned at the other parting surface at least as large as the supernatant of the honeycomb layer, so that in the assembled state of the housing intermediate bottom, the honeycomb layer is pressed into the sprayed layer. As a result, the spray layer extends in the assembled state of the housing intermediate base only in the honeycomb interstices of the honeycomb layer, since the honeycomb layer abuts the bottom of the trough - with a certain margin for manufacturing tolerances - of the other part joint surface. As a result, the parting line with the honeycomb layer and the sprayed layer is stable and tightly sealed. Alternatively, preferably, the supernatant is carried out on the sprayed layer.

Bevorzugt ist es, dass der Gehäusezwischenboden aus einer Unterhälfte und einer Oberhälfte gebildet ist, die im Montagezustand die Teilfuge in einer Ebene bilden, in der die Drehachse der Strömungsmaschine liegt. Dadurch ist der Gehäusezwischenboden aus den in etwa gleich großen Hälften gebildet, so dass der Gehäusezwischenboden einfach montierbar und demontierbar ist. Bevorzugt ist es, dass an der Unterhälfte die eine Teilfugenfläche mit der Honeycomb-Schicht und an der Oberhälfte die andere Teilfugenfläche mit der Spritzschicht vorgesehen ist. Alternativ bevorzugt ist es, dass an der Oberhälfte die eine Teilfugenfläche mit der Honeycomb-Schicht und an der Unterhälfte die andere Teilfugenfläche mit der Spritzschicht vorgesehen ist.It is preferred that the housing intermediate bottom is formed from a lower half and an upper half, which in the assembled state form the parting line in a plane in which the axis of rotation of the turbomachine lies. As a result, the housing intermediate bottom is formed from the approximately equal halves, so that the housing intermediate floor is easy to assemble and disassemble. It is preferred that on the lower half of the one part of the joint surface with the honeycomb layer and on the upper half of the other part of the joint surface is provided with the sprayed layer. Alternatively, it is preferred that on the upper half of a parting surface with the Honeycomb layer and on the lower half of the other part of the joint surface is provided with the sprayed layer.

Bevorzugt ist es, dass die Strömungsmaschine ein Radialturboverdichter ist, der eine Radialturboverdichterstufe mit einem Ringdiffusor, einem Umlenkkanal und einem Rückführkanal aufweist, die von mindestens zwei Gehäusezwischenböden gebildet sind.It is preferred that the turbomachine is a radial turbocompressor having a radial turbocompressor stage with a ring diffuser, a deflection channel and a return channel, which are formed by at least two housing intermediate floors.

Im Folgenden wird eine bevorzugte Ausführungsform des erfindungsgemäßen Gehäusezwischenbodens und des erfindungsgemäßen Radialturboverdichters anhand der beigefügten schematischen Zeichnungen erläutert. Es zeigt:

Fig. 1
einen Längsschnitt eines Radialturboverdichters, horizontal geteilt,
Fig. 2
einen Längsschnitt eines Radialturboverdichters, vertikal geteilt,
Fig. 3
eine Teilfuge von Gehäusezwischenböden,
Fig. 4 und 5
einen Detailquerschnitt der Teilfuge des Gehäusezwischenbodens und
Fig. 6 und 7
Details der Draufsicht der Teilfuge des Gehäusezwischenbodens.
In the following, a preferred embodiment of the housing intermediate floor according to the invention and the radial turbo-compressor according to the invention will be explained with reference to the accompanying schematic drawings. It shows:
Fig. 1
a longitudinal section of a radial turbocompressor, horizontally divided,
Fig. 2
a longitudinal section of a radial turbocompressor, vertically divided,
Fig. 3
a parting line of housing intermediate floors,
4 and 5
a detail cross-section of the parting line of the housing intermediate floor and
6 and 7
Details of the plan view of the parting line of the housing intermediate floor.

Wie es aus Fig. 1 und 2 ersichtlich ist, weist ein Radialturboverdichter 1 ein Gehäuse 2 bzw. ein Gehäuse 2 und ein Innengehäuse 33 und einen Rotor 3 auf. An dem Gehäuse 2 ist ein Saugstutzen 4 und ein Druckstutzen 5 vorgesehen, wobei der Saugstutzen 4 im Inneren des Gehäuses 2 in einen Einlauf 6 mündet und eine im Inneren des Gehäuses 2 vorgesehene Austrittsspirale 7 in den Druckstutzen 5 mündet.Like it out Fig. 1 and 2 a radial turbo compressor 1 comprises a housing 2 or a housing 2 and an inner housing 33 and a rotor 3. On the housing 2, a suction nozzle 4 and a discharge nozzle 5 is provided, wherein the suction nozzle 4 opens in the interior of the housing 2 in an inlet 6 and an opening provided in the interior of the housing 2 exit spiral 7 opens into the discharge nozzle 5.

In dem Radialturboverdichter 1 gemäß Fig. 1 und 2 sind sechs Radialturboverdichterstufen 8 ausgebildet, die jeweils von einem Laufrad 9 des Rotors 3 gebildet sind. Jedes Laufrad 9 hat eine in Richtung der Drehachse 24 des Rotors 3 zeigende, axiale Zuströmrichtung und eine radiale nach außen zeigende Abströmrichtung. In jeder Radialturboverdichterstufe 8 ist ein Ringdiffusor 10, der radial nach außen innerhalb des Gehäuses 2 verläuft und sich stromab des Laufrads 9 sich diesem anschließt. Dem Ringdiffusor 10 folgt in Strömungsrichtung ein Umlenkkanal 11, in dem Prozessgas von dem Ringdiffusor 10 in einen Rückführkanal 12 umgelenkt wird, in dem das Prozessgas radial nach innen zu dem Laufrad 9 der nächsten Radialturboverdichterstufe 8 strömt.In the radial turbo compressor 1 according to Fig. 1 and 2 are formed six radial turbo compressor stages 8, each of an impeller 9 of the rotor 3 are formed. Each impeller 9 has an axial inflow direction pointing in the direction of the rotation axis 24 of the rotor 3 and a radial outflow direction pointing outwards. In each Radialturboverdichterstufe 8 is a ring diffuser 10, which extends radially outward within the housing 2 and downstream of the impeller 9 this is followed. The annular diffuser 10 is followed in the flow direction by a deflection channel 11, in which process gas is deflected by the ring diffuser 10 into a return channel 12, in which the process gas flows radially inwards towards the impeller 9 of the next radial turbocompressor stage 8.

In dem Gehäuse 2 ist für die Radialturboverdichterstufe 8 ein erster Gehäusezwischenboden 13 und ein zweiter Gehäusezwischenboden 14 vorgesehen, die mit einer derartigen Kontur versehen und zueinander derart angeordnet sind, dass unter Zusammenwirken des ersten Gehäusezwischenbodens 13 und des zweiten Gehäusezwischenbodens 14 der Ringdiffusor 10, der Umlenkkanal 11 und der Rückführkanal 12 in dem Gehäuse 2 ausgebildet sind.In the housing 2, a first intermediate housing bottom 13 and a second housing intermediate bottom 14 is provided for the Radialturboverdichterstufe 8, which are provided with such a contour and arranged to each other such that under cooperation of the first housing intermediate bottom 13 and the second housing intermediate bottom 14 of the ring diffuser 10, the deflection channel 11 and the return channel 12 are formed in the housing 2.

Der erste Gehäusezwischenboden 13 hat eine zylindrische Außenseite 15 und liegt an der Innenseite des Gehäuses 2 an, wobei der erste Gehäusezwischenboden 13 mit einem Ringsteg 16 an dem Gehäuse 2 verriegelt ist. Der erste Gehäusezwischenboden 13 und der zweite Gehäusezwischenboden 14 sind in ihrem Aufbau ähnlich, so dass im Folgenden lediglich auf den ersten Gehäusezwischenboden 13 Bezug genommen wird. Der erste Gehäusezwischenboden 13 weist eine Unterhälfte 17 und eine Oberhälfte 18 auf, so dass von der Unterhälfte 17 und der Oberhälfte 18 eine Teilfuge 19 ausgebildet ist. Die Unterhälfte 17 und die Oberhälfte 18 sind im Wesentlichen geometrisch gleich ausgebildet, so dass die Teilfuge 19 in einer Ebene liegt, in der die Drehachse 24 des Radialturboverdichters 11 angesiedelt ist. Die Unterhälfte 17 weist eine Teilfugenfläche 20 und die Oberhälfte 18 weist eine Teilfugenfläche 21 auf, wobei die Teilfugenflächen 20, 21 in ihrem Umriss identisch ausgebildet sind, so dass, wenn die Unterhälfte 17 an die Oberhälfte 18 unter Ausbildung der Teilfuge 19 angelegt ist, die Teilfugenflächen 20 und 21 sich vollständig überdecken.The first housing intermediate bottom 13 has a cylindrical outer side 15 and is located on the inside of the housing 2, wherein the first housing intermediate bottom 13 is locked with an annular web 16 on the housing 2. The first housing intermediate bottom 13 and the second housing intermediate bottom 14 are similar in their construction, so that in the following only the first housing intermediate bottom 13 is referred to. The first housing intermediate bottom 13 has a lower half 17 and an upper half 18, so that of the lower half 17 and the upper half 18, a parting line 19 is formed. The lower half 17 and the upper half 18 are formed substantially geometrically the same, so that the parting line 19 lies in a plane in which the axis of rotation 24 of the radial turbocompressor 11 is located. The lower half 17 has a part-joint surface 20 and the upper half 18 has a part-joint surface 21, wherein the part-joint surfaces 20, 21 formed identically in their outline are, so that when the lower half 17 is applied to the upper half 18 to form the parting line 19, the parting surfaces 20 and 21 completely overlap.

In Fig. 3 ist eine Draufsicht der Teilfugenfläche 20 der Unterhälfte 17 gezeigt. Im Innenbereich der Teilfugenfläche 20 ist eine Mulde 22 vorgesehen, deren Umrandung von der Umrandung der Teilfugenfläche 20 stets im Abstand angeordnet ist. So ist die Mulde 22 vollständig von der Teilfugenfläche 20 umgeben. In der Mulde 22 ist eine Honeycomb-Schicht 23 untergebracht, die die Mulde 22 vollständig ausfüllt. Wie es in Fig. 6 und 7 gezeigt ist, ist die Honeycomb-Schicht 23 aus Blechstreifen 25 aufgebaut, die wellenartig geformt sind und unter Ausbildung von Waben zusammengefügt sind. An der Umrandung der Mulde 22 ist ein Lot 27 vorgesehen, mit dem die Honeycomb-Schicht 23 in der Mulde 22 befestigt ist.In Fig. 3 a plan view of the parting surface 20 of the lower half 17 is shown. In the interior of the parting surface 20, a trough 22 is provided, the border of which is always arranged at a distance from the edge of the parting surface 20. Thus, the trough 22 is completely surrounded by the parting surface 20. In the trough 22, a honeycomb layer 23 is housed, which completely fills the trough 22. As it is in 6 and 7 is shown, the honeycomb layer 23 is constructed of metal strips 25 which are wave-shaped and are joined together to form honeycomb. At the border of the trough 22, a solder 27 is provided, with which the honeycomb layer 23 is secured in the trough 22.

Wie es in Fig. 4 gezeigt ist, hat die Honeycomb-Schicht 23 eine Steghöhe 28, die größer ist als die Tiefe der Mulde 22. Dadurch ergibt sich an der Honeycomb-Schicht 23 ein Überstand 29, der von der Teilfugenfläche 20 vorsteht. Die im Montagezustand des Gehäusezwischenbodens 13 der Teilfugenfläche 20 der Unterhälfte 17 zugewandte Teilfugenfläche 21 der Oberhälfte 18 weist eine Mulde 30 auf, deren Umrandung parallel zu der Umrandung der Mulde 22 verläuft. Tendenziell ist die Mulde 30 in ihrer Erstreckung entlang der Teilfugenfläche 21 größer ausgebildet als die Mulde 22, so dass die Mulde 30 die Mulde 22 vollständig überdeckt. Dadurch ist es unterbunden, dass die Honeycomb-Schicht 23, die in der Mulde 22 angeordnet ist, mit dem Rand der Mulde 30 und der Teilfugenfläche 20 in Kontakt kommt.As it is in Fig. 4 is shown, the honeycomb layer 23 has a ridge height 28 which is greater than the depth of the trough 22. This results in the honeycomb layer 23, a projection 29 which projects from the parting surface 20. The in the assembled state of the housing intermediate bottom 13 of the parting surface 20 of the lower half 17 facing parting surface 21 of the upper half 18 has a trough 30, the edge of which runs parallel to the border of the trough 22. The trough 30 tends to be larger in its extent along the parting surface 21 than the trough 22, so that the trough 30 completely covers the trough 22. Thereby, it is prevented that the honeycomb layer 23, which is arranged in the trough 22, comes into contact with the edge of the trough 30 and the parting surface 20.

In der Mulde 30 ist eine Spritzschicht 31 vorgesehen, die die Mulde 30 vollständig ausfüllt. Die Tiefe der Mulde 30 ergibt eine Schichtdicke 32, die fertigungsbedingt entweder gleich dem Überstand 29 oder größer ausgebildet ist.In the trough 30, a spray layer 31 is provided, which completely fills the trough 30. The depth of the trough 30 results in a layer thickness 32, which is formed due to production either equal to the supernatant 29 or greater.

Beim Montieren des Gehäusezwischenbodens 13 wird die Oberhälfte 18 mit ihrer Teilfugenfläche 21 auf die Teilfugenfläche 20 der Unterhälfte 17 gesetzt, wobei die Mulden 22 und 30 zur Überdeckung kommen. Aufgrund des Überstands 29 der an der Mulde 22 vorgesehenen Honeycomb-Schicht 23 trägt sich diese in die Spritzschicht 31 ein. Dadurch ist in der Teilfuge 19 mit der Honeycomb-Schicht 23 und der Spritzschicht 31 eine dichte und stabile Konfiguration geschaffen.When mounting the housing intermediate bottom 13, the upper half 18 is set with its parting surface 21 on the parting surface 20 of the lower half 17, wherein the troughs 22 and 30 come to cover. Due to the supernatant 29 of the honeycomb layer 23 provided on the trough 22, this wears into the sprayed layer 31. As a result, a dense and stable configuration is created in the parting line 19 with the honeycomb layer 23 and the sprayed layer 31.

Claims (11)

  1. Intermediate housing floor for a fluid kinetic machine (1), having a part joint (19), at which the intermediate housing floor (13, 14) can be divided during the mounting into and/or dismantling from the fluid kinetic machine (1), and which part joint (19) is formed by at least two part joint faces (20, 21) which overlap one another on mutually facing sections (17, 18) of the intermediate housing floor (13, 14), characterized in that a recess (22, 30) is provided in the region of the overlap in at least the one part joint face (20, 21), in which recess (22, 30) a coating (23, 31) is accommodated which protrudes from the one part joint face (20, 21) as a projection (29) in the dismantled state of the intermediate housing floor (13, 14), in which state the intermediate housing floor (13, 14) is divided at the part joint (19), with the result that, in the mounted state of the intermediate housing floor (13, 14), the coating (22, 30) bears against the other part joint face (20, 21) which faces the one part joint face (20, 21), as a result of which the part joint (19) is sealed, the one recess (22) being provided in the one part joint face (20) in the region of the overlap and the other recess (30) being provided in the other part joint face (21), in which recesses (22, 30) in each case one of the coatings (23, 30) is accommodated, the coatings (23, 30) being arranged so as to overlap one another.
  2. Intermediate housing floor according to Claim 1, the coating being a honeycomb layer (23).
  3. Intermediate housing floor according to Claim 2, the honeycomb layer (23) being soldered into the recess (22).
  4. Intermediate housing floor according to one of Claims 1 to 3, the coating being a flame-sprayed or plasma-sprayed coating (30).
  5. Intermediate housing floor according to Claim 4, the sprayed layer (30) having an Ni-Al-Cr basis.
  6. Intermediate housing floor according to Claim 1, the coating of the one part joint face (20) being the honeycomb layer (23) and the coating of the other part joint face (21) being the sprayed layer (30).
  7. Intermediate housing floor according to Claim 6, the layer thickness (32) of the sprayed layer (30) of the other part joint face (21) being dimensioned to be at least as large as the projection (29) of the honeycomb layer (23), with the result that the honeycomb layer (23) is pressed into the sprayed layer (30) in the mounted state of the intermediate housing floor (13, 14).
  8. Intermediate housing floor according to one of Claims 1 to 7, the intermediate housing floor (13, 14) being formed from a lower half (17) and an upper half (18) which, in the mounted state, form the part joint (19) in a plane, in which the rotational axis (24) of the fluid kinetic machine (1) lies.
  9. Intermediate housing floor according to Claim 8, the one part joint face (20) with the honeycomb layer (23) being provided on the lower half (17), and the other part joint face (21) with the sprayed layer (31) being provided on the upper half (18).
  10. Fluid kinetic machine having an intermediate housing floor (13, 14) according to one of Claims 1 to 9.
  11. Fluid kinetic machine according to Claim 10, the fluid kinetic machine being a radial turbocompressor (1) which has a radial turbocompressor stage (8) with an annular diffuser (10), a deflection channel (11) and a return channel (12) which are formed by at least two intermediate housing floors (13, 14).
EP09782156.5A 2008-09-03 2009-08-25 Intermediate housing floor for a fluid kinetic machine Not-in-force EP2321534B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008045669 2008-09-03
PCT/EP2009/060922 WO2010026077A1 (en) 2008-09-03 2009-08-25 Intermediate housing floor for a fluid kinetic machine

Publications (2)

Publication Number Publication Date
EP2321534A1 EP2321534A1 (en) 2011-05-18
EP2321534B1 true EP2321534B1 (en) 2016-11-16

Family

ID=41165166

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09782156.5A Not-in-force EP2321534B1 (en) 2008-09-03 2009-08-25 Intermediate housing floor for a fluid kinetic machine

Country Status (4)

Country Link
US (1) US8142151B2 (en)
EP (1) EP2321534B1 (en)
CN (1) CN102144098B (en)
WO (1) WO2010026077A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2623730A1 (en) * 2012-02-02 2013-08-07 Siemens Aktiengesellschaft Flow engine component with joint and steam turbine with the flow engine component
JP6963471B2 (en) * 2017-11-09 2021-11-10 三菱重工コンプレッサ株式会社 Rotating machine
FR3096728B1 (en) * 2019-05-29 2022-01-28 Thermodyn Compressor cartridge, motor-compressor and method of assembling such a motor-compressor

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB168772A (en) 1920-08-19 1921-09-15 Gen Electric Improvements in and relating to centrifugal compressors and the like
US3390830A (en) 1967-04-14 1968-07-02 Kahane Wilhelm Sealing of horizontally-split centrifugal compressors
DE2542336C3 (en) 1975-09-23 1978-06-15 Igor Martynovitsch Kalnin Multi-stage centrifugal compressor
SU732556A1 (en) 1978-07-18 1980-05-05 Ордена Ленина И Ордена Трудового Красного Знамени Производственное Объединение "Невский Завод" Им. В.И.Ленина Horizontally split stator of turbomachine
CH676487A5 (en) 1988-10-19 1991-01-31 Proizv Ob Nevsky Z Im V I
CN1042758A (en) * 1988-11-18 1990-06-06 列宁联合企业涅弗斯克工厂 Centrifugal compressor with horizontal dismountable plane
CN2075700U (en) * 1989-07-14 1991-04-24 徐晓强 High efficient gas turbine
JP3294491B2 (en) * 1995-12-20 2002-06-24 株式会社日立製作所 Turbocharger for internal combustion engine
ITMI20011348A1 (en) * 2001-06-27 2002-12-27 Nuovo Pignone Spa BALANCING PISTON FOR CENTRIFUGAL COMPRESSORS WITH DIVERGENT CELLETTE SEAL
ITMI20032149A1 (en) * 2003-11-07 2005-05-08 Nuovo Pignone Spa MULTI-STAGE CENTRIFUGAL COMPRESSOR WITH HORIZONTALLY OPENABLE CASE

Also Published As

Publication number Publication date
CN102144098B (en) 2013-08-28
CN102144098A (en) 2011-08-03
EP2321534A1 (en) 2011-05-18
US20110158794A1 (en) 2011-06-30
WO2010026077A1 (en) 2010-03-11
US8142151B2 (en) 2012-03-27

Similar Documents

Publication Publication Date Title
EP2886961B1 (en) Washer of a combustion chamber shingle of a gas turbine
EP2647795B1 (en) Seal system for a turbo engine
EP3369996B1 (en) Combustion chamber shingle arrangement of a gas turbine
EP2478186B1 (en) Rotor of a turbomachine
EP2808559B1 (en) Structure assembly for a turbomachine
EP3273001B1 (en) Methods of manufacturing a tandem guide vane segment
EP2696029A1 (en) Blade tow with side wall contours and fluid flow engine
EP2993356A1 (en) Radial compressor stage
EP2321534B1 (en) Intermediate housing floor for a fluid kinetic machine
EP2411631B1 (en) Sealplate and rotor blade system
DE102019210699A1 (en) Intermediate element for a blade-rotor disk connection in a rotor of a turbomachine and a rotor for a turbomachine
EP2232080B1 (en) Impeller for a pump
EP2218918A1 (en) Axial turbo compressor for a gas turbine with low blade-tip leakage losses and diffuser losses
EP1995413B1 (en) Gap seal for airfoils of a turbomachine
EP2526263B1 (en) Housing system for an axial turbomachine
EP3236011A1 (en) Rotor with overhang on rotor blades for a securing element
EP2808557A1 (en) Structure assembly for a turbomachine
DE102018210600A1 (en) COAT RING ARRANGEMENT FOR A FLOWING MACHINE
EP3159487B1 (en) Stator of a turbine of a gas turbine with improved cooling air conduction
EP2871418B1 (en) Gas turbine combustion chamber and method for its manufacture
EP3737865A1 (en) Turbomachine inner housing
EP2980481A1 (en) Aircraft gas turbine having a seal for sealing a spark plug to the combustor chamber wall of a gas turbine
EP3935283B1 (en) Side channel blower
EP3581760B1 (en) Blade for a turbomachine
EP2811117A2 (en) Shroud assembly for a turbo engine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20110216

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/08 20060101ALI20160512BHEP

Ipc: F04D 29/62 20060101ALI20160512BHEP

Ipc: F04D 29/42 20060101ALI20160512BHEP

Ipc: F04D 17/12 20060101ALI20160512BHEP

Ipc: F04D 29/44 20060101ALI20160512BHEP

Ipc: F04D 29/16 20060101ALI20160512BHEP

Ipc: F04D 1/06 20060101AFI20160512BHEP

INTG Intention to grant announced

Effective date: 20160608

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 846221

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161215

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502009013383

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20161116

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170216

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170217

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170316

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502009013383

Country of ref document: DE

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170216

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

26N No opposition filed

Effective date: 20170817

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502009013383

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170825

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170831

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170831

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170831

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20180430

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170825

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170825

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170825

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180301

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170831

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170831

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 846221

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170825

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170825

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20090825

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20161116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161116

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20170316