EP3617519A1 - Rotor de compresseur radial, compresseur radial, compresseur à engrenage - Google Patents

Rotor de compresseur radial, compresseur radial, compresseur à engrenage Download PDF

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Publication number
EP3617519A1
EP3617519A1 EP18190976.3A EP18190976A EP3617519A1 EP 3617519 A1 EP3617519 A1 EP 3617519A1 EP 18190976 A EP18190976 A EP 18190976A EP 3617519 A1 EP3617519 A1 EP 3617519A1
Authority
EP
European Patent Office
Prior art keywords
shaft
impeller
radial compressor
radial
imp1
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.)
Withdrawn
Application number
EP18190976.3A
Other languages
German (de)
English (en)
Inventor
Rosario Montante
Attilla Yildiz
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
Priority to EP18190976.3A priority Critical patent/EP3617519A1/fr
Priority to PCT/EP2019/068569 priority patent/WO2020043379A1/fr
Publication of EP3617519A1 publication Critical patent/EP3617519A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F04D25/163—Combinations of two or more pumps ; Producing two or more separate gas flows driven by a common gearing arrangement
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • 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
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • 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
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/51—Inlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power

Definitions

  • the invention relates to a radial compressor with a radial compressor rotor defined at the outset.
  • the invention relates to a gear compressor with such a radial compressor rotor.
  • Radial compressors of this type are preferably used, in particular in the version as geared compressors, each with corresponding radial compressor rotors for compressing air.
  • Large compression capacities are required in particular for systems for separating air into the individual components.
  • main air compressor main air compressor
  • BAC booster air compressor
  • Conventional MAC are usually designed as at least three-stage gear compressors. Arrangements with a gear compressor or gear compressor are already from the DE102010020145-A1 . DE102009015862-A1 . DE102014225136-A1 . DE102015200439-A1 . DE102015203287-A1 known.
  • Compression systems of this type are correspondingly expensive because, as a rule, a gear and at least two compressor shafts are required, on the shaft ends of which the corresponding compressors can be attached.
  • the high installation effort, the maintenance costs and the amount of the investment are simply undesirable from an economic point of view.
  • the object of the invention is to alleviate these disadvantages.
  • the invention proposes a radial compressor rotor.
  • the invention also relates to a radial compressor or a gear compressor, each of which makes use of the radial compressor rotor according to the invention.
  • a relatively high energy density can be achieved per stage, including that stage which has a connecting shaft according to the invention with the drive in the area of the axial suction - attached by means of an adapter flange to the first impeller or to the shaft.
  • a pressure ratio ratio between inlet pressure and outlet pressure from the compressor
  • the process fluid at an outlet pressure of for example to compress 1 bar up to 6 bar.
  • the connecting shaft can preferably be a coupling flange or a coupling in order to enable the detachable connection of other rotor components, which are in particular attributable to the drive.
  • the proposed design according to the invention enables not only a high energy density per impeller or per compression stage, but also a drive of the compressor rotor without an intermediate gear.
  • the drive can be a gas turbine, a steam turbine or an electric motor, which transmits the respective speed inherent in the drive unit without conversion to the radial compressor rotor according to the invention.
  • the arrangement according to the invention of the drive on the side of the axial suction of an impeller of the axially suction and radially extending impeller has the particular advantage that a so-called back-to-back arrangement is made possible without providing a gear for driving the radial compressor rotor.
  • the back-to-back arrangement enables the axial suction, which is particularly favorable in terms of flow, without prior sharp deflection, as is provided in a single-shaft construction with corresponding impellers by means of the so-called feedback stages. Instead, the impellers suck in axially from opposite directions - arranged at the shaft ends - and the radial compressor rotor has radial bearing points between the two impellers in the back-to-back arrangement.
  • the two impellers have a so-called flying arrangement on the shaft in terms of rotor dynamics with respect to the bearing.
  • flying arrangement on the shaft in terms of rotor dynamics with respect to the bearing.
  • the adapter flange is particularly advantageously fastened to the first impeller, the first impeller being attached axially to the shaft and being arranged axially between the shaft and the connecting shaft. It is basically possible to provide a connection by means of a Hirth toothing between the adapter flange and the first impeller and between the first impeller and the shaft.
  • connection and centering between the adapter flange and the impeller by means of pins, in particular by means of tapered pins and by means of a plurality of axially extending screws arranged over the circumference in a certain diameter.
  • pins in particular by means of tapered pins and by means of a plurality of axially extending screws arranged over the circumference in a certain diameter.
  • This can take turns Pins or taper pins and screws can be arranged over the circumference on the same diameter.
  • cylindrical pins and centering can also be provided by means of an at least partially tapered contact surface between the adapter flange and the impeller.
  • connection of the shaft to the first impeller by means of a tie rod extending axially through the first impeller is particularly useful, so that the first impeller is attached to a first axial end of the shaft.
  • this tie rod can also be used to axially attach the adapter flange to the connecting shaft on the first impeller.
  • the shaft has at least one radial bearing point.
  • the shaft has at least one axial bearing point.
  • the invention can be developed particularly expediently in that the shaft has at least one radial bearing point a groove extending in the circumferential direction and axially, which essentially encompasses the area of the radial bearing in the axial and circumferential direction, and the shaft has a cover sleeve radially outside the groove, which Covering the groove radially outwards. In this way, the so-called Morton effect can be prevented, so that the radial compressor rotor runs more smoothly.
  • any thermal influences from a so-called hot spot which can occur locally at a circumferential position of the radial bearing point, are not transmitted to the core area of the shaft, so that the straightness of the shaft from such a local thermal influence is not worsened.
  • a radial compressor with a radial compressor rotor according to the invention and a housing with an inflow, which is at least axially configured as an annular channel has an adjustable inlet guide in the axial region of the ring channel, the inlet guide being by means of Rotation around a respective one Has vane longitudinally adjustable guide vanes and wherein the vane longitudinal axes run obliquely to the axis of the shaft, a movement gap is provided between the ends of the vane longitudinal axis of the guide vanes and the boundary contours, the guide vane ends being designed such that the height of the movement gap increases with increasing distance from the longitudinal axis of the vane .
  • the guide vanes of the inlet guide apparatus can be adjusted in the circumferential direction in spite of the natural curvature of the ring channel and despite the guide vanes arranged obliquely to the axis of the radial compressor rotor, so that the desired flow technology of the respectively illuminated operating point can be set.
  • the height of the movement gap increases with increasing distance from the longitudinal axis of the blade such that the guide blade ends have a rounded or round shape, preferably the blade ends are rounded in a spherical shape. In this way, a particularly wide angular adjustment range of the respective guide vanes of the inlet guide apparatus is ensured without the risk of jamming.
  • the invention or the radial compressor rotor according to the invention can be used particularly expediently for a transmission compressor.
  • a gear compressor comprises a gear box on which compressors are arranged, a large wheel arranged in the gear box, a plurality of pinion shafts with pinions which are arranged distributed around the large wheel, the pinions being in engagement with the large wheel, at least some of which Pinion shafts are attached to the shaft ends of the compressor impellers, with at least one pinion shaft, preferably exactly one pinion shaft, as a radial compressor rotor with the inventive one Arrangement of an adapter flange and a connecting shaft for a drive is provided.
  • Figure 1 shows a schematically illustrated longitudinal section along an axis X of a radial compressor rotor RCR.
  • the radial compressor rotor RCR is particularly well suited for use in a radial compressor RCP, as is shown in a schematic partial longitudinal section with an inlet guide device IGV in Figure 3 is shown or for a gear compressor GTC, as in Figure 4 is shown schematically with a radial compressor rotor RCR.
  • FIG. 2 shows a detail of a shaft SH of the radial compressor rotor RCR, as in Figure 1 is shown, the detail in Figure 1 is marked with II.
  • the in Figure 1 The radial compressor rotor RCR shown comprises a shaft SH which extends along the axis X, at least one impeller IMP1, IMP2, here a first impeller IMP1 and a second impeller IMP2 being axially attached to the shaft SH.
  • the impellers IMP1, IMP2 suck in axially and discharge a process fluid PFL radially.
  • the RCR radial compressor rotor also includes an adapter flange CPL, a connecting shaft CSH and a drive DRV.
  • the first impeller IMP1 is attached using a tie rod TBL.
  • the tie rod TBL is screwed axially into the SH shaft and clamps the impeller IMP1, IMP2 using a nut NUT.
  • This method of fastening by means of the central tie rod TBL is the same on both axial sides of the shaft SH, the impeller IMP being fastened to the shaft SH by means of a separate nut NUT by means of the tie rod TBL.
  • the first impeller is also axially connected to an adapter flange CPL, the adapter flange CPL surrounding the nut NUT for connecting the shaft SH to the first impeller IMP1 at the contact surface in the circumferential direction or having a central recess for the nut NUT.
  • the nut NUT is preferably a separate component separate from the adapter flange CPL. It is also conceivable that the nut NUT axially braces both the first impeller IMP1 and the adapter flange CPL.
  • Present in Figure 1 is not a one-piece design of the nut NUT and the adapter flange CPL on the part of the first impeller IMP1, but the nut NUT and the adapter flange CPL are separate components.
  • the adapter flange CPL is secured against twisting and loosening by means of screws TSC and pins TPN.
  • the pins TPN can be conical for the purpose of centering.
  • a contact surface CFS between the adapter flange CPL and the first impeller IMP1 can be at least partially conical.
  • a connecting shaft CSH is attached to the adapter flange CPL in the axial direction, a contact surface between the connecting shaft CSH and the adapter flange CPL being conically centered. Without this centering function, this contact surface CSF can have a flat design on the face.
  • the adapter flange CPL has an internal thread ITH for attaching the connecting shaft CSH and the connecting shaft CSH has an external thread OTH.
  • the direction of rotation of the internal thread ITH or external thread OTH, which interlock and fasten the connecting shaft CSH to the adapter flange CPL, is matched to the direction of rotation of the drive DRV, which is drivingly connected to the connecting shaft CSH, in such a way that a drive torque from the drive DRV transferred to the radial compressor rotor RCR does not lead to a loosening of this connection.
  • the Figure 1 shows the preferred embodiment, wherein the adapter flange CPL is provided on the first impeller IMP1, the first impeller IMP1 being axially attached to the shaft SH and axially between the shaft SH and the connecting shaft CSH.
  • Axial between the two impellers IMP1, IMP2 is the shaft SH, which extends in the axial direction and which has two radial bearing points RBE and one axial bearing point ABE.
  • the axial side to which the first impeller IMP1 is attached is referred to as the axial end AX1 and the axial side of the shaft SH, which supports the second impeller IMP2, is referred to as the second axial end AX2.
  • the Figure 1 shows an arrangement of the two impellers IMP1, IMP2 at the two axial ends AX1, AX2 in a so-called flying bearing, in which a radial bearing point RBE is provided only on one side of the two impellers IMP1, IMP2.
  • the two impellers IMP1, IMP2 draw in a process fluid PFL from different axial directions and emit it radially, which is in the configuration of the Figure 1 is referred to as a so-called back-to-back arrangement of the two impellers IMP1, IMP2 on the shaft SH to one another.
  • a Hirth toothing HRT is provided on the end of the shaft SH and on the end of the second impeller IMP2, which centers the components radially to one another and ensures reliable transmission of the torques.
  • Such a connection is in principle also possible on the part of the first impeller IMP1.
  • the in the embodiment of the Figure 1 The variant shown for connecting the first impeller IMP1 to the shaft instead provides radial centering by means of a recess RZS in the impeller, into which the shaft is fitted on the face side - here shrunk (radial shrink fit RSC).
  • the axial or end face contact surface FFS between the first impeller IMP1 or the end face FFS in the recess RZS and the end face of the first shaft end AX1 essentially serves to transmit the torque under the axial prestress by means of the tie rod TBL.
  • a friction-increasing means is advantageously provided axially between the end face of the first shaft end AX1 and the end face FFS in the recess RZS - here a disc DMT with axially protruding diamond tips.
  • the Figure 2 shows the detail of the radial bearing point RBE from the Figure 1 of the RCR radial compressor rotor.
  • the shaft is provided at the radial bearing point RBE with an axially and circumferentially extending groove GRV, which essentially covers or covers or covers the area of the radial bearing essentially axially and in the circumferential direction.
  • the shaft SH also includes a cover sleeve SLV, which is arranged radially outside the groove GRV, so that the groove GRV is covered radially outwards.
  • An arrangement “radially outside the groove GRV” is understood by the invention to mean that the sleeve SRV is at least partially arranged radially outside the groove.
  • Embodiments in which the sleeve SLV at least partially also has elements within the groove GRV are not preferred by the invention, but are also not necessarily excluded from this. Accordingly, the sleeve SLV on the shaft SH non-positively, for. B. by means of a shrink connection or be non-positive and positive (also for example by means of a shrink connection). Because the groove GRV is located on the shaft SH, the mechanical requirements on the sleeve SLV are reduced compared to an embodiment in which a corresponding recess is provided in the sleeve SLV. Therefore, the entire arrangement is thinner with otherwise essentially the same mechanical properties.
  • the Figure 3 shows in a fragmentary schematic longitudinal section a radial compressor RCP with a radial compressor rotor RCR according to the invention.
  • the longitudinal section shows the detail of an adjustable inlet guide device IGV in an inflow INL of a housing CAS of the radial compressor RCP.
  • the inflow is formed at least axially in sections as a ring channel ANC and the inlet guide device IGV is located in the axial region of the ring channel ANC.
  • the inlet guide device IGV has adjustable guide vanes VNS, which change the fluidic properties of the compressor stage by rotating about a respective longitudinal blade axis VX.
  • the blade longitudinal axis VX runs obliquely to the axis X of the shaft SH.
  • Limiting contours LCI, LCO which delimit the ring channel ANC radially inward (LCI) and radially outward (LCO), are formed parallel to one another at least in the area of the inlet guide apparatus IGV or in the area of the guide vanes VNS.
  • the ends of the guide blades VNS are provided with a rounded or round shape in the direction of the blade longitudinal axis VX, at least in such a way that the height HGT of a movement gap CLG between the boundary contours LCI, LCO and the guide vane ends with increasing distance from the blade longitudinal axis VX is increasingly formed.
  • the height HGT of the movement gap CLG is particularly preferably designed with increasing distance from the blade longitudinal axis VX such that the guide blade ends have a rounded or round shape, preferably are rounded off in a spherical shape.
  • FIG 4 shows the schematic representation of a gear compressor GTC in an axially sectioned plan view of the gear compressor GTC.
  • the gear compressor GTC comprises a radial compressor rotor RCR or a radial compressor RCP in the design according to the invention.
  • a pinion PNN is provided on the shaft SH of the radial compressor rotor RCR, which drives a large wheel BLG.
  • At least one further pinion shaft PSH is driven by the large wheel BLG, as in the Figure 4 schematically indicated, further compressors CPM are arranged at the shaft ends.
  • the casings CAS of the compressors CPM are attached to a gearbox GBX in which the large wheel BLG, the pinion PNN and the shafts SH are essentially arranged and stored.
  • the drive DRV can be implemented without a corresponding transmission gear between the gear compressor GTC and the drive DRV, the drive DRV having the speed with the radial compressor rotor RCR in the nominal speed operation.
  • the gear ratios and sizes of the large wheel BLG and the individual pinion PNN are designed as required. Due to the elimination of the need to drive the BLG large wheel, the space available for attaching the individual compressors CPM to the GBX gearbox has been improved.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP18190976.3A 2018-08-27 2018-08-27 Rotor de compresseur radial, compresseur radial, compresseur à engrenage Withdrawn EP3617519A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP18190976.3A EP3617519A1 (fr) 2018-08-27 2018-08-27 Rotor de compresseur radial, compresseur radial, compresseur à engrenage
PCT/EP2019/068569 WO2020043379A1 (fr) 2018-08-27 2019-07-10 Rotor de compresseur radial, compresseur radial, compresseur à engrenages

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18190976.3A EP3617519A1 (fr) 2018-08-27 2018-08-27 Rotor de compresseur radial, compresseur radial, compresseur à engrenage

Publications (1)

Publication Number Publication Date
EP3617519A1 true EP3617519A1 (fr) 2020-03-04

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EP18190976.3A Withdrawn EP3617519A1 (fr) 2018-08-27 2018-08-27 Rotor de compresseur radial, compresseur radial, compresseur à engrenage

Country Status (2)

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EP (1) EP3617519A1 (fr)
WO (1) WO2020043379A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022101277A1 (fr) * 2020-11-16 2022-05-19 Atlas Copco Airpower, N.V. Turbomachine ayant un arbre couplé à une roue à aubes avec un anneau de friction interposé axialement
US11401942B2 (en) * 2020-05-15 2022-08-02 Garrett Transportation I Inc Fastener arrangement for rotating group of turbomachine

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB967091A (en) * 1961-04-14 1964-08-19 Borsig Ag Improvements in or relating to three-stage radial-flow compressors
US6294842B1 (en) * 1997-12-19 2001-09-25 Alliedsignal Inc. Fog cycle for microturbine power generating system
EP1144826A1 (fr) * 1998-12-24 2001-10-17 AlliedSignal Inc. Appareil et procede permettant d'augmenter la puissance d'une turbine
US6634853B1 (en) * 2002-07-24 2003-10-21 Sea Solar Power, Inc. Compact centrifugal compressor
DE102009015862A1 (de) 2009-04-01 2010-10-07 Siemens Aktiengesellschaft Getriebeverdichterrotor für Kaltgasanwendungen
DE102010020145A1 (de) 2010-05-11 2011-11-17 Siemens Aktiengesellschaft Mehrstufiger Getriebeverdichter
US20160084301A1 (en) * 2013-04-24 2016-03-24 Nuovo Pignone Srl Rotating machinery with adaptive bearing journals and methods of operating
DE102014225136A1 (de) 2014-12-08 2016-06-09 Siemens Aktiengesellschaft Getriebeverdichter, Anordnung mit einem Antrieb und einem Getriebeverdichter
DE102015200439A1 (de) 2015-01-14 2016-07-14 Siemens Aktiengesellschaft Anordnung, Getriebeverdichter
DE102015203287A1 (de) 2015-02-24 2016-08-25 Siemens Aktiengesellschaft Getriebeverdichtergehäuse, Getriebeverdichter
EP3121449A1 (fr) * 2015-07-22 2017-01-25 Thermodyn Compresseur centrifuge sous-marin avec arbre horizontal et avec un seul palier de poussée axiale
US20170356451A1 (en) * 2014-12-16 2017-12-14 Nuovo Pignone Srl Copmpression unit for high and low pressure services

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB967091A (en) * 1961-04-14 1964-08-19 Borsig Ag Improvements in or relating to three-stage radial-flow compressors
US6294842B1 (en) * 1997-12-19 2001-09-25 Alliedsignal Inc. Fog cycle for microturbine power generating system
EP1144826A1 (fr) * 1998-12-24 2001-10-17 AlliedSignal Inc. Appareil et procede permettant d'augmenter la puissance d'une turbine
US6634853B1 (en) * 2002-07-24 2003-10-21 Sea Solar Power, Inc. Compact centrifugal compressor
DE102009015862A1 (de) 2009-04-01 2010-10-07 Siemens Aktiengesellschaft Getriebeverdichterrotor für Kaltgasanwendungen
DE102010020145A1 (de) 2010-05-11 2011-11-17 Siemens Aktiengesellschaft Mehrstufiger Getriebeverdichter
US20160084301A1 (en) * 2013-04-24 2016-03-24 Nuovo Pignone Srl Rotating machinery with adaptive bearing journals and methods of operating
DE102014225136A1 (de) 2014-12-08 2016-06-09 Siemens Aktiengesellschaft Getriebeverdichter, Anordnung mit einem Antrieb und einem Getriebeverdichter
US20170356451A1 (en) * 2014-12-16 2017-12-14 Nuovo Pignone Srl Copmpression unit for high and low pressure services
DE102015200439A1 (de) 2015-01-14 2016-07-14 Siemens Aktiengesellschaft Anordnung, Getriebeverdichter
DE102015203287A1 (de) 2015-02-24 2016-08-25 Siemens Aktiengesellschaft Getriebeverdichtergehäuse, Getriebeverdichter
EP3121449A1 (fr) * 2015-07-22 2017-01-25 Thermodyn Compresseur centrifuge sous-marin avec arbre horizontal et avec un seul palier de poussée axiale

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11401942B2 (en) * 2020-05-15 2022-08-02 Garrett Transportation I Inc Fastener arrangement for rotating group of turbomachine
WO2022101277A1 (fr) * 2020-11-16 2022-05-19 Atlas Copco Airpower, N.V. Turbomachine ayant un arbre couplé à une roue à aubes avec un anneau de friction interposé axialement
BE1028803B1 (nl) * 2020-11-16 2022-06-14 Atlas Copco Airpower Nv Turbomachine

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