US3241744A - Rotary piston, positive displacement compressors - Google Patents

Rotary piston, positive displacement compressors Download PDF

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Publication number
US3241744A
US3241744A US313118A US31311863A US3241744A US 3241744 A US3241744 A US 3241744A US 313118 A US313118 A US 313118A US 31311863 A US31311863 A US 31311863A US 3241744 A US3241744 A US 3241744A
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Prior art keywords
rotors
compressor
portions
lands
chambers
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Expired - Lifetime
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US313118A
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English (en)
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Schibbye Lauritz Benedictus
Nilsson Hans Robert
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Svenska Rotor Maskiner AB
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Svenska Rotor Maskiner AB
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Priority to BE653766D priority Critical patent/BE653766A/xx
Priority to DE19641428274 priority patent/DE1428274C/de
Priority to GB3997464A priority patent/GB1067913A/en
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Publication of US3241744A publication Critical patent/US3241744A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C18/00—Rotary-piston pumps specially adapted for elastic fluids
    • F04C18/08—Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
    • F04C18/12—Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type
    • F04C18/14—Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
    • F04C18/16—Rotary-piston pumps specially adapted for elastic fluids of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with helical teeth, e.g. chevron-shaped, screw type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
    • F04C18/00—Rotary-piston pumps specially adapted for elastic fluids

Definitions

  • the present invention relates to rotary piston positive displacement compressors of the kind commonly referred to as screw compressors.
  • Such compressors are characterized generally by the creation of compression chambers formed by the intermeshing action of the lands of two intermeshing helically threaded rotors acting in conjunction with a suitably ported enclosing casing structure providing inlet and discharge ports, the compression chambers decreasing in volume as the rotors revolve between the time of cutofl of the chambers from the inlet port and the time of communication of the chambers with the discharge port, to thereby provide an in-built compression ratio within the compressor.
  • Dry compressors are characterized by the fact that the compression chambers are sealed by means by what is generally referred to as space packing, that is, packing afforded by extremely close clearances which are maintained between the intermeshing rotors through the intermediary of synchronizing or timing gears, and equally close clearances between the peripheries and the end surfaces of the rotors and the enclosing casing structure, established by precision manufacture of these parts.
  • the second and more recently developed category of such compressors is the so-called wet or flooded type, in which a liquid, usually oil such as ordinary lubricating oil, is introduced into the compression chambers for the dual purpose of providing a liquid seal for closing the clearance spaces and also for the purpose of cooling the gaseous fluid being compressed directly during the compression phase of the cycle.
  • a liquid usually oil such as ordinary lubricating oil
  • the compressor disclosed in the Bailey et al., US. Patent No. 3,073,514 granted January 15, 1963 constitutes a pioneer example of this latter category of compressor.
  • the present invention relates specifically to compressors of the wet or flooded type, and in one of its aspects has as a principal objective the improvement of the overall efiiciency of the compressor through the reduction of the churning losses created by the presence of the liquid in the compressor. This objective is obtained through the provision of novel improvements in structure hereinafter more fully described as this specification proceeds.
  • the compression chambers are defined in part by intermeshing portions of the lands of the cooperating rotors and in the normal operation of a wet compressor there is a certain amount of leakage or blow past these intermeshing surfaces of a mixture of gaseous fluid and liquid from the relatively high pressure within a compression chamber to the relatively lower pressure outside that chamber.
  • the liquid content of this mixture blowing from the compression chamber has been heated above inlet temperature by the heat of compression generated in the chamber, and from the standpoint of obtaining maximum operating efficiency it is highly desirable that the heat content of this liquid above inlet temperature be prevented as far as possible from being transferred to the incoming gaseous fluid before the latter reaches the compression chambers, in order to prevent temperature rise with consequent expansion of the gaseous fluid and with resultant decrease in volumetric capacity of the compressor.
  • FIG. 1 is a longitudinal section of a compressor embodying the invention, taken on line 1-1 of FIG. 3;
  • FIG. 2 is a top plan view of the apparatus shown in FIG. 1;
  • FIG. 3 is a cross sectional view taken on line 33 of FIG. 1;
  • FIGS. 4 to 7 inclusive are fragmentary cross sectional views similar to FIG. 3, showing modifications of the structure shown in FIG. 3 and adapted to be incorporated in machines of the kind shown in FIGS. 1 and 2;
  • FIG. 8 is a fragmentary section taken on line 8-8 of FIG. 7;
  • FIG. 9 is a view similar to FIG. 1, partly in section and partly in elevation and with portions of the rotor structure broken away, of a further embodiment of the invention.
  • FIG. 10 is a cross section taken on line 1010 of FIG. 9.
  • FIG. 11 is a view similar to FIG. 1, of the casing structure only of a further modification of the invention.
  • the compressor illustrated is of generally known construction and comprises a casing structure having a main barrel portion 10 closed at one end by a removable closure member 12 and providing a working space having intersecting co-planar bores 28 and 28' (FIG. 3).
  • these bores are cylindrical, with parallel axes, and house helically threaded intermeshing male and female rotors of which the male rotor 14 is seen in FIG. 1, the rotors having been omitted from FIG. 3 for clarification.
  • the barrel portion 10 of the casing has a low pressure port 16 located on one side of the plane of the axes of the rotors constituting what may be termed the low pressure side of the compressor and providing a radial inlet to the working space for the working fluid, and a high pressure port 18 on the opposite side of said plane constituting what may be termed the high-pressure side of the compressor and providing a radial-axial flow discharge of the compressed fluid, the direction of flow of the working fluid being indicated by the arrows 20 and 22 in FIG. 1.
  • male and female rotors as herein employed refer to the forms of rotors characteristic of this type of compressor, in which the pitch circle of the rotor lies at or adjacent to the bottom of the grooves in the rotor and the pitch circle of the female rotor is at or closely adjacent to the outer periphery of the rotor.
  • the intermeshing helical lands and grooves of the rotors form a series of chevron shaped compression chambers each composed of a portion of a male rotor groove and a portion of a female rotor groove, the base ends of the chambers being determined by the fixed transverse plane at the high pressure end of the working space and the apex ends of the chambers being formed by the places of intermesh between the coacting grooves.
  • the latter move axially from the low pressure toward the high pressure end of the working space as the rotors revolve to reduce the volumes of the compression chambers.
  • the major portion of the inlet 16 lies to one side, in this case the upper side, of the plane of the rotor axes, while the major portion of the discharge port 18 is located at the opposite or lower side of said plane.
  • the compression chambers are formed along the bottom portion of the rotors, the apex ends of the chambers traveling from right to left as viewed 4 in FIG. 1 with the rotors turning in the directions indicated by the arrows 34 and 34 in FIG. 3.
  • liquid is supplied to the working space of the compressor through a series of longitudinally spaced supply openings 32 located along the line of intersection 28a of the bores on the lower or high pressure side of the working space.
  • the compression chambers are of course defined by the walls of the rotor grooves on the one hand and the confronting portions of the casing structure on the other hand and in order for these chambers to be effectively sealed a close running clearance must be maintained between the relatively moving parts.
  • a close running clearance may advantageously be, in the case of a dry compressor, of the order of one-thousandth of an inch per inch of rotor diameter. In the case of a wet or flooded compressor, it may be less.
  • the portions of the walls of the bores which provide running clearance between the casing structure and the rotors is substantially confined to the area corresponding to the area of each compression chamber when it is first formed by two groove portions coming into intermeshing relation at the low pressure end of the working space.
  • the remaining portion of the walls of the bores is relieved to provide spacing in radial direction between the walls and the peripheries of the rotors, which spacing is many times greater than the spacing represented by the running clearances, and great enough to preclude any appreciable sealing effect between the relatively moving parts, even with liquid introduced into the working space.
  • the spacing provided by such relieved portions may be of the order of A1, A or a larger fraction of an inch.
  • the relieved and unrelieved portions of the barrel walls are separated by relatively abrupt shoulders 30 following helical lines which coincide respectively with the helix lines of the lands of the respective rotors.
  • the liquid which has far greater viscosity than the gaseous working fluid, is confined in close running clearance space only over the minimum required area, with consequent reduction of churning losses to a minimum.
  • the relieved portions of the walls of the barrel portion of the casing structure not only operate to minimize churning losses occasioned by the introduction of liquid into the working space, but also afford relatively open paths of communication over a large area between the inlet port proper and the grooves which are to be filled with the working fluid during the suction phase of the cycle. Thus in two different ways this feature of construction operates to improve overall efficiency.
  • the gaseous fluid trapped in the compression chambers and being compressed therein has two paths of egress or escape therefrom, one being through the running clearance between the rotors and the casing structure and the other being through the running clearance between the rotors along the line of intermesh therebetween.
  • the fluid escaping through these running clearances is a mixture of the gaseous fluid being compressed and of the sealing and cooling liquid that has been injected into the compression chambers. Since the compression process generates heat, the fluids leaking from the compression chambers are at a temperature higher than that of the fluid being drawn into the machine for compression, and by reference to FIG. 3, it will be seen that with the compression chambers being situated below the plane of the rotor axes and the low pressure zone of the working space being located above that plane, leakage from such chambers through the line of intermesh between the rotors is directed upwardly and in counter-current flow relation to the flow of the incoming working fluid. In the absence 5.
  • baflling means positioned to provide an obstruction preventing this adverse counter-current flow and to effect a kind of flow which will minimize the rate of heat exchange between the two bodies of fluid.
  • bafliing means is provided which in the present embodiment is in the form of a deflecting member disposed in radially spaced relation with respect to the peripheries of the rotors and extending longitudinally of the working space between the line of intermesh between the rotors, through which the leakage occurs, and the inlet through which the incoming supply of gaseous working fluid is flowing toward the rotors.
  • this baflling means takes the form of a deflector member 36 having symmetrically curved laterally extending blade portions each operative to deflect the fluids leaking past the line of intermesh between the rotors and impinging upon the blades, laterally toward the relieved side walls of the casing structure.
  • deflected flow results in a hot leakage liquid traversing the incoming gaseous fluid in a transverse flow relationship which results in the minimum of opportunity for heat exchange between the two media, with resultant minimum of preheating of the incoming gaseous fluid before compression takes place.
  • the relieved portions of the walls, at the level where the walls are impinged by liquid deflected by the deflector member 36, are provided with longitudinally extending drainage troughs 37, which advantageously are arranged with a slight pitch causing the liquidcaught therein to flow toward one end of the working space, from which the liquid may be drained through a suitable drainage opening 46 in the end wall of the casing structure.
  • FIG. 6 the blade portions of the deflector member 36 are curled inwardly at their outer edges to form troughs 38 into which the fluids impinging the deflective member are diverted and collected for drainage from the working space of the compressor through the drainage openings 46.
  • FIG. 7 still another embodiment is illustrated in which a corrector member 42 is disposed between the deflector member 36 and the inlet opening.
  • the deflected fluids pass between the inturned edges 40 of the deflected member at the overlying edges 44 of the collector member to accumulate in the trough formed by the deflector member itself and to drain through the opening 46.
  • inwardly projecting fins 48 are provided extending inwardly from the relieved wall portions closely adjacent to the shoulders 30, these fins advantageously having substantially the same helix angle as the shoulders and the fins acting as dams for stopping and turning back hot liquid tending to flow upwardly along the walls of the working space in the low pressure zone, in heat exchange relation to the incoming gaseous fluid in that zone.
  • the hot fluid thus intercepted by these fins is advantageously removed from the working chamber through suitably positioned drainage openings 50 appropriately located at the lower ends of these helically disposed fins.
  • FIGS. 9 and 10 illustrate one suitable embodiment for incorporating the principles of the invention in a compressor having an axial flow inlet.
  • the barrel portion 10 of the casing structure is provided wth a low pressure port 16 at one end thereof, the low pressure end closure member 12 being formed to provide an inlet passage for chamber 52 for working fluid in communication with port 16.
  • the discharge port 18 is of the combined radial-axial flow type located at the lower side of the compressor, while the major portion of the inlet port is located above the plane of the rotor axes.
  • the female rotor 15 as well as the male rotor 14! appears and as will be evident from these figures, the reduction in churning losses is achieved by confining the area of close running clearances between the rotors and the walls of the bores of the casing structure to the area representing the maximum size of the compression chambers.
  • this baflling means in the form of a radially inwardly projecting lip 54- is provided at the inlet end of the barrel portion of the casing, the radially inner face of this lip being located to provide only a close running clearance between itself and the inlet ends of the rotors.
  • FIG. 11 there is shown the casing portion of an embodiment in which the principles of the invention are applied to a compressor having a combined radial-axial flow inlet.
  • the radial flow portion of the inlet is indicated at lfia while the axial flow portion of the inlet is indicated at 16b.
  • the radial portion of the inlet is baffled by a deflector member 36 extending axially along the length of the radial portion of the ilet.
  • this baflie may advantageously be of the kind illustrated in FIG.
  • the easing structure is provided with an additional bafl le in the form of a lip 54 similar to that shown in FIG. 9.
  • FIGS. 9 and 11 omit illustration of baffling means such as the fins 48 shown in FIG. and the several drainage openings such as the openings 46 and 50 shown in FIGS. 5 to 8, it will be understood that all of these features of construction may readily be applied to the modifications of FIGS. 9 and 11 and also that the deflector 36 in the modifications shown in FIG. 11 may take any of the forms previously described.
  • a rotary piston, positive displacement compressor having a housing structure including a barrel portion comprised of intersecting bores with co-planar axes providing a working space extending longitudinally of said barrel portion, such structure having a low pressure port communicating with one end of said space to provide an inlet a major portion of which is located at one side of the plane of said axes constituting the low-pressure side of the compressor and a high pressure port spaced from said low pressure port to provide a discharge from said space the major portion of which is located at the opposite side of said plane constituting the high-pressure side of the compressor, rotors provided with helical lands and grooves having an effective wrap angle of less than 360 degrees rotatably mounted in said bores and comprising a male rotor having lands provided with convexly curved flanks and intervening grooves the major portions of which lie outside the pitch circle of the male rotor and a female rotor having lands provided with concavely curved flanks and intervening grooves the major portions of which lie inside the pitch circle of
  • a compressor as defined in claim 1 in which the portion of the housing having running clearance with respect to the peripheries of the rotors is of generally triangular form substantially conforming to the perimeter of said chambers when the apex ends thereof are at the inlet end of the compressor.
  • a compressor as defined in claim 2 in which the side edges of said triangular portion are helices having substantially the same helix angles as the helical crests of the lands of the respectively confronting rotors.
  • each of said side edges is defined by a relatively abrupt shoulder between the portion of the barrel wall providing run ning clearance and the relieved portion thereof providing said spacing.
  • a rotary piston, positive displacement compressor having a housing structure including a barrel portion comprised of intersecting bores with co-planar axes providing a working space extending longitudinally of said barrel portion, such structure having a low pressure port communicating with one end of said space to provide an inlet a major portion of which is located at one side of the plane of said axes constituting the low pressure side of the compressor and a high pressure port spaced from said low pressure port to provide a discharge from said space the major portion of which is located at the opposite side of said plane constituting the high pressure side of the compressor, rotors provided with helical lands and grooves having an effective wrap angle of less than 360 rotatably mounted in said bores and comprising a male rotor having lands provided with convexly curved flanks and intervening grooves the major portions of which lie outside the pitch circle of the male rotor and a female rotor having lands provided with concavely curved flanks and intervening grooves the major portions of which lie inside the pitch circle of the female
  • a compressor as defined in claim including baflle means located to provide an obstruction preventing direct flow to said inlet of liquid escaping from said compression chambers to the low pressure side of the compressor along the line of intermesh between the rotors.
  • a compressor as defined in claim 8 in which said low pressure port provides for radial admission of working fluid through the barrel portion of said casing structure and in which said baflie means comprises a deflector member extending longitudinally of said casing structure in radially spaced relation to said rotors, said deflector member being disposed between said line of intermesh and said low pressure inlet and being shaped to deflect fluids impinging thereon laterally toward relieved portions of the walls of said barrel portions adjacent to said low pressure inlet.
  • a compressor as defined in claim 9 in which said deflector member is symmetrical with respect to said line of intermesh and comprises curved blade portions conforming substantially to the curvature of the circumferences of the rotors.
  • a compressor as defined in claim 9 in which the radial spacing between the rotors and said deflector member is suflicient to preclude any appreciable sealing effect between the confronting members.
  • a compressor as defined in claim 14 in which said troughs are pitched to create drainage flow of the collected liquid and drainage openings are provided for discharge of said liquid from the working space of the compressor.
  • a compressor as defined in claim in which the laterally outer edges of said blade portions are inwardly bent to provide troughs for catching and conducting deflected liquid away from said low pressure inlet.
  • a compressor as defined in claim 16 in which drainage openings are provided in communication with said troughs for discharge of collected liquid from the working space of the compressor.
  • a compressor as defined in claim 10 in which a collecting member interposed between said deflecting member and said low pressure inlet cooperates with the former to provide a canal for draining the collected liquid away from the latter.
  • a compressor as defined in claim 5 in which said low pressure inlet provides for axial admission of working fiuid to said working space and said baflle means comprises a lip extending radially inwardly from the relieved portions of said bores at the inlet ends thereof which communicate with said low pressure inlet, said lip providing only a running clearance between itself and the inlet ends of said rotors to thereby restrict and substantially prevent free axial flow of liquid from the inlet ends of the walls of the relieved portions of said bores into the inlet passage leading to said low pressure inlet.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Applications Or Details Of Rotary Compressors (AREA)
US313118A 1959-09-01 1963-10-01 Rotary piston, positive displacement compressors Expired - Lifetime US3241744A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
BE653766D BE653766A (no) 1963-10-01 1964-09-30
DE19641428274 DE1428274C (de) 1963-10-01 1964-10-01 Mit Einspritzung von Dicht und Kühlflüssigkeit arbeitender außenachsi ger Drehkolbenverdichter
GB3997464A GB1067913A (en) 1963-10-01 1964-10-01 Rotary positive displacement compressors of the screw rotor type

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SE807659 1959-09-01

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US3241744A true US3241744A (en) 1966-03-22

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BE (1) BE594633A (no)
CH (1) CH404065A (no)
DE (1) DE1403595C3 (no)
DK (1) DK108685C (no)
FI (1) FI41187B (no)
FR (1) FR1268715A (no)
GB (1) GB966529A (no)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3311291A (en) * 1965-09-16 1967-03-28 Charles J Surdy Helical screw compressors
US3484823A (en) * 1967-12-15 1969-12-16 Cornell Aeronautical Labor Inc Multirecompression heater and/or high temperature compressor
US3677664A (en) * 1967-09-21 1972-07-18 Edwards High Vacuum Int Ltd Rotary mechanical pumps of the screw type
US3848422A (en) * 1972-04-27 1974-11-19 Svenska Rotor Maskiner Ab Refrigeration plants
USRE30994E (en) * 1978-03-02 1982-07-13 Dunham-Bush, Inc. Vertical axis hermetic rotary helical screw compressor with improved rotary bearings and oil management
US4443170A (en) * 1981-11-25 1984-04-17 Sullair Technology Ab Arrangement at oil-injected high-pressure screw compressor
WO1988000294A1 (en) * 1986-07-08 1988-01-14 Svenska Rotor Maskiner Ab Screw rotor compressor
DE4426761C2 (de) * 1994-07-22 2003-07-17 Grasso Gmbh Refrigeration Tech Schraubenverdichter
EP3467315A1 (en) 2017-10-04 2019-04-10 Ingersoll-Rand Company Screw compressor with oil injection at multiple volume ratios
US11149734B2 (en) * 2016-08-23 2021-10-19 Hitachi Industrial Equipment Systems Co., Ltd. Fluid machine

Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1319776A (en) * 1919-10-28 Wet vacuum pump
US1409868A (en) * 1920-08-05 1922-03-14 W M Hardwick Pump
US1424312A (en) * 1920-05-05 1922-08-01 George I Leonard Compressor
US1439628A (en) * 1921-06-07 1922-12-19 Emmett S Newton Pump
US1672571A (en) * 1926-03-27 1928-06-05 Leonard Pump & Motor Co Compressor
US1673260A (en) * 1926-03-11 1928-06-12 Stacold Corp Pump
US1675524A (en) * 1927-09-30 1928-07-03 Zajac Leopold Rotary compressor or motor
US2111568A (en) * 1935-02-12 1938-03-22 Lysholm Alf Rotary compressor
US2425000A (en) * 1943-03-27 1947-08-05 Joy Mfg Co Apparatus for automatically controlling pressure and temperature within aircraft cabins
US2474653A (en) * 1945-04-26 1949-06-28 Jarvis C Marble Helical gear compressor or motor
US2477004A (en) * 1945-10-20 1949-07-26 Joy Mfg Co Screw type air pump
US2477002A (en) * 1942-07-25 1949-07-26 Joy Mfg Co Gear type air pump with changespeed gearing and lubrication
US2642003A (en) * 1949-12-16 1953-06-16 Read Standard Corp Blower intake port
US2652192A (en) * 1947-06-13 1953-09-15 Curtiss Wright Corp Compound-lead screw compressor or fluid motor
US2755990A (en) * 1948-08-04 1956-07-24 Svenska Rotor Maskiner Ab Housing construction for displacement engines of screw rotor type
US2804260A (en) * 1949-07-11 1957-08-27 Svenska Rotor Maskiner Ab Engines of screw rotor type
US2849988A (en) * 1954-10-26 1958-09-02 Svenska Rotor Maskiner Ab Rotary devices and casing structures therefor
GB832386A (en) * 1956-05-17 1960-04-06 Svenska Rotor Maskiner Ab Improvements in rotary displacement machines
US2963884A (en) * 1957-04-17 1960-12-13 Atlas Copco Ab Screw-rotor compressors or motors
US3073514A (en) * 1956-11-14 1963-01-15 Svenska Rotor Maskiner Ab Rotary compressors
US3086474A (en) * 1960-02-18 1963-04-23 Laval Turbine Screw pump

Patent Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1319776A (en) * 1919-10-28 Wet vacuum pump
US1424312A (en) * 1920-05-05 1922-08-01 George I Leonard Compressor
US1409868A (en) * 1920-08-05 1922-03-14 W M Hardwick Pump
US1439628A (en) * 1921-06-07 1922-12-19 Emmett S Newton Pump
US1673260A (en) * 1926-03-11 1928-06-12 Stacold Corp Pump
US1672571A (en) * 1926-03-27 1928-06-05 Leonard Pump & Motor Co Compressor
US1675524A (en) * 1927-09-30 1928-07-03 Zajac Leopold Rotary compressor or motor
US2111568A (en) * 1935-02-12 1938-03-22 Lysholm Alf Rotary compressor
US2477002A (en) * 1942-07-25 1949-07-26 Joy Mfg Co Gear type air pump with changespeed gearing and lubrication
US2425000A (en) * 1943-03-27 1947-08-05 Joy Mfg Co Apparatus for automatically controlling pressure and temperature within aircraft cabins
US2474653A (en) * 1945-04-26 1949-06-28 Jarvis C Marble Helical gear compressor or motor
US2477004A (en) * 1945-10-20 1949-07-26 Joy Mfg Co Screw type air pump
US2652192A (en) * 1947-06-13 1953-09-15 Curtiss Wright Corp Compound-lead screw compressor or fluid motor
US2755990A (en) * 1948-08-04 1956-07-24 Svenska Rotor Maskiner Ab Housing construction for displacement engines of screw rotor type
US2804260A (en) * 1949-07-11 1957-08-27 Svenska Rotor Maskiner Ab Engines of screw rotor type
US2642003A (en) * 1949-12-16 1953-06-16 Read Standard Corp Blower intake port
US2849988A (en) * 1954-10-26 1958-09-02 Svenska Rotor Maskiner Ab Rotary devices and casing structures therefor
GB832386A (en) * 1956-05-17 1960-04-06 Svenska Rotor Maskiner Ab Improvements in rotary displacement machines
US3073514A (en) * 1956-11-14 1963-01-15 Svenska Rotor Maskiner Ab Rotary compressors
US2963884A (en) * 1957-04-17 1960-12-13 Atlas Copco Ab Screw-rotor compressors or motors
US3086474A (en) * 1960-02-18 1963-04-23 Laval Turbine Screw pump

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3311291A (en) * 1965-09-16 1967-03-28 Charles J Surdy Helical screw compressors
US3677664A (en) * 1967-09-21 1972-07-18 Edwards High Vacuum Int Ltd Rotary mechanical pumps of the screw type
US3484823A (en) * 1967-12-15 1969-12-16 Cornell Aeronautical Labor Inc Multirecompression heater and/or high temperature compressor
US3848422A (en) * 1972-04-27 1974-11-19 Svenska Rotor Maskiner Ab Refrigeration plants
USRE30994E (en) * 1978-03-02 1982-07-13 Dunham-Bush, Inc. Vertical axis hermetic rotary helical screw compressor with improved rotary bearings and oil management
US4443170A (en) * 1981-11-25 1984-04-17 Sullair Technology Ab Arrangement at oil-injected high-pressure screw compressor
WO1988000294A1 (en) * 1986-07-08 1988-01-14 Svenska Rotor Maskiner Ab Screw rotor compressor
DE4426761C2 (de) * 1994-07-22 2003-07-17 Grasso Gmbh Refrigeration Tech Schraubenverdichter
US11149734B2 (en) * 2016-08-23 2021-10-19 Hitachi Industrial Equipment Systems Co., Ltd. Fluid machine
EP3467315A1 (en) 2017-10-04 2019-04-10 Ingersoll-Rand Company Screw compressor with oil injection at multiple volume ratios
EP3467315B1 (en) * 2017-10-04 2021-03-24 Ingersoll-Rand Industrial U.S., Inc. Screw compressor with oil injection at multiple volume ratios
US11118585B2 (en) 2017-10-04 2021-09-14 Ingersoll-Rand Industrial U.S., Inc. Screw compressor with oil injection at multiple volume ratios
US11732715B2 (en) 2017-10-04 2023-08-22 Ingersoll-Rand Industrial U.S., Inc. Screw compressor with oil injection at multiple volume ratios
US12117001B2 (en) 2017-10-04 2024-10-15 Ingersoll-Rand Industrial U.S., Inc. Screw compressor with oil injection at multiple volume ratios

Also Published As

Publication number Publication date
DK108685C (da) 1968-01-29
FI41187B (no) 1969-06-02
DE1403595C3 (de) 1978-04-20
FR1268715A (fr) 1961-08-04
GB966529A (en) 1964-08-12
DE1403595B2 (de) 1977-08-25
BE594633A (fr) 1961-01-02
CH404065A (de) 1965-12-15
DE1403595A1 (de) 1969-01-09

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