US3303989A - Axial-and radial-flow, multistage centrifugal compressor - Google Patents

Axial-and radial-flow, multistage centrifugal compressor Download PDF

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Publication number
US3303989A
US3303989A US348729A US34872964A US3303989A US 3303989 A US3303989 A US 3303989A US 348729 A US348729 A US 348729A US 34872964 A US34872964 A US 34872964A US 3303989 A US3303989 A US 3303989A
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Prior art keywords
flow
stage
axial
radial
stages
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Expired - Lifetime
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US348729A
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English (en)
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Rurik Josef
Weinrich Hellmut
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Gutehoffnungshutte Sterkrade AG
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Gutehoffnungshutte Sterkrade AG
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F04D17/02—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal
    • F04D17/025—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal comprising axial flow and radial flow stages

Definitions

  • the invention utilizes adjustable stationary blades, such as are known per se in axial-flow stages.
  • adjustable stationary blades In known combined axialand radial-flow compressors, such adjustable stationary blades have been used in all axialfiow stages, and the resulting greater length of the compressor has partly been compensated by the use of at least one radial-flow impeller as the last stage.
  • the invention is based on a recognition which is of special significance for relatively high compression ratios, i.e., for compressors having a large number of stages. This recognition resides in that the desired object can be quite adequately accomplished even when adjustable stationary blades are provided only to a limited extent.
  • the invention resides in that only a part of the axial-flow stages is provided with adjustable stationary blades and at least one axial-flow stage having non-adjustable stationary blades is disposed between these adjustable axialfiow stages and the succeeding radial-flow stage or stages.
  • a plurality of successive axial-flow stages .are to be provided with adjustable stationary blades it is advantageous to use for this purpose a common adjusting linkage.
  • Intermediate levers of different length may be provided "ice in known manner for an adjustment through different angles.
  • a further feature of the invention resides in that the length of the intermediate levers is such that the largest angle of adjustment is obtained in the first stage and the angle of adjustment obtained in each succeeding adjustable stage is somewhat smaller than in the preceding stage in such a manner that a zero pressure rise is obtained in each of these stages when they are all completely shut off.
  • a plurality of axial-flow stages serving as a low-pressure section and a plurality of radial-flow stages serving as a succeeding high-pressure section may be arranged on a common shaft, and a cooler may be interposed in known manner between any two adjacent radial-flow stages.
  • two stage groups each of which comprises preferably a plurality of axial-flow stages and a succeeding radial-flow stage, may be arranged for mutually opposed directions of axial flow in such a manner that the inlet axial-flow stages of the two groups lie on the outside beside the shaft bearings and their outlet radial-flow stages lie on the inside one beside the other.
  • a cooler is suitably interposed between the two combined axialand radial-flow stage groups.
  • FIG. 1 shows a compressor which comprises four lowpressure, axial-flow stages succeeded by three high-pressure, radial-flow stages.
  • FIG. 2 shows a compressor which comprises adjustable axial-flow stages 811 and a non-adjustable axial-flow stage 16.
  • the compressor shown in FIG. 3 has two stage groups, the first of which consists of five series-connected axialflow stages and a succeeding radial-flow stage, whereas the second stage group has four axial-flow stages and a succeeding radial-flow stage.
  • FIG. 4 shows .a modification of FIG. 3 and includes an additional radial-flow stage, which is floatingly mounted on one end of the shaft outside the shaft bearing and succeeds the second stage group.
  • FIG. 5 is a graph showing an operating characteristic curve a for the pressure rise in percent of a centrifugal compressor plotted against the volumetric intake rate.
  • FIG. 6 shows a comparison between the power consumption in percent of a cooled radial-flow compressor having swirl-controlled first stages and of an axialand radial-flow compressor having adjustable stationary blades in the axial-flow section, in the same range of about -110% of the normal volumetric intake rate at full load
  • the compressor shown in FIG. 1 comprises a low-pressure section '1 comprising four axial-flow stages, and a succeeding high-pressure part '2 consisting of three radialflow stages. All axial-flow stages'and radial-flow stages are mounted in a common housing 3 and are carried by a common shaft 4 between two supporting bearings 5, 6 of this shaft.
  • the last radial-flow stage has an inlet in a direction which is opposite to the two other radialfiow stages and the axial-flow stages so that the axial thrust is at least partly compensated. More radial-flow stages may be reversed in this way, except for the first one, the inlet of which is suitably directly opposite to the outlet of the last axial-flow stage, for flow-dynamical reasons.
  • An interstage cooler is arranged between every two adjacent radial-flow stages.
  • two interstage coolers are provided, which are suitably symmetric-ally arranged on both sides of the compressor and for this reason are not apparent from the longitudinal sectional view which is shown.
  • the stationary blades of the axial stages are adjustable according to the invention with the aid of a common adjusting linkage 7. Details of such an adjusting device, which is known per so, are apparent on a larger scale from FIG. 2.
  • a special feature resides in that the intermediate levers 12-15 leading to the stationary blades of the various adjustable axial-flow stages 8-11 have different lengths.
  • the intermediate lever 12 associated with the first axial-flow stage 8 is the shortest.
  • the intermediate lever of each succeeding, adjustable axial-flow stage is somewhat longer than that of the preceding stage.
  • the blades of succeeding stages are adjusted through different angle-s.
  • the relatively largest angle of adjustment is obtained in the first stage 8 and the relatively smallest angle in the last stage 11. Tests have shown that the different angles of adjustment are suitably selected so that a reduced total pressure rise of all adjustable axial-flow stages is divided so as to obtain progressively increasing stage pressure rises, and that for a zero overall pressure rise the pressure rise of each stage is also zero.
  • Such an adjusting device enables the respective axialflow stages to be entirely or largely shut olf in consideration of. their different blade lengths so that during partial-load operation the fluid to be compressed can flow substantially without obstruction through these stages with a power consumption which is very small in comparison with that of the swirl control employed with radialfiow stages.
  • the adjustable axialflow stages 811 are succeeded by-a non-adjustable axialflow stage 16.
  • One stage group 20 comprises five series-connected axial-flow stages and a succeeding radial-flow stage.
  • the other stage group 21 comprises four axial-flow stages and a succeeding radial-flow stage. Both stage groups are disposed in such a relation to each other that the inlet axial-flow stages are disposed on the outside beside the shaft bearings and the radial-flow stages are arranged on the inside one beside the other.
  • a cooler 24 is arranged between the two stage groups 20, 21.
  • This cooler may be attached to the compressor housing, not shown, or may be separate from this hous ing.
  • the volume of the pro-compressed fluid is considerably reduced from the outlet of the radial stage of the first stage group 20 to the inlet of. the first axial-flow stage of the second stage group 21.
  • FIG. 4 shows an additional radial-flow stage 25, which is floatingly mounted on one end portion of the shaft 19 outside the shaft bearing 23 and succeeds the second stage group 21.
  • a second cooler 26 is arranged between the outlet radial-flow stage of the second stage group 21 and the additional radial-flow stage 25. While retaining all other advantages of a compressor according to the invention, this embodiment enables an even higher overall compression ratio.
  • the axialflow stages are provided at least in part with adjustable stationary blades for a good adaptation to changing operating conditions.
  • curve a represents the operating characteristic curve of a centrifugal compressor.
  • the pressure rise in percent is plotted against the volumetric intake rate.
  • These curves b (for the pure axial-flow compressor) and c (for the combined axialand radial-flow compressor) have been measured and computed for two compressors which have the same final pressure and indicate that the compressor according to the invention has a lower power consumption throughout the range which is represented. This difference is particularly high in the partial-load region.
  • a multi-sta-ge centrifugal compressor comprising, in combination, a common drive shaft extending between a pair of axially spaced bearings; two serially connected multi-stage sections supported on said common drive shaft between said bearings; a common housing enclosing both multi-stage sections between said bearings; each multistage section comprising plural axial flow fluid inlet stages and at least one radial flow fluid outlet stage, the axial flow stages being at the axially outer end of each section and the radial flow stages being disposed axially between the two sets of axial flow stages; the fluid flowing serially through the two sect-ions in respective opposed axial directions; at least one axial stage of each section having adjustable guide vanes; adjusting means operable to adjust said guide vanes; and a cooler connected to the outlet of at least one radial stage.
  • a multi-stage centrifugal compressor as claimed in claim 1, in which plural axial stages of each section have said adjustable guide vanes; said adjusting means including respective crank arms each connected to the guide vanes of a respective axial stage; a common operator connected to the free ends of said crank arms to simultaneously pivot all of said crank arms; said crank arms having different lengths with the lengths of. the crank arms varying in a manner such that the adjustment angle for the first axial stage has the largest value, with the adjustment angle for each succeeding axial stage being progressively smaller.
  • a m-ulti-sta-ge centrifugal compressor as claimed in claim 1, including an individual radial flow stage supported on said common drive shaft and arranged, in the direction of fluid flow through said compressor, downstream of said two serial connected multi-stage sections; and a cooler connected between the outlet of the downstream one of the two serially connected multi-stage sections and the inlet of said individual radial stage.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US348729A 1963-03-02 1964-03-02 Axial-and radial-flow, multistage centrifugal compressor Expired - Lifetime US3303989A (en)

Applications Claiming Priority (1)

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DEG0037187 1963-03-02

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CH (1) CH419426A (de)
DE (1) DE1428106B2 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3508839A (en) * 1968-01-15 1970-04-28 Sulzer Ag Plural-stage axial compressor
US3795458A (en) * 1971-01-20 1974-03-05 Bbc Sulzer Turbomaschinen Multistage compressor
US5961282A (en) * 1996-05-07 1999-10-05 Institut Francais Du Petrole Axial-flow and centrifugal pumping system
US6547514B2 (en) 2001-06-08 2003-04-15 Schlumberger Technology Corporation Technique for producing a high gas-to-liquid ratio fluid
US20130318988A1 (en) * 2012-03-16 2013-12-05 Mtu Aero Engines Gmbh Aircraft engine with turbine heat exchanger bypass
US20170370284A1 (en) * 2016-06-22 2017-12-28 Rolls-Royce Plc Gas turbine engine
CN109707671A (zh) * 2019-02-02 2019-05-03 沈阳透平机械股份有限公司 一种轴流式压缩机的内置静叶可调机构
US10428823B2 (en) 2014-11-06 2019-10-01 General Electric Company Centrifugal compressor apparatus

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS597708A (ja) * 1982-07-07 1984-01-14 Hitachi Ltd 軸流機械における静翼取付角可変装置

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1093374A (en) * 1911-12-15 1914-04-14 Ingersoll Rand Co Pressure-equalizer for rotary blowers.
CH70671A (de) * 1915-06-24 1915-10-16 Oerlikon Maschf Zweistufiges Gebläse
CH71107A (de) * 1915-07-05 1915-12-01 Oerlikon Maschf Mehrstufiges Turbo-Gebläse
CH71244A (de) * 1915-07-12 1915-12-16 Oerlikon Maschf Mehrstufiges Turbo-Gebläse
CH102821A (de) * 1922-08-12 1924-01-02 Bbc Brown Boveri & Cie Mehrstufiger Kreiselverdichter.
US2161517A (en) * 1936-10-26 1939-06-06 Escher Wyss Machinenfabriken A Axial flow turbo compressor
US2371706A (en) * 1941-02-10 1945-03-20 Eugene Andre Paul Axial flow compressor
US2500070A (en) * 1945-06-15 1950-03-07 Westinghouse Electric Corp Multistage, axial flow, gas compressor
US3060680A (en) * 1957-12-30 1962-10-30 Rolls Royce By-pass gas-turbine engine and control therefor
GB921842A (en) * 1960-01-25 1963-03-27 Bbc Brown Boveri & Cie Fluid-flow machines such as axial-flow compressors

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1093374A (en) * 1911-12-15 1914-04-14 Ingersoll Rand Co Pressure-equalizer for rotary blowers.
CH70671A (de) * 1915-06-24 1915-10-16 Oerlikon Maschf Zweistufiges Gebläse
CH71107A (de) * 1915-07-05 1915-12-01 Oerlikon Maschf Mehrstufiges Turbo-Gebläse
CH71244A (de) * 1915-07-12 1915-12-16 Oerlikon Maschf Mehrstufiges Turbo-Gebläse
CH102821A (de) * 1922-08-12 1924-01-02 Bbc Brown Boveri & Cie Mehrstufiger Kreiselverdichter.
US2161517A (en) * 1936-10-26 1939-06-06 Escher Wyss Machinenfabriken A Axial flow turbo compressor
US2371706A (en) * 1941-02-10 1945-03-20 Eugene Andre Paul Axial flow compressor
US2500070A (en) * 1945-06-15 1950-03-07 Westinghouse Electric Corp Multistage, axial flow, gas compressor
US3060680A (en) * 1957-12-30 1962-10-30 Rolls Royce By-pass gas-turbine engine and control therefor
GB921842A (en) * 1960-01-25 1963-03-27 Bbc Brown Boveri & Cie Fluid-flow machines such as axial-flow compressors

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3508839A (en) * 1968-01-15 1970-04-28 Sulzer Ag Plural-stage axial compressor
US3795458A (en) * 1971-01-20 1974-03-05 Bbc Sulzer Turbomaschinen Multistage compressor
US5961282A (en) * 1996-05-07 1999-10-05 Institut Francais Du Petrole Axial-flow and centrifugal pumping system
US6547514B2 (en) 2001-06-08 2003-04-15 Schlumberger Technology Corporation Technique for producing a high gas-to-liquid ratio fluid
US20130318988A1 (en) * 2012-03-16 2013-12-05 Mtu Aero Engines Gmbh Aircraft engine with turbine heat exchanger bypass
US10428823B2 (en) 2014-11-06 2019-10-01 General Electric Company Centrifugal compressor apparatus
US20170370284A1 (en) * 2016-06-22 2017-12-28 Rolls-Royce Plc Gas turbine engine
CN109707671A (zh) * 2019-02-02 2019-05-03 沈阳透平机械股份有限公司 一种轴流式压缩机的内置静叶可调机构

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Publication number Publication date
DE1428106B2 (de) 1971-12-16
DE1428106A1 (de) 1969-02-06
CH419426A (de) 1966-08-31

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