WO2012119914A1 - Boîtier de collecte de sortie pour compresseur radial - Google Patents

Boîtier de collecte de sortie pour compresseur radial Download PDF

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Publication number
WO2012119914A1
WO2012119914A1 PCT/EP2012/053496 EP2012053496W WO2012119914A1 WO 2012119914 A1 WO2012119914 A1 WO 2012119914A1 EP 2012053496 W EP2012053496 W EP 2012053496W WO 2012119914 A1 WO2012119914 A1 WO 2012119914A1
Authority
WO
WIPO (PCT)
Prior art keywords
flow
annular cavity
radial
housing arrangement
compressor
Prior art date
Application number
PCT/EP2012/053496
Other languages
German (de)
English (en)
Inventor
Werner Jonen
Christian Woiczinski
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2012119914A1 publication Critical patent/WO2012119914A1/fr

Links

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
    • F04D29/40—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/045—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector 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
    • 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
    • F04D29/40—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
    • F04D29/444—Bladed diffusers
    • 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
    • F05D2250/52—Outlet

Definitions

  • the invention relates to a housing arrangement for a
  • Radial compressor and a method for flow guidance of a flow medium in a centrifugal compressor are provided.
  • Radial compressors are known, for example from EP 1 356 168 Bl.
  • Such centrifugal compressors consist of a one
  • Compressor stage forming, rotating about a rotation axis impeller with a - with respect to the axis of rotation of the impeller - axial inlet and a radial outlet.
  • To be compressed gas flows axially into the impeller of
  • Compressor stage and is then deflected to the outside (radially or in the radial direction), wherein it emerges from the impeller at high speed and twisted.
  • Such a diffuser is usually formed by two non-rotating, an annular cavity or an annular space forming rings, which annular space radially adjoins the impeller outlet or which rings or annular
  • Walls / side surface radially adjoin the impeller outlet and are usually perpendicular to the axis of rotation of the impeller or to this at a very obtuse angle.
  • the gas exiting the impeller is guided radially outward in this annular space between these two annular walls and reaches a collector and / or a spiral. about which the compressed gas is collected and released from the
  • Such a spiral also called volute casing, receives continuously by a growing over a circumference of the spiral cross section, the gas to be discharged and leads it into an outlet nozzle, which is usually a piping system for further or discharge of the
  • the exit diffuser further retards the flow and thus part of its kinetic energy into potential energy, i. in pressure, converted (pressure gain or
  • Compressor stages are connected in series, wherein for collecting and discharging the compressed gas from the last compressor stage or from one compressor stage to the next compressor stage also such a spiral is used as described.
  • Pinion shafts arranged turbochargers wear, of a large, mounted in the housing drive gear, a
  • spirals or spiral housing have the disadvantage that they are technically complicated to manufacture.
  • Radial compressor allows the highest possible pressure recovery. Also, the invention should be simple and inexpensive to implement, make optimal use of the available space and flexible adaptable to different flows in centrifugal compressors or at different currents in
  • the task is accomplished by a housing arrangement for a
  • the housing assembly for the centrifugal compressor has a first, substantially radially oriented, annular Cavity as well as a second, substantially axial
  • a guide grid is arranged in the second, substantially axially aligned, annular cavity.
  • the flow medium is in
  • the flow medium is deflected substantially in an axial direction and in the substantially
  • This kinetic energy withdrawn from the flow medium is converted into potential energy in the form of pressure, i. a (desired) pressure increase of the flow medium,
  • the flow medium for example a process gas, should be spin-free.
  • aligned used for example for the radially oriented, annular cavity or the axially aligned
  • annular cavity - in the sense of a flow direction, for example, defined by the cavity or realized flow direction of the flow medium, to understand.
  • the flow medium usually a process gas
  • the first substantially radially oriented
  • annular cavity radially outward is characterized by the
  • the invention thus uses a (downstream) guide grille known, for example, from a recirculation stage in a multi-stage turbomachine, such as a multistage radial compressor.
  • a multi-stage turbomachine such as a multistage radial compressor.
  • the Nachleitgitter or its profiling (blading) in this case causes the flow of the depressed by the impeller of the centrifugal compressor twisted and converted into pressure (conversion of kinetic energy into potential).
  • the Nachleitgitter not - as in the known feedback stage - centripetally flows through, but according to the invention in the axial direction.
  • Pressure recovery is a solution that uses this efficiently in a restricted space.
  • the invention allows by their, compared to a spiral flow guide, simpler
  • the guide grid according to the invention of the swirling flow flow to remove the swirl and implement this in a pressure increase (pressure recovery), which is a
  • this can be adapted to the flow or the flow over a channel height or over a height of the second cavity to the leading edge angle.
  • the invention in particular in combination with a collecting housing, a structurally advantageous and simpler as well as more economical solution for collecting and discharging a flow medium from a
  • Compressor stage of the centrifugal compressor connected to a radial inlet of the first, substantially radially oriented, annular cavity.
  • this annulus has an optionally adjustable blading through which the pressure recovery can be increased.
  • annular collecting space, in particular with a over a circumference of the annular collecting space constant cross-section, is arranged (concentric arrangement). Also a collection room with changing over the scope
  • the outlet diffuser is conical.
  • a separation rib may be arranged in the collecting space, which divides a flow entering into the collecting space into two approximately equal flows.
  • Outlet flange connected to a piping system, whereby the compressed flow medium from the
  • the flow medium usually has a predetermined or
  • Radial compressor off or in the piping system entry This specification of a flow velocity can be based on structural boundary conditions, such as load limits in the pipeline system.
  • Flow medium in the second, substantially axially aligned, annular cavity is adapted and / or that the flow over a cross section or a (channel) height of the second, substantially axially aligned, annular cavity is adapted to the leading edge angle of the profile of the guide grid ,
  • the housing assembly can be used in a single or multi-stage radial compressor.
  • a multi-stage centrifugal compressor can also as
  • Turbomachines are used, where a flow medium is radially out or to lead into a turbomachine.
  • a flow medium is radially out or to lead into a turbomachine.
  • Flow direction of the flow medium is then adjusted accordingly.
  • the flow medium first flows through the second cavity, is then deflected in the radial direction and flows through the first cavity radially inwards.
  • FIG 3 sketch in section through the
  • FIG. 2
  • FIG 4 sketch in section through a
  • FIG. 1 shows a radial compressor 100, whose
  • Outlet collecting housing 1 according to an imple mentation form in the figures 2 and 3 is shown in more detail.
  • This radial compressor 100 has an impeller 10 which rotates about an axis 11 at high speed.
  • the impeller 10 has a hub 12 and radially projecting blades 13th
  • the - with flow direction 101 - axially flowing gas is rotated by the impeller 10 in rotation and leaves the Impeller 10 in the radial flow direction 101 to the axis 11 and at an obtuse angle to the axis 11 with high
  • the blades 13 are attached to a common back plate 14 of the hub 12.
  • the impeller 10 is located in a housing 15, the wall 16 of the outer contour of the impeller 10 is adjusted.
  • the fan formed by the impeller 10 has an axial inlet 17 and a radial outlet 18 extending around the circumference of the impeller 10.
  • Impeller 10 may also be provided with a final cover plate (not shown) on the outer contour.
  • FIGS. 2 and 3 show an annular space 2 or diffuser 2, which is firmly connected to the housing 15 and does not rotate.
  • the annulus or diffuser 2 has a substantially radial support wall 21, to the wings 22nd
  • Blade 22 occupied, radially aligned cavity or channel forms.
  • the wings 22 extend substantially radially to the axis 11th
  • the task of the diffuser 2 is that of the
  • Impeller 10 accelerated gas, which has a high kinetic
  • the adaptation takes place via a front edge angle 27 of a radially inner wall 28 of the
  • the axial annular channel 3 has an (annular)
  • Outlet opening 25 through which the compressed and now twist-free gas in an annular cross-section 6, a collecting space 6, occurs.
  • the gas is further via an outlet flange 8 (not shown) in a
  • Pipe system 9 (not shown) with the desired pressure of for example 6 to 8 bar at desired
  • FIGS. 4 to 6 show further embodiments of the invention
  • Exit manifold housing 1 of the radial compressor 100 The same components are denoted by the same and, if not described in detail, designed according to the above.
  • the collecting space 6 is in such a manner with the axial annular channel 3
  • FIG 4 An embodiment according to FIG 4 is implemented, if presumably still a residual twist after the guide grid 5 is present. It is ensured that the swirl through the guide grille. 5
  • FIG 2 a more compact design can be selected according to FIG 2, in which the collecting space 6 is further offset to the axis 11.
  • FIG. 5 shows a discharge collecting housing 1, in which the
  • the annular channel formed in the collecting chamber 6 has constant cross-sections around the circumference.
  • the collecting chamber 6 is arranged concentrically with the axial annular channel 3 (concentric Arrangement).
  • a radial separating rib 24 is provided in the collecting space 6, which, as FIG. 5 shows, in the collecting space 6
  • twist-free flow is provided in a right or left flowing or guided gas flow.
  • the discharge nozzle or the conical outlet diffuser 7 both streams are discharged radially outward.
  • the collecting chamber 6 is eccentric to the axial annular channel. 3
  • Collecting space 6 is arranged offset.
  • FIG 6 shows, the collecting space 6, the barrier rib 24 to
  • a special feature of this radial compressor 100 or its housing 1 according to FIGS. 1 to 6 lies in the use of a secondary lattice known from a return stage, in this case lattice grids 5, together with the collecting housing 6.
  • the Nachleitgitter 5 in this case causes the flow of the impressed by the impeller 10 and after flowing through the
  • bladed diffuser is still deprived of existing twist (conversion of kinetic into potential energy).
  • the Nachleitgitter 5 is not - as in the known feedback stage - centripetally flows through, but in the axial direction 101 in the axial annular channel. 3
  • the used Profi 1 26 of the Nachleitgitters 5 can be adjusted via the leading edge angle 27 to the flow or the flow over the height of the axial annular channel 3 at the leading edge angle 27.
  • Housing 1 represents an advantageous alternative to the use of a spiral, if this is due to
  • Radial compressors are used. There it can - as described above - for flow guidance behind the last stage of such a multi-stage centrifugal compressor as well as each between two stages of such a multi-stage
  • Radial compressor can be used.
  • such a multi-stage centrifugal compressor can also be a transmission compressor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un boîtier pour un compresseur radial et un procédé de guidage d'écoulement d'un milieu d'écoulement dans un compresseur radial. Ce boîtier pour le compresseur radial comporte une première cavité annulaire orientée sensiblement radialement et une deuxième cavité annulaire orientée sensiblement axialement, lesquelles sont reliées ensemble par l'intermédiaire d'un ensemble de déviation. Dans la deuxième cavité annulaire orientée sensiblement axialement est disposée une grille de guidage. Selon le procédé destiné à guider l'écoulement d'un milieu d'écoulement dans un compresseur radial, le milieu d'écoulement est guidé vers l'extérieur sensiblement dans une direction radiale. Ensuite, le milieu d'écoulement est dévié sensiblement dans une direction axiale et sensiblement réacheminé dans la direction axiale. Lorsque le milieu d'écoulement continue de s'écouler sensiblement dans la direction axiale, un moment cinétique est éliminé au moins en partie de l'écoulement.
PCT/EP2012/053496 2011-03-04 2012-03-01 Boîtier de collecte de sortie pour compresseur radial WO2012119914A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102011005105.8A DE102011005105B4 (de) 2011-03-04 2011-03-04 Austrittssammelgehäuse für einen Radialverdichter
DE102011005105.8 2011-03-04

Publications (1)

Publication Number Publication Date
WO2012119914A1 true WO2012119914A1 (fr) 2012-09-13

Family

ID=45808854

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2012/053496 WO2012119914A1 (fr) 2011-03-04 2012-03-01 Boîtier de collecte de sortie pour compresseur radial

Country Status (2)

Country Link
DE (1) DE102011005105B4 (fr)
WO (1) WO2012119914A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102022120820A1 (de) 2022-08-17 2024-02-22 Rolls-Royce Solutions GmbH Verdichtergehäuse, Radialverdichter mit einem solchen Verdichtergehäuse, Radialverdichteranordnung, Abgasturbolader und Brennkraftmaschine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3832089A (en) * 1972-08-28 1974-08-27 Avco Corp Turbomachinery and method of manufacturing diffusers therefor
US5722813A (en) * 1996-10-28 1998-03-03 Alliedsignal Inc. Segmented composite compressor deswirl
US20050005606A1 (en) * 2003-07-11 2005-01-13 Gary Vrbas Turbocharger compressor with non-axisymmetric deswirl vanes
WO2005042946A1 (fr) * 2003-11-04 2005-05-12 Pratt & Whitney Canada Corp. Diffuseur a vanne hybride
EP1356168B1 (fr) 2000-12-21 2006-08-30 Dresser-Rand Company Dispositif de pressurisation d'un fluide
DE102008025249A1 (de) * 2008-05-27 2009-12-03 Siemens Aktiengesellschaft Sammelraum und Verfahren zur Fertigung

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE8601577L (sv) * 1985-04-29 1986-10-30 Teledyne Ind Diffusorsystem foe en centrifugalkompressor och forfarande for tillverkning av densamma
US5076758A (en) * 1990-07-18 1991-12-31 Ingersoll-Rand Company Centrifugal pumps
DE4219249C2 (de) * 1992-06-12 1994-03-31 Kuehnle Kopp Kausch Ag Radialverdichter, insbesondere eines Turboladers
FR2904033B1 (fr) * 2006-07-19 2011-01-21 Snecma Ensemble diffuseur-redresseur pour une turbomachine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3832089A (en) * 1972-08-28 1974-08-27 Avco Corp Turbomachinery and method of manufacturing diffusers therefor
US5722813A (en) * 1996-10-28 1998-03-03 Alliedsignal Inc. Segmented composite compressor deswirl
EP1356168B1 (fr) 2000-12-21 2006-08-30 Dresser-Rand Company Dispositif de pressurisation d'un fluide
US20050005606A1 (en) * 2003-07-11 2005-01-13 Gary Vrbas Turbocharger compressor with non-axisymmetric deswirl vanes
WO2005042946A1 (fr) * 2003-11-04 2005-05-12 Pratt & Whitney Canada Corp. Diffuseur a vanne hybride
DE102008025249A1 (de) * 2008-05-27 2009-12-03 Siemens Aktiengesellschaft Sammelraum und Verfahren zur Fertigung

Also Published As

Publication number Publication date
DE102011005105A1 (de) 2012-09-06
DE102011005105B4 (de) 2016-05-12

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