US2469125A - Centrifugal compressor for high stage pressures - Google Patents

Centrifugal compressor for high stage pressures Download PDF

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Publication number
US2469125A
US2469125A US555790A US55579044A US2469125A US 2469125 A US2469125 A US 2469125A US 555790 A US555790 A US 555790A US 55579044 A US55579044 A US 55579044A US 2469125 A US2469125 A US 2469125A
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United States
Prior art keywords
rotor
inlet
blades
outlet
centrifugal compressor
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Expired - Lifetime
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US555790A
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English (en)
Inventor
Meisser Christian
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Sulzer AG
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Sulzer AG
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Publication of US2469125A publication Critical patent/US2469125A/en
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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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the invention relates to a centrifugal compressor for high stage-pressures and consists in that the blades of the rotor extend diagonally to the rotor axis and have at least two zones, whereby in the inlet'zone the angle of inclination of the backwardly bent blade-surface with respect to the peripheral direction increases from the value required for freedom from shock at the inlet at normal load to a maximum value, whilst in the outlet zone the blade-surfaces have a decreasing angle of inclination, whose cosine at the point of outlet is greater than the ratio of the relative velocity to twice the peripheral velocity, so that the angle of inclination is again reduced from the maximum value to a value at which the absolute outlet velocity does not exceed the velocity of sound to such an extent that Mach sound waves can be formed.
  • the angle of inclination with respect to the peripheral direction decreases up to the blade-outlet, whereby, in addition. to the desired reduction of v the absolute outlet velocity, a relative accelera tion of the flow occurs, which prevents any excessive loading of the blades or any deviation may be obtained at the part of the rotor where the diameter increases, for instance by a contion and service conditions by making the two parts of the rotor separately and of different materials.
  • the inlet part of the rotor being of smaller diameter, it is subjected to lower mechanical stresses than the outlet part.
  • the inlet part with its hub might be made of a casting, for instance of steel, light metal, or such like. It would also be possible to ilnish the blades of the inlet part together with the hub as one pressed part, for instance from some kind I of plastic material, such as Bakelite, Pressspahn, etc. Further the blades and. the hub of the inlet part could each be made separately as pressed parts and then fitted together, for instance by welding or by means of suitable grooves in the hub. The blades of the inlet part could be made together with the hub from one piece of metal by adopting some suitable method of machining, for instance, by milling from the solid or from pre-shaped material.
  • Making the rotor of the compressor in two parts has further the advantage that one and the same outlet part of the rotor can be adopted for different working conditions by fitting it with interchangeable inlet parts, since only the latter have to be suited within wide limits to changing working conditions.
  • the number of blades'of the inlet part or of the-several inlet parts may be the same as the number in the main rotor, or the number may be lessor greater. When the number of blades on the inlet part and on the outlet part of the rotor is the same,
  • the centrifugal compressor may be constructed in such a way that it is possible quickly to change the inlet part, or the several inlet parts, for parts with' a dlflerent inlet-characteristic.
  • Fixed or adjustable guide blades may be ar ranged in front of the inlet parts. If these guide blades are flxed, it would be possible to constructthem as supporting ribs connected to the inlet casing, for taking a rotor bearing.
  • the guide blades may be constructed so that they can be adjusted while the compressor is at rest or while it is running. They may be movable about the rotor axis or have an axis of rotation cutting or crossing the rotor axis.
  • the blades on one or several inlet parts of the rotor might also be arranged adjustable in the manner mentioned. In. the case of blades automatically adjustable duringservice, this could be effected by adopting electrical, hydraulic, pneumatic or mechanical means and dependent on one or several servicefactors, for instance the pressure of the medium handled.
  • the outlet part Whilst the blades of the inlet part have an increasin pitch and an increasing cross-section of flow and extend for the most part axially, the outlet part can have blades of a constant pitch and extend in a pronounced radial direction and less pronounced axial direction, thus'causing the angle of inclination of the blade with respect to the peripheral direction to be reduced, as desired, from the maximum value p: to the outlet angle B3.
  • the centrifugal compressor according to Fi 4 has a rotor part 9 at the outlet end which is machined, along with the blades ll'L'out or the.
  • the material used is preferably a lightmetal alloy of great tensile strength, for instance, Duralumin, Elektron, and such like, in order to be able towithstand the centrifugal stresses occurring at peripheral velocities of 400 m./sec.
  • FIG. I shows in longitudinal section a centrifugal compressor whose rotor is in one piece
  • Fig. 7 shows in longitudinal section a centrifugal compressor whose rotor is formed of four parts
  • Fig. 8 a blade arrangement for. that compressor developed along the line I1IIII in Fig. 7.
  • the centrifugal compressor according to Figs. 1 and 2 has a rotor l, which is provided with backwardly bent blades 2 extending diagonally to the rotor axis and arranged in the form of a screw.
  • the rotor I which has no central bore, is flanged to the shaft 3 and carried overhung in one or more bearings 4.
  • the covering hood 5 is connected to the rotor I.
  • the rotor I is surrounded by the casing 6 which leads through a diffusor 1 into the outlet spiral 8.
  • the blades 2 are inclined at the angle #1 to the peripheral direction u, as is obtained from the inlet triangle of velocities for given working con- "ditions'at normal loading for inlet free from shock, and amounts for instance to 30.
  • the angle increases up to a maximum value 52, and amounts for instance to 60.
  • the outlet zone the angle which the blade surface makes with and higher.
  • the rotor part 9 may be able to withstand the high centrifugal stresses, it is constructed, at least approximately, as a disc of uniform strength. In order to prevent any dangerous edge stresses this rotor part 9 is made without a central bore and flanged to the shaft 3, and it is also provided at the inlet end with a centered annular groove ll into which is inserted the central continuation of the hub i2 of the inlet part provided with the inlet blades l3 and secured to the rotor part 9 to prevent one of them turning with respect to the other.
  • the inlet part l2, i3 is secured against being axially displaced with respect to the rotor part 9.
  • the inlet blades l3, Fig. 4 are preferably made of aerofoil section and arranged according to the blade drawings in Figs. 5 and 6.
  • the two rotor parts 9 and I2, supported overhung at the inlet end, are surrounded by the casing 6 which leads. into the diifusor 1 and the outlet spiral 8.
  • the shape and arrangement of the blades correspond essentially to those shown in Figs. 1, 2 and 3.
  • the centrifugal compressor shown in Fig. 7 has a rotor part9 at the outlet end which is essentially shaped similarly to-the outlet part shown in Fig. 4.
  • the centered annular groove ll one inlet part I5 is inserted.
  • This has also a centered annular groove IS, in which the middle inlet part I! is held.
  • the first inlet part III is fixed on the middle inlet part.
  • the axial bolt I9 is fixed, whose free end has a plate 29' on which a bearing pin 2
  • the plate 20 keeps the inlet parts l5, l1 and I8 from being displaced axially.
  • the bearing pin M is supported within a covering hood 22, held by a 9 in uniform progression over all three inlet parts.
  • the two adjusting mechanisms can be coupled to each other according to a law of motion ensuring a high overall efficiency, and this combined adjustment may be effected automatically in accordance with one or more service factors or by hand. In this manner a high overall efliciency can be obtained over a wide range of working.
  • a centrifugal compressor suitable for high peripheral speeds comprising a rotor, to be driven at a peripheral speed not less than 300 meters per second, with a plurality of blades extending from the inlet part on a small diameter to the outlet part on a greater diameter, the latter part being spaced axially from the former, the blades being bent backwards throughout their length and having at least two zones, one, an inlet zone in which the angle of inclination of the backwardly bent blade surfaces with respect to the peripheral direction increases from the relatively small angle required for freedom from shock at the inlet at normal load to the maximum value attained from inlet to outlet, and the other, an outlet zone in which the angle of inclination of the backwardly bent blade surfaces with respect to the peripheral direction decreases from the maximum value attained from inlet to outlet to an angle at the outlet whose cosine is greater than the ratio of the relative velocity to twice the peripheral velocity.
  • a centrifugal compressor according to claim 1 in which the inlet and outlet parts of the rotor are separable members each carrying its own blading detachably assembled into a unitary rotor structure.
  • a centrifugal compressor according to claim 3 in which the outlet rotor member is formed at least approximately as a disc of uniform tensile strength and without any central bore.
  • a centrifugal compressor according to claim 4 in which the inlet rotor member consists of a relatively light blade carrying annulus assembled to the outlet member by clamping through its central bore.
  • a centrifugal compressor according to claim 1 in which the inlet'and outlet parts of the rotor are separable members each carrying its own blading detachably assembled into a unitary rotor structure and in which the blades in the inlet zone are offset. on the blades of the outlet zone.
  • a compressor according to claim 6 in which the offset of the blades in the inlet zone from the blades of the outlet zone can be adjusted by relative rotation of their respective rotor members about the rotor axis.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US555790A 1943-12-11 1944-09-26 Centrifugal compressor for high stage pressures Expired - Lifetime US2469125A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH2469125X 1943-12-11

Publications (1)

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US2469125A true US2469125A (en) 1949-05-03

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US555790A Expired - Lifetime US2469125A (en) 1943-12-11 1944-09-26 Centrifugal compressor for high stage pressures

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US (1) US2469125A (enrdf_load_stackoverflow)
NL (1) NL115026B (enrdf_load_stackoverflow)

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2859909A (en) * 1952-01-31 1958-11-11 Edward A Stalker Radial diffusion compressors having reduced rotor exits
US2896543A (en) * 1956-12-20 1959-07-28 Ethridge F Ogles Irrigation ditch pumping apparatus with reversible impeller
US2991927A (en) * 1958-02-03 1961-07-11 Thomas E Quick Apparatus for moving fluids
US2999315A (en) * 1953-04-24 1961-09-12 Benson Lehner Corp Graph transformation apparatus
US3059834A (en) * 1957-02-21 1962-10-23 Hausammann Werner Turbo rotor
US3316848A (en) * 1964-07-14 1967-05-02 Egger & Co Pump casing
US3433145A (en) * 1966-03-04 1969-03-18 Colchester Woods Impellers,especially for ventilators
US3444817A (en) * 1967-08-23 1969-05-20 William J Caldwell Fluid pump
US3574480A (en) * 1968-10-08 1971-04-13 Siemens Ag Semiaxial fan rotor
US3627447A (en) * 1969-03-17 1971-12-14 United Aircraft Canada Radial turbines
US3726605A (en) * 1969-06-30 1973-04-10 H Bachl Fluid-flow machine
US3782851A (en) * 1973-01-02 1974-01-01 Outboard Marine Corp Die castable centrifugal fan
US3904308A (en) * 1973-05-16 1975-09-09 Onera (Off Nat Aerospatiale) Supersonic centrifugal compressors
US3941506A (en) * 1974-09-05 1976-03-02 Carrier Corporation Rotor assembly
US4125344A (en) * 1975-06-20 1978-11-14 Daimler-Benz Aktiengesellschaft Radial turbine wheel for a gas turbine
US4183719A (en) * 1976-05-13 1980-01-15 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft (MAN) Composite impeller wheel with improved centering of one component on the other
JPS57127804U (enrdf_load_stackoverflow) * 1981-02-04 1982-08-09
FR2533977A1 (fr) * 1982-09-30 1984-04-06 Gen Electric Roue centrifuge a plusieurs etages
US5213473A (en) * 1990-09-15 1993-05-25 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Radial-flow wheel for a turbo-engine
US5364228A (en) * 1992-04-27 1994-11-15 Gebr, Becker Gmbh & Co. Turbine for gas compression
US6499953B1 (en) * 2000-09-29 2002-12-31 Pratt & Whitney Canada Corp. Dual flow impeller
US20050260070A1 (en) * 2004-05-19 2005-11-24 Delta Electronics, Inc. Heat-dissipating device
DE102006056820A1 (de) * 2006-03-01 2007-09-13 Institut für Luft- und Kältetechnik gGmbH Wasseraufbereitungsanlage
US20080092538A1 (en) * 2005-04-29 2008-04-24 Peter Fledersbacher Exhaust gas turbocharger for an internal combustion engine
US20080260528A1 (en) * 2005-11-25 2008-10-23 Mathias Weber Turbocharger
WO2009065894A1 (de) * 2007-11-20 2009-05-28 Mann+Hummel Gmbh Verdichterrad eines radialverdichters und verfahren zur herstellung eines solchen verdichterrades
US20170268527A1 (en) * 2014-12-11 2017-09-21 Kawasaki Jukogyo Kabushiki Kaisha Impeller for supercharger
US10428823B2 (en) 2014-11-06 2019-10-01 General Electric Company Centrifugal compressor apparatus

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1042506A (en) * 1912-03-15 1912-10-29 Charles Emile Jules De Vallat Propeller.
US1075300A (en) * 1904-12-10 1913-10-07 Gen Electric Centrifugal compressor.
US1341882A (en) * 1915-09-07 1920-06-01 Buffalo Forge Co Centrifugal fan
US1771939A (en) * 1926-10-19 1930-07-29 Rees Edmund Scott Gustave Propeller, pump, or fan
US2369051A (en) * 1942-07-10 1945-02-06 Sulzer Ag Welded turbine rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1075300A (en) * 1904-12-10 1913-10-07 Gen Electric Centrifugal compressor.
US1042506A (en) * 1912-03-15 1912-10-29 Charles Emile Jules De Vallat Propeller.
US1341882A (en) * 1915-09-07 1920-06-01 Buffalo Forge Co Centrifugal fan
US1771939A (en) * 1926-10-19 1930-07-29 Rees Edmund Scott Gustave Propeller, pump, or fan
US2369051A (en) * 1942-07-10 1945-02-06 Sulzer Ag Welded turbine rotor

Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2859909A (en) * 1952-01-31 1958-11-11 Edward A Stalker Radial diffusion compressors having reduced rotor exits
US2999315A (en) * 1953-04-24 1961-09-12 Benson Lehner Corp Graph transformation apparatus
US2896543A (en) * 1956-12-20 1959-07-28 Ethridge F Ogles Irrigation ditch pumping apparatus with reversible impeller
US3059834A (en) * 1957-02-21 1962-10-23 Hausammann Werner Turbo rotor
US2991927A (en) * 1958-02-03 1961-07-11 Thomas E Quick Apparatus for moving fluids
US3316848A (en) * 1964-07-14 1967-05-02 Egger & Co Pump casing
US3433145A (en) * 1966-03-04 1969-03-18 Colchester Woods Impellers,especially for ventilators
US3444817A (en) * 1967-08-23 1969-05-20 William J Caldwell Fluid pump
US3574480A (en) * 1968-10-08 1971-04-13 Siemens Ag Semiaxial fan rotor
US3627447A (en) * 1969-03-17 1971-12-14 United Aircraft Canada Radial turbines
US3726605A (en) * 1969-06-30 1973-04-10 H Bachl Fluid-flow machine
US3782851A (en) * 1973-01-02 1974-01-01 Outboard Marine Corp Die castable centrifugal fan
US3904308A (en) * 1973-05-16 1975-09-09 Onera (Off Nat Aerospatiale) Supersonic centrifugal compressors
US3941506A (en) * 1974-09-05 1976-03-02 Carrier Corporation Rotor assembly
US4125344A (en) * 1975-06-20 1978-11-14 Daimler-Benz Aktiengesellschaft Radial turbine wheel for a gas turbine
US4183719A (en) * 1976-05-13 1980-01-15 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft (MAN) Composite impeller wheel with improved centering of one component on the other
JPS57127804U (enrdf_load_stackoverflow) * 1981-02-04 1982-08-09
US4502837A (en) * 1982-09-30 1985-03-05 General Electric Company Multi stage centrifugal impeller
FR2533977A1 (fr) * 1982-09-30 1984-04-06 Gen Electric Roue centrifuge a plusieurs etages
US5213473A (en) * 1990-09-15 1993-05-25 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Radial-flow wheel for a turbo-engine
US5364228A (en) * 1992-04-27 1994-11-15 Gebr, Becker Gmbh & Co. Turbine for gas compression
US6499953B1 (en) * 2000-09-29 2002-12-31 Pratt & Whitney Canada Corp. Dual flow impeller
US20050260070A1 (en) * 2004-05-19 2005-11-24 Delta Electronics, Inc. Heat-dissipating device
US7607886B2 (en) * 2004-05-19 2009-10-27 Delta Electronics, Inc. Heat-dissipating device
US7870731B2 (en) * 2005-04-29 2011-01-18 Daimler Ag Exhaust gas turbocharger for an internal combustion engine
US20080092538A1 (en) * 2005-04-29 2008-04-24 Peter Fledersbacher Exhaust gas turbocharger for an internal combustion engine
US20080260528A1 (en) * 2005-11-25 2008-10-23 Mathias Weber Turbocharger
US8641382B2 (en) * 2005-11-25 2014-02-04 Borgwarner Inc. Turbocharger
DE102006056820A1 (de) * 2006-03-01 2007-09-13 Institut für Luft- und Kältetechnik gGmbH Wasseraufbereitungsanlage
WO2009065894A1 (de) * 2007-11-20 2009-05-28 Mann+Hummel Gmbh Verdichterrad eines radialverdichters und verfahren zur herstellung eines solchen verdichterrades
US10428823B2 (en) 2014-11-06 2019-10-01 General Electric Company Centrifugal compressor apparatus
US20170268527A1 (en) * 2014-12-11 2017-09-21 Kawasaki Jukogyo Kabushiki Kaisha Impeller for supercharger

Also Published As

Publication number Publication date
NL115026B (enrdf_load_stackoverflow) 1949-04-15

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