EP3581802A1 - Arrangement and method for the support of the impeller of a radial turbomachine - Google Patents

Abstract

Arrangement (AR), comprising - radial turbine machine impeller (IMP), - housing (CAS) with axial and radial flow opening (INL, EXT), - shaft (SH), which extends along an axis (X), - at least one radial bearing (RB ), - at least one shaft seal (SHS), the radial turbomachine impeller (IMP) being detachably attached to one shaft end (SE) of the shaft (SH), the radial turbomachine impeller (IMP) being located in an interior (INS) of the housing (CAS) , wherein the shaft (SH) extends through a through opening (TH) provided in a first housing wall (CW1) of the housing (CAS), sealed by means of the shaft seal (SHS), the shaft seal (SHS) axially between the radial turbine engine impeller (IMP ) and the radial bearing (RB) on the shaft (SH) is arranged. To reduce the assembly and maintenance costs, at least two closable openings (OP1, OP2, OP3) are provided in the housing wall (CW1), with one support element (SP1, SP2, SP3) through the closable opening (OP1, OP2, OP3). protrudes through it and contacts the radial turbomachine impeller (IMP) to intercept at least part of the weight.

Description

• ein Radialturbomaschinenlaufrad,
• ein Gehäuse mit axialer und radialer Strömungsöffnung,
• eine Welle, die sich entlang einer Achse erstreckt,
• mindestens ein Radiallager,
• mindestens eine Wellendichtung,

wobei das Radialturbomaschinenlaufrad an einem Wellenende der Welle lösbar angebracht ist,
wobei das Radialturbomaschinenlaufrad sich in einem Inneren des Gehäuses befindet,
wobei die Welle sich durch eine Durchführungsöffnung, vorgesehen in einer ersten Gehäusewand des Gehäuses, abgedichtet mittels der Wellendichtung erstreckt,
wobei die Wellendichtung axial zwischen dem Radialturbomaschinenlaufrad und dem Radiallager an der Welle angeordnet ist.The invention relates to an arrangement comprising

• a radial turbine engine impeller,
• a housing with axial and radial flow opening,
• a shaft that extends along an axis,
• at least one radial bearing,
• at least one shaft seal,

the radial turbine engine impeller being releasably attached to a shaft end of the shaft,
the radial turbine engine impeller being located in an interior of the housing,
wherein the shaft extends through a through opening provided in a first housing wall of the housing, sealed by means of the shaft seal,
wherein the shaft seal is arranged axially between the radial turbine engine impeller and the radial bearing on the shaft.

Furthermore, the invention relates to a method for disassembling or assembling such an arrangement.

Arrangements of the type defined at the outset are generally used for impellers which are arranged or mounted on the fly. This means that the bearing of the shaft or the rotor - in particular the radial bearing of the rotor - is only on one axial side of the impeller / the impellers. Accordingly, the radial turbine engine impeller is attached to a shaft end of the shaft. Such an arrangement, as is also known from so-called geared turbo compressors, can also be used independently of a geared turbo compressor - that is, driven or driving in another way.

In the typical use of the overhung radial compressor impellers or radial turbo machine impellers for the arrangement according to the invention, these radial turbo machine impellers - impellers for short - are connected axially, preferably by means of a Hirth toothing - to a shaft end. A shaft seal, for example a gas seal or mechanical seal (fluid seal) and then a radial bearing are provided in the axial continuation of the shaft. In addition to the radial bearing, an axial bearing is regularly provided, which absorbs at least part of the thrust arising from the impeller due to the pressure difference.

With such a flying arrangement, the housing that surrounds the impeller or the impellers is generally formed in one piece in the circumferential direction. This advantageous embodiment is made possible because there are no obstructing components, in particular storage, on one side due to the flying mounting, which would prevent the housing from being axially joined to the shaft end. For reasons of assembly, the housing can optionally have a substantially radial parting joint or a cover with a radial joint course. Basically, an essentially axial-radial parting line is also conceivable, but this option does not take advantage of all the advantages of the invention.

Conventionally, the shaft seal and the shaft bearing of the shaft, at the shaft end of which the impeller or the arrangement is provided, cannot be easily dismantled or assembled, but dismantling begins conventionally axially on the part of the impeller and a sequence of assembly usually closes with the Assemble the impeller if other components, such as pipes, are not used.

The gas seal is dismantled or assembled from the process gas side or from the side of the axial inflow into the compressor, since the shaft is anchored in the gearbox on the drive side, for example in the case of a geared compressor.

In the individual application of a flying stage or an arrangement according to the invention, this would also be connected to the drive machine or another work machine in the line with a coupling, so that the gas seal is also installed on the process gas side in such a case.

Implementation of the invention in connection with a single-shaft compressor is particularly advantageous. Geared turbo compressors are already known, for example, from the following publications: EP3106670-A1 . EP3061991-A1 . EP3045686-A1 . WO2016091495-A1 . WO2016062549-A1 . WO2016046037-A1 . WO2015043879-A1 . WO2014195390-A1 . WO2012104366-A1 . WO2012104153-A1 ,

A decisive disadvantage of a generic arrangement of conventional design is that for assembly, disassembly or inspection, in particular the gas seal, the bearing or other components that are located axially behind the impeller, either the entire drive train or output train on which the Impeller of the compressor is attached axially at the end, must be dismantled or that the entire compressor of the generic arrangement must be dismantled from the shaft end and in itself in order to reach the corresponding components located axially behind the impeller. The effort involved is extremely time and cost intensive, so that maintenance and service costs undesirably reduce the likelihood of sales of such arrangements.

Based on the problems and disadvantages of the conventional design, it is the object of the invention to develop an arrangement of the type defined in the introduction in such a way that the assembly effort and the maintenance costs are reduced.

To achieve the object, the invention proposes an arrangement of the type defined in the introduction with the additional features of claim 1. In addition, according to the procedural claims proposed a method for disassembly and assembly according to the invention.

By means of the at least two closable openings in the housing wall, one support element can be inserted per opening, which contacts the radial turbine engine impeller to intercept at least part of the weight. These at least two - preferably several - support elements make it possible, on the one hand, to hold the impeller in an axial position, at the same time preventing the impeller from tipping and fixing the radial position of the impeller. Accordingly, when disassembling and assembling at least one bearing or a shaft seal of the compressor from the shaft, it is possible not to have to dismantle the compressor itself, since the impeller is in the axial and radial - or spatial - position by the corresponding support elements is held, preferably exactly at the point where the shaft end would or should fix the impeller in a certain position when the machine is fully assembled. It is thus possible, the bearing and shaft seal and even the impeller itself together with the housing and possibly other peripherals using the support elements according to the invention, which are introduced through corresponding openings in the interior of the housing for contacting and supporting the impeller, essentially unchanged to assemble or disassemble and in this way save a multitude of operations that are necessary without the corresponding support elements, so that there are no collisions between limits of the interior of the housing due to an impeller that is no longer spatially held in a specific position. In addition to axial contact surfaces, the support elements preferably also have at least partially radial support arrangements, for example radial contact surfaces or contact surfaces arranged obliquely between axial alignment and radial alignment, which contact on corresponding oblique surfaces of the impeller. Finally, the support elements or the contact surfaces of the support elements and the corresponding ones Surfaces formed on the impeller in such a way that a translational or rotary spatial movement is not possible if the shaft end is no longer supported.

It is particularly preferred here if at least two closable openings, the first closable opening and a second closable opening are provided in the first housing wall. In this case, it makes sense if a second support element is provided projecting through the second closable opening and the radial turbine machine impeller contacts a part of the weight force in a circumferential direction at a distance from the first support element.

A variant is particularly preferred in which a third closable opening is provided in the first housing wall, the arrangement being designed for an operating set-up in which the first support element and the second support element support the radial turbine engine impeller against the weight from below and the third support element secures the radial turbine engine impeller spaced from the other two support elements in the circumferential direction against tipping over. In this context, it is preferred if the arrangement has exactly three support elements and corresponding openings in the housing wall.

An advantageous development of the invention provides that at least one support element has a radial adjustment possibility for a contact surface for contacting the radial turbomachine impeller. This radial adjustment option facilitates the insertion of the corresponding support elements through the corresponding openings, since the insertion, which is usually carried out axially, can take place independently of the contacting of the impeller. A particularly preferred embodiment variant is one in which each support element has at least two contact surfaces, at least one of which is configured obliquely that this inclined contact surface with increasing radial approach to the impeller results in both radial and axial bracing or fixing of the impeller.

A further advantageous development of the invention provides that at least one support element, preferably all support elements, has an axial adjustment facility for one, preferably all, contact surfaces for contacting the radial turbine machine impeller of the corresponding support element.

Particularly preferably, at least two of three support elements have radial position adjustment devices and preferably at least some - particularly preferably all - support elements are designed to be adjustable in their axial position of the contact surfaces. The axial adjustability can be designed to be combinable with the introduction of the support elements into the corresponding openings of the housing wall, preferably in the axial direction.

The radial adjustability of the contact surfaces of the support elements is particularly preferably designed such that at least one support element has a rotatably mounted sleeve with an eccentric bore, a support carrier being arranged in the eccentric bore such that the support carrier has at least one contact surface for contacting the impeller is formed and such that a rotation of the sleeve results in a radial displacement of the at least one contact surface in the radial direction.

The support elements are preferably arranged and designed to cooperate in such a way that they are suitable, in an operating position, to support the radial turbine engine impeller against the gravitational pull.

The method according to the invention for disassembling the arrangement provides that in a first step closable openings in the housing wall of the housing are opened, in a second step support elements are guided through this opening, in a third step the support elements are brought into contact with the radial turbine machine impeller and are stationary are attached in such a way that the radial turbomachine impeller is supported and secured, in particular the weight of the radial turbomachine impeller. In a fourth step, the shaft seal and / or the radial bearing is / are removed.

Assembly is carried out in the reverse order of steps and in reverse of the correspondingly described actions.

Figur 1

eine schematische Darstellung eines Längsschnitts durch eine erfindungsgemäße Anordnung,

Figur 2

eine perspektivische schematische Darstellung einer erfindungsgemäßen Anordnung,

Figur 3

ein mit III in Figur 1 ausgewiesenes Detail,

Figur 4

ein mit IV in Figur 3 ausgewiesenes Detail,

Figur 5

eine schematische Darstellung des erfindungsgemäßen Verfahrens.

The invention is described in more detail below on the basis of a special exemplary embodiment with reference to drawings. Show it:

Figure 1

2 shows a schematic representation of a longitudinal section through an arrangement according to the invention,

Figure 2

2 shows a perspective schematic illustration of an arrangement according to the invention,

Figure 3

one with III in Figure 1 proven detail,

Figure 4

one with IV in Figure 3 proven detail,

Figure 5

a schematic representation of the method according to the invention.

The Figures 1 - 4 each show an embodiment of an arrangement AR according to the invention in different representations, so that identical reference numerals here mean identical components of an identical embodiment. Throughout the document, information such as axial, radial, tangential or circumferential direction on an axis X of a shaft SH, which is identical to the axis of rotation. The arrangement AR according to the invention comprises a radial turbine machine impeller IMP, a housing CAS with an axial and radial flow opening, an inlet flow opening INL and an outlet flow opening EXT, further comprising a shaft SH that extends along the axis X, at least one radial bearing RB (in the Figure 1 two radial bearings RB are shown axially spaced from each other) and at least one shaft seal SHS. The shaft seal SHS seals a process pressure of a process gas PFL possibly existing in the housing CAS in such a way that essentially no process gas PFL can escape from the inside INS of the housing CAS in the region of a through opening TH. This applies all the more if there is a toxic process fluid PFL or other dangerous process fluid PFL inside the housing CAS. The shaft SH is fixed in a bearing block BSP in a radial, axial or spatially unambiguous position by means of the at least one radial bearing RB and here additionally by means of a second radial bearing RB and an axial bearing AB outside the housing CAS. A radial turbo machine impeller IMP is detachably attached to a shaft end SE of the shaft SH. In a manner not shown, a Hirth toothing can preferably be provided with an axial attachment of the radial turbine machine impeller IMP to the shaft end SE. The through opening TH of the housing CAS is provided for a first housing wall CW1 of the housing CAS, in this exemplary embodiment a modular design of the housing CAS with possible disassembly of the first housing wall CW1 is provided. This disassembly option is used to disassemble the radial turbo machine impeller IMP from the CAS housing and, if necessary, to access other compressor components of the AR arrangement, which are located inside the INS of the CAS housing. Basically, a one-piece design of the first housing wall CW1 of the housing CAS with the rest of the housing CAS is also possible. Complete disassembly or removal of the radial turbine machine impeller from the CAS housing is proportionate complex since all of these components must be sealed and centered again when reassembled. In order to avoid such an effort, for example when inspecting the radial bearing RB or the shaft seal SHS, it is provided according to the invention that closable openings OP1, OP2, OP3 are provided in the housing wall CW1, through the support elements SP1, SP2, SP3 into the interior INS of the housing CAS can be inserted so that they protrude through the housing wall CW1 and in this way - quasi from the outside - contact the radial turbine engine impeller IMP at least a part of the weight force, so that the radial turbine engine impeller in the housing CRS in a certain spatial position relative to the housing CAS, in particular radially and axially - can be fixed. The individual support elements SP1, SP2, SP3 are spaced radially and in the circumferential direction CDR, at least the first support element SP1 and the second support element SP2 supporting the radial turbine engine impeller IMP from below against the gravitational acceleration g - that is, intercepting the weight of the radial turbine engine impeller IMP. The upper third support element SP3 has a radial gap GAP to the radial outer edge of the impeller IMP, because this third support element SP3 essentially serves to fix the spatial position against tilting of the impeller IMP.

In the Figure 2 the rear of the housing wall CW1 is visible, support elements SP1 and SP3 or the two closable openings OP1, OP3 being shown in their preferred radial and circumferential positions. The second support element (not shown) or the second closable opening OP2 is arranged correspondingly mirror-symmetrically to an imaginary vertical plane through the axis X in the first housing wall CW1.

The Figures 3 and 4 show in detail the structure of a corresponding support element SP1, SP2, SP3. The support element SP1, SP2, SP3 are to be fastened with fixing elements FXT virtually stationary on the first housing wall CW1 after passing through a corresponding lockable opening OP1, OP2, OP3. The support element SP1 - SP3 essentially consists of an outer sleeve OSV, an inner sleeve ISV and a central bolt CBT. Contact surfaces CSF are provided on the central bolt CBT for contacting and intercepting the radial turbine engine impeller IMP. The inner sleeve ISV has an eccentric bore EXC for receiving the central pin CBT. When the inner sleeve ISV rotates, the central bolt CBT shifts in the radial direction, so that in a certain circumferential position of the inner sleeve ISV the contact surfaces CSF of the support element SP1-SP3 contact corresponding contact surfaces of the radial turbine machine impeller IMP and in this way with a corresponding setting of all the provided support elements SP1-SP3 of an arrangement AR according to the invention, the radial turbine machine impeller IMP is fixedly positioned relative to the housing CAS and in particular the weight of the impeller IMP is absorbed.

In Figure 5 the method according to the invention for disassembly or assembly is illustrated with four successive steps 1, 2, 3, 4. During disassembly, each of the closable openings OP1, OP2, OP3 in the first housing wall CW1 of the housing CRF is opened in the first step 1. In a second step 2, support elements SP1-SP3 are guided through these openings OP1-OP3. In a third step, the support elements SP1 - SP3 are brought into contact with the radial turbine machine impeller and fixed in place. The attachment is carried out in such a way that the radial turbomachine impeller IMP is supported and secured, in particular the weight of the radial turbomachine impeller IMP.

In a fourth step, the shaft seal SHS and / or the radial bearing RB are / are removed.

An assembly according to the invention is carried out in the reverse order of steps and in reverse of the actions described.

The support elements SP1, SP2, SP3 according to the invention receive the concentric bearings of the shaft SH with the impeller IMP, so that assembly and disassembly of the shaft seal SHS and the bearing RB is possible.

Claims (9)

Arrangement (AR), comprehensive - radial turbine engine impeller (IMP), - housing (CAS) with axial and radial flow opening (INL, EXT), - shaft (SH) extending along an axis (X), - at least one radial bearing (RB), - at least one shaft seal (SHS), the radial turbine engine impeller (IMP) being detachably attached to a shaft end (SE) of the shaft (SH), the radial turbine machine impeller (IMP) being located in an interior (INS) of the housing (CAS),
wherein the shaft (SH) extends through a through opening (TH) provided in a first housing wall (CW1) of the housing (CAS), sealed by means of the shaft seal (SHS),
the shaft seal (SHS) being arranged axially between the radial turbomachine impeller (IMP) and the radial bearing (RB) on the shaft (SH),
characterized,
that at least one closable opening (OP1) is provided in the housing wall (CW1),
wherein a support element (SP1) protrudes through the first closable opening (OP1) and contacts the radial turbomachine impeller (IMP) to intercept at least part of the weight. Arrangement according to claim 1,
at least two closable openings (OP1, OP2), the first closable opening (OP1) and a second closable opening (OP2) are provided in the first housing wall (CW1), a second support element (SP2) through the second closable opening (OP2 ) is provided projecting therethrough and the radial turbine engine impeller (IMP) is spaced in a circumferential direction (CDR) from the first support element (SP1) contacted at least a part of the weight force. AR arrangement according to claim 2,
wherein a third closable opening (OP3) is provided in the first housing wall (CW1), the arrangement (AR) being designed for an operational setup in which the first support element (SP1) and the second support element (SP2) the radial turbine engine impeller (IMP) support against the weight from below and the third support element (SP3) the radial turbine engine impeller (IMP) spaced from the other two support elements (SP1, SP2) in the circumferential direction (CDR), secures against tipping over. Arrangement according to at least one of the preceding claims 1-3,
wherein at least one support element (SP1, SP2, SP3) has a radial adjustment option (RAJ) for a contact surface for contacting the radial turbine engine impeller (IMP). Arrangement according to at least one of the preceding claims 1-4,
wherein the support elements (SP1, SP2, SP3) have a radial adjustment option (RAJ) for radially displacing the contact surface for contacting the radial turbine engine impeller (IMP). Arrangement according to at least one of the preceding claims 1-5,
wherein at least one support element (SP1, SP2, SP3) has a rotatably mounted sleeve with an eccentric bore (EXC), a support carrier (SPC) being arranged in the eccentric bore (EXC), such that the support carrier (SPC) with at least a contact area (CSF) to Contacting the radial turbine engine impeller (IMP) and such that twisting the sleeve (SLV) results in a radial displacement of the at least one contact surface (CSF). Arrangement AR according to at least one of the preceding claims 1-6, wherein the support elements (SP1, SP2, SP3) are designed to work together in such a way that they are suitable for supporting the radial turbine engine impeller (IMP) against the gravitational pull (g). Method for dismantling an arrangement according to at least one of claims 1-7,
whereby a step-by-step procedure provides that for the purpose of disassembly
in a first step, closable openings (OP1, OP2, OP3) are opened in the first housing wall (CW1) of the housing (CAS),
in a second step, support elements (SP1, SP2, SP3) are passed through these openings (OP1, OP2, OP3),
in a third step, the support elements (SP1, SP2, SP3) are brought into contact with the radial turbine machine impeller (IMP) and fixed in place in such a way that the radial turbine machine impeller (IMP) is supported and secured, in particular the weight of the radial turbine machine impeller (IMP) is
in a fourth step the shaft seal (SHS) and / or the radial bearing (RB) is / are dismantled. Method for assembling an arrangement according to at least one of claims 1-7,
wherein for the purpose of assembly steps 1-4 according to claim 8, are carried out in the reverse order and with reversal of the actions.

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