US3179330A - Rotary engines and compressors - Google Patents

Rotary engines and compressors Download PDF

Info

Publication number
US3179330A
US3179330A US134447A US13444761A US3179330A US 3179330 A US3179330 A US 3179330A US 134447 A US134447 A US 134447A US 13444761 A US13444761 A US 13444761A US 3179330 A US3179330 A US 3179330A
Authority
US
United States
Prior art keywords
rotors
rotor
casing
clearances
threads
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.)
Expired - Lifetime
Application number
US134447A
Inventor
Ian A Maccoll
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.)
James Howden and Co Ltd
Original Assignee
James Howden and Co Ltd
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 James Howden and Co Ltd filed Critical James Howden and Co Ltd
Application granted granted Critical
Publication of US3179330A publication Critical patent/US3179330A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00—Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00—Rotary-piston machines or engines
    • F01C1/08—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing
    • F01C1/082—Details specially related to intermeshing engagement type machines or engines
    • F01C1/084—Toothed wheels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01C—ROTARY-PISTON OR OSCILLATING-PISTON MACHINES OR ENGINES
    • F01C1/00—Rotary-piston machines or engines
    • F01C1/08—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing
    • F01C1/12—Rotary-piston machines or engines of intermeshing engagement type, i.e. with engagement of co- operating members similar to that of toothed gearing of other than internal-axis type
    • F01C1/14—Rotary-piston machines or engines 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
    • F01C1/16—Rotary-piston machines or engines 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
    • 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
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B2730/00—Internal combustion engines with pistons rotating or oscillating with relation to the housing
    • F02B2730/05—Internal combustion engines with pistons rotating or oscillating with relation to the housing with pistons intermeshing as gear wheels; with helicoidal rotors
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the tip diameters of the threads are gradually reduced from xat the inlet end to x at the outlet end to provide a taper t.
  • the root diameters of the grooves are gradually reduced from y at the inlet end to y at the outlet end to provide a taper t.
  • the tapers t are identical and are shown exaggerated for the sake of'clearness.
  • grooves of the female rotor and the threads of the male rotor are of arcuate profile, and the pitch circles from which the grooves and threads of the rotors are struck gradually-reduce in diameter from end to end of the rotors to provide thetaper;

Description

April 20, 1965 A, MaccoLL 3,179,330
ROTARY ENGINES AND COMPRESSORS Filed Aug. 28, 1961 3 Sheets-Sheet 1 FIG] U Inventor [W 44/572? 4414' ('01;
A ttorneyS' April 20, 1965 A. M coLL ROTARY ENGINES AND COMPRESSORS 3 Sheets-Sheet 2 Filed Aug. 28. 1961 A tlorneys A ril 20, 1965 I. A. MaccoLL 3,179,330
I ROTARY ENGINES AND COMPRESSORS Filed Aug. 28, 1961 3 Sheets-Sheet 3 Inventor /4/v ,4L/5'IJ4/e M65011 Attorneys United States Patent'O 3,179,330 ROTARY ENGINES AND COMPRESSORS Ian A. MacColl, Stockport, Cheshire, England, assignor to James Howden and Company Limited, Glasgow, Great Britain, a British company Filed Aug. 28, 1961, Ser. No. 134,447 Claims priority, application Great Britain, Aug. 30, 1960, 29,920/ 60 Claims. (Cl. 230-143) This invention relates to rotary compressors and engines of the type comprisinga casing presenting two sideby-side intersecting bores, two side-by-side rotors rotatably mounted in the respective bores and having helical grooves and threads which mesh at the intersection of the bores, inlet and outlet ports respectively at opposite ends of the casing, and means for driving the rotors so that the working medium is compressed or expanded in working chambers formed between the rotors and the casing, and there is a gradual increase in temperature from end to end of the rotors and a corresponding gradual increase in the thermal expansion of the rotors from end to end of the rotors.
Generally, in the aforesaid type of compressor or engine the casing presents parallel cylindrical bores, and the rotors have parallel axes of rotation and are interconnected through timing .gears. A compressor or engine of the aforesaid type is described for example in British patent specification No. 627,162.
Up to now it has been the practice to .machine the rotors so that the root and tip diameters of the grooves and threads are constant throughout the length of the rotor. If the temperature of the rotors remained constant throughout their length during operation, thethermal expansion of the rotors and consequently the. general clearances between the intermeshing parts and between the rotors and the casing would be uniform throughout the length of the rotors although they might differ from the clearances when cold. In practice, however, the temperature of the rotors and consequently their thermal expansion may vary along their length in operation. This variation is dependent upon the cooling arrangements when such are provided, and upon the degree of expansion or compression of the working medium in the working chambers.
When a rotor is machined, as previously referred to, the clearances when cold must be such as to provide the requisite working clearances for the hottest part of the rotor when in operation. This means that the clearances at the colder end of the rotor are larger than necessar with a consequent loss of efiiciency.
The object of the invention is to so construct the'rotors that this reduction of eificiency is prevented or mitigated.
According to the present invention, in a rotary compressor or engine of theaforesaid type, the rotor and tip diameters of the grooves and threads of a rotormgradually reduce from end to end of the rotor to provide tapered clearances between the rotor on the one hand and the casing and second rotor on the other hand, said clearances gradually increasing in correspondence with said gradual increase in the thermal expansion of the rotors to permit said thermal expansion so that in operation optimum working clearances for maximum efliciency are provided at all points along the length of the rotors.
In one form of the invention the rotor is so machined that what may be termed the circumferential width of each thread is gradually reduced from end to end of the rotor, with consequent gradual increase in the circumferential width of each groove from end to end of the rotor.
3,179 ,330 Patented .Apr. 20, 1965 ice This tapering of the rotor may be present in the female rotor only, in the male rotor only, or in both rotors.
As an example of one way of carrying the invention into effect, when machining a female rotor the rotor may be inserted into a thread miller in such a way that the centre line of the rotor blank is arranged at a small angle to the centre line of the thread miller so that in the finished product there is a slight taper at the bottom of the grooves and the tips of the threads from end to end of the rotor. The degree of taper chosen may be such that the tapering feature disappears at the temperatures of normal operation. The variations of radial dimensions which are introduced by the invention will have little effect on the important clearances between the tips of the female threads and the developed portions of the male rotor threads or lobes, which.clearances are not afiected appreciably by the temperature gradient.
The following data, which is given by way of example only, relates to the degree of diametral taper we have found to be desirable in a particular design of female compressor rotor of 200 mm. diameter. The corresponding male rotor was not tapered.
In a compressor with a discharge pressure of 35 lbs. per square inch gauge, a taper of .004 inch was found to be satisfactory.
With a compressor discharging at.60 lbs. per sq. inch gauge a taper of .010 inch was necessary.
The. invention may be applied to compressors wherein the land combinations of the male and female rotors are 3/3, 4/ 4, 4/6 or other desired combination.
Although the invention has been describedin connection with a compressor only, it may also be applied in connection with an engine or machine in which. expansion of the working medium occurs instead of compression, with a consequent temperature gradient along the length of the rotor.
The invention is illustrated, by way of example, in the accompanying diagrammatic drawings as applied to compressors wherein both rotors are tapered.
In the drawings, FIGS. 1 and 2 are side views of a male and a female rotor; FIGS. 3 and 4 show profiles of a female and amale rotor of a compressor having a land combination of the male and female rotors of 4/6; and FIGS. 5 and 6 show a modified form of the rotors of FIGS. 3 and 4.
In FIGS. 1 and 2, the tip diameters of the threads are gradually reduced from xat the inlet end to x at the outlet end to provide a taper t. Similarly, the root diameters of the grooves are gradually reduced from y at the inlet end to y at the outlet end to provide a taper t. The tapers t are identical and are shown exaggerated for the sake of'clearness. v
FIG. 3.shows the profiles of a female rotor, the inlet end profile being shown by a full line a and the outlet end profile being shown by a broken line b, and
. FIG. 4 shows the corresponding profiles of the male rotor, the inlet end profile being shown by a full line 0 and the outlet end profile being shown by a broken line d.
The degree of'tapering has been exaggerated considerably for thesake of clearness of illustration.
The threads or lobes of the male rotor and the grooves of the female rotor are shown as having a radius R. This radius is constant throughout the length of the rotors. The pitch circles from which the lobes and grooves are struck are shown by chain-dotted lines for the inlet ends of the rotors, and by short spaced arcs from the outlet ends.
In FIG. 3 the pitch circles are shown by chain-dotted line e and spaced arcs f and in FIG. 4 they are shown by line g and arcs h.
considerably for the sake of clarity.
In this case the radius R2 (FIG. 6) ofthe male rotor lobes at the outlet end is less than the radius R1 of the lobes at the inlet end, and the radius R3 (FIG. 5) of the female rotor grooves at the outlet end is greater than the radius R1 of the grooves at the inlet end. This change in radius is combined with the reduction in pitch circle diameter from the inlet end to the outlet end to provide the required degree of taper.
In FIG. 5 the pitch circles are shown by chain-dotted lines It and spaced arcs p and in FIG. 6. by line q and arcs s.
I claim:
1. In a rotary compressor or engine comprising a casing] presenting two side-by-side intersecting bores, two side-by-side rotors rotatably mounted in the respective bores and having helical grooves and threads which mesh at the intersection of the bores, inlet and outlet ports respectively at opposite ends of the'casing, and means for driving the rotors so that the working medium is compressed or expanded in working chambers formed between the rotors and the casing and there is a gradual increase in temperature from end to end of the rotors and a corresponding gradual increase in the thermal expansion of the rotors from end to end of the rotors,
the root and tip diameters of the grooves and threads of a rotor gradually reduce from end to end of the rotor to provide tapered clearances between the rotor on the one hand and the casing-and second rotor on the other hand, said clearances gradually increasing in correspondence with said gradual increase in the thermal expansion of the rotors to permit said thermal expansion so that in operation optimum working clearances for maximum efiiciency are provided at all points along the length of the rotors.
2. A compressor or engine according to claim 1, wherein the reduction in the root diameter of the rotor is the same as the reduction in the tip diameter.
3. A compressor or engine according to claim 2, wherein the circumferential width of each thread of the tapered rotor is gradually reduced from end to end of the rotor with consequent gradual increase in the circumferential width of each groove from end to end of the rotor.
4. A compressor or engine according to claim 3, wherein the grooves or threads of the tapered rotor are of arcuate profie, and the pitch circles from which the grooves or threads are struck gradually reduce in diameter from end to end of the rotor to provide the taper.
5. A compressor or engine according to claim 4, wherein theradius of each groove or thread'of-the tapered rotor is the same from end to end of the rotor.
6. A compressor or engine according to claim 4, wherein the radius ofeach groove or thread of the tapered rotor increases or reduces from end to end of the rotor to contribute to the production of the-required degree of taper.
7. In a rotary compressor or engine comprising a casing presenting two parallel cylindrical intersecting bores, two male and female rotors mounted in the respective bores for rotation on parallel axes and having helical grooves and threads which mesh at the intersection of the bores, inletand outlet ports respectively at opposite ends of the casing, and means for driving the rotors so that the working medium is compressed or expanded in working chambers formed between the rotors and the casing and there is a gradual increase in temperature from end to end of the rotors and a corresponding gradual increase'in the thermal expansion of the rotors from end to end of the rotors the root and tip diameters of the grooves and threads of the rotors gradually reduce from end to end of the rotors to provide tapered clearances between the rotors and between the rotors and the casing, said clearances gradually increasing in correspondence with said gradual increase in the thermal expansion of the rotors to permit said thermal expansion so that in operation the taper of the clearances tends to disappear and optimum working clearances for maximum efliciency are provided at all points along thelength of the rotors.
8. A compressor or engine according to claim 7, wherein the grooves of the female rotor and the threads of the male rotor are of arcuate profile, and the pitch circles from which the grooves and threads of the rotors are struck gradually-reduce in diameter from end to end of the rotors to provide thetaper;
9. A compressor or engine according to claim 8, wherein the radius of each. groove or thread of each tapered rotor is the same from end to end of the rotor.
10. A compressor or engine according to claim 8, wherein the radius of the male rotor threads at one end is less than the radius of said threads at the other end, and the radius of the female rotor grooves at said one end is greater than the radius of said grooves at said other end, said change in radii from end to end of the rotors contributing to the formation of the desired tapered clearances.
. References Cited by the Examiner UNITED STATES PATENTS KARL .T. ALBRECHT, Primary Examiner.
LAURENCE V. EFNER, WILBUR J. GOODLIN,
JOSEPH H. BRANSON, JR., Examiners.

Claims (1)

1. IN A ROTARY COMPRESSOR OR ENGINE COMPRISING A CASING PRESENTING TWO SIDE-BY-SIDE INTERSECTIONG BORES, TWO SIDE-BY-SIDE ROTORS ROTATABLY MOUNTED IN THE RESPECTIVE BORES AND HAVING HELICAL GROOVES AND THREADS WHICH MESH AT THE INTERSECTION OF THE BORES, INLET AND OUTLET PORTS RESPECTIVELY AT OPPOSITE ENDS OF THE CASING, AND MEANS FOR DRIVING THE ROTORS SO THAT THE WORKING MEDIUM IS COMPRESSED OR EXPANDED IN WORKING CHAMBERS FORMED BETWEEN THE ROTORS AND THE CASING AND THERE IS A GRADUAL INCREASE IN TEMPERATURE FROM END TO END OF THE ROTORS AND A CORRESPONDING GRADUAL INCREASE IN THE THERMAL EXPANSION OF THE ROTORS FROM END TO END OF THE ROTORS, THE ROOT AND TIP DIAMETERS OF THE GROOVES AND THREADS OF A ROTOR GRADUALLY REDUCE FROM END TO END OF THE ROTOR TO PROVIDE TAPERED CLEARANCES BETWEEN THE ROTOR ON THE ONE HAND AND THE CASING AND SECOND ROTOR ON THE OTHER HAND, SAID CLEARANCES GRADUALLY INCREASING IN CORRESPONDENCE WITH SAID GRADUAL INCREASE IN THE THERMAL EXPANSION OF THE ROTORS TO PERMIT SAID THERMAL EXPANSION SO THAT IN OPERATION OPTIMUM WORKING CLEARANCES FOR MAXIMUM EFFICIENCY ARE PROVIDED AT ALL POINTS ALONG THE LENGTH OF THE ROTORS.
US134447A 1960-08-30 1961-08-28 Rotary engines and compressors Expired - Lifetime US3179330A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB29920/60A GB968195A (en) 1960-08-30 1960-08-30 Improvements in or relating to rotary engines and compressors

Publications (1)

Publication Number Publication Date
US3179330A true US3179330A (en) 1965-04-20

Family

ID=10299344

Family Applications (1)

Application Number Title Priority Date Filing Date
US134447A Expired - Lifetime US3179330A (en) 1960-08-30 1961-08-28 Rotary engines and compressors

Country Status (3)

Country Link
US (1) US3179330A (en)
DE (1) DE1403534A1 (en)
GB (1) GB968195A (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3283996A (en) * 1963-09-12 1966-11-08 Svenska Rotor Maskiner Ab Screw rotor machine for elastic working fluid
US3307777A (en) * 1963-12-23 1967-03-07 Svenska Rotor Maskiner Ab Screw rotor machine with an elastic working fluid
US4089625A (en) * 1974-12-21 1978-05-16 Comprotek, S. A. Rotary gas machine
US4475878A (en) * 1982-09-27 1984-10-09 Hitachi, Ltd. Screw rotor with tooth form produced by thermal deformation and gear backlash
US4522576A (en) * 1982-12-23 1985-06-11 Societe Anonyme D.B.A. Volumetric machine with conical screws
US4952125A (en) * 1988-04-06 1990-08-28 Hitachi, Ltd. Nonlubricated screw fluid machine
US4963079A (en) * 1986-10-24 1990-10-16 Hitachi, Ltd. Screw fluid machine with high efficiency bore shape
US20050089433A1 (en) * 2003-01-15 2005-04-28 Kazuhiro Matsumoto Screw compressor and method of manufacturing rotors thereof
US20080292487A1 (en) * 2007-05-21 2008-11-27 Gm Global Technology Operations, Inc. Tapered Rotor Assemblies for a Supercharger
US20100260637A1 (en) * 2007-12-07 2010-10-14 Daikin Industries, Ltd. Single-screw compressor
US20150118093A1 (en) * 2012-05-08 2015-04-30 Ralf Steffens Spindle compressor
CN106401947A (en) * 2016-11-16 2017-02-15 中国石油大学(华东) Screw rotor with variable pitch and variable meshing clearance
CN113153742A (en) * 2021-02-24 2021-07-23 西安交通大学 Variable-line double-screw rotor and design method thereof
CN115853771A (en) * 2023-02-16 2023-03-28 冰轮环境技术股份有限公司 Low-temperature BOG double-screw compressor

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3220516A1 (en) * 1982-06-01 1983-12-01 Karl Prof.Dr.-Ing. 3000 Hannover Bammert DRYING SCREW MACHINE
DE3277846D1 (en) * 1982-09-24 1988-01-28 Hitachi Ltd Method for producing a pair of screw rotors of a screw compressor
DE3278039D1 (en) * 1982-10-25 1988-03-03 Hitachi Ltd Screw rotor machine
GB2608630A (en) * 2021-07-08 2023-01-11 Leybold Gmbh Screw pump, screw rotor, method of manufacturing a screw rotor, and use of a screw pump or a screw rotor

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1164546A (en) * 1913-04-29 1915-12-14 Alfons H Neuland Displacement apparatus.
US1677980A (en) * 1925-08-05 1928-07-24 Montelius Carl Oscar Josef Rotary pump, motor, meter, or the like
GB384355A (en) * 1931-08-05 1932-12-08 Frederick Charles Greenfield Improvements in and relating to rotary machines for the compression and propulsion of
FR789211A (en) * 1935-04-24 1935-10-25 Cfcmug Rotary positive displacement motor or compressor
GB464475A (en) * 1934-10-16 1937-04-16 Milo Ab Improvements in rotary engines
US2134153A (en) * 1936-02-05 1938-10-25 S H Johnston Gear pump
US2210152A (en) * 1939-05-22 1940-08-06 Nellie M Gottschalt Gear pump
US2294805A (en) * 1942-03-28 1942-09-01 Robert B Robinson Rotary engine construction
US2477797A (en) * 1945-08-06 1949-08-02 Nellie M Gottschalt Gear pump with wear compensating means
US2922377A (en) * 1957-09-26 1960-01-26 Joseph E Whitfield Multiple arc generated rotors having diagonally directed fluid discharge flow
US2931308A (en) * 1957-03-29 1960-04-05 Improved Machinery Inc Plural intermeshing screw structures
US2939745A (en) * 1958-07-02 1960-06-07 Improved Machinery Inc Discharge apparatus
US3072065A (en) * 1959-09-08 1963-01-08 Leland A Borden Fluid means

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1164546A (en) * 1913-04-29 1915-12-14 Alfons H Neuland Displacement apparatus.
US1677980A (en) * 1925-08-05 1928-07-24 Montelius Carl Oscar Josef Rotary pump, motor, meter, or the like
GB384355A (en) * 1931-08-05 1932-12-08 Frederick Charles Greenfield Improvements in and relating to rotary machines for the compression and propulsion of
GB464475A (en) * 1934-10-16 1937-04-16 Milo Ab Improvements in rotary engines
FR789211A (en) * 1935-04-24 1935-10-25 Cfcmug Rotary positive displacement motor or compressor
US2134153A (en) * 1936-02-05 1938-10-25 S H Johnston Gear pump
US2210152A (en) * 1939-05-22 1940-08-06 Nellie M Gottschalt Gear pump
US2294805A (en) * 1942-03-28 1942-09-01 Robert B Robinson Rotary engine construction
US2477797A (en) * 1945-08-06 1949-08-02 Nellie M Gottschalt Gear pump with wear compensating means
US2931308A (en) * 1957-03-29 1960-04-05 Improved Machinery Inc Plural intermeshing screw structures
US2922377A (en) * 1957-09-26 1960-01-26 Joseph E Whitfield Multiple arc generated rotors having diagonally directed fluid discharge flow
US2939745A (en) * 1958-07-02 1960-06-07 Improved Machinery Inc Discharge apparatus
US3072065A (en) * 1959-09-08 1963-01-08 Leland A Borden Fluid means

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3283996A (en) * 1963-09-12 1966-11-08 Svenska Rotor Maskiner Ab Screw rotor machine for elastic working fluid
US3307777A (en) * 1963-12-23 1967-03-07 Svenska Rotor Maskiner Ab Screw rotor machine with an elastic working fluid
US4089625A (en) * 1974-12-21 1978-05-16 Comprotek, S. A. Rotary gas machine
US4475878A (en) * 1982-09-27 1984-10-09 Hitachi, Ltd. Screw rotor with tooth form produced by thermal deformation and gear backlash
US4522576A (en) * 1982-12-23 1985-06-11 Societe Anonyme D.B.A. Volumetric machine with conical screws
US4963079A (en) * 1986-10-24 1990-10-16 Hitachi, Ltd. Screw fluid machine with high efficiency bore shape
US4952125A (en) * 1988-04-06 1990-08-28 Hitachi, Ltd. Nonlubricated screw fluid machine
US5064363A (en) * 1988-04-06 1991-11-12 Hitachi, Ltd. Non-lubricated screw machine with a rotor having a taper and varied helical angle
US7040845B2 (en) 2003-01-15 2006-05-09 Hitachi Industries Co., Ltd. Screw compressor and method of manufacturing rotors thereof
US20050089433A1 (en) * 2003-01-15 2005-04-28 Kazuhiro Matsumoto Screw compressor and method of manufacturing rotors thereof
US7044724B2 (en) * 2003-01-15 2006-05-16 Hitachi Industries Co., Ltd. Screw compressor and method of manufacturing rotors thereof
US20050147519A1 (en) * 2003-01-15 2005-07-07 Kazuhiro Matsumoto Screw compressor and method of manufacturing rotors thereof
US7882826B2 (en) * 2007-05-21 2011-02-08 GM Global Technology Operations LLC Tapered rotor assemblies for a supercharger
US20080292487A1 (en) * 2007-05-21 2008-11-27 Gm Global Technology Operations, Inc. Tapered Rotor Assemblies for a Supercharger
US8568119B2 (en) * 2007-12-07 2013-10-29 Daikin Industries, Ltd. Single screw compressor
US20100260637A1 (en) * 2007-12-07 2010-10-14 Daikin Industries, Ltd. Single-screw compressor
US20150118093A1 (en) * 2012-05-08 2015-04-30 Ralf Steffens Spindle compressor
JP2015519508A (en) * 2012-05-08 2015-07-09 ステファン ラルフＳＴＥＦＦＥＮＳ， Ｒａｌｆ Spindle compressor
CN106401947A (en) * 2016-11-16 2017-02-15 中国石油大学(华东) Screw rotor with variable pitch and variable meshing clearance
CN113153742A (en) * 2021-02-24 2021-07-23 西安交通大学 Variable-line double-screw rotor and design method thereof
CN113153742B (en) * 2021-02-24 2022-07-12 西安交通大学 Variable-line double-screw rotor and design method thereof
CN115853771A (en) * 2023-02-16 2023-03-28 冰轮环境技术股份有限公司 Low-temperature BOG double-screw compressor

Also Published As

Publication number Publication date
DE1403534A1 (en) 1969-01-30
GB968195A (en) 1964-08-26

Similar Documents

Publication Publication Date Title
US3179330A (en) Rotary engines and compressors
US2804260A (en) Engines of screw rotor type
US3632239A (en) Rotatable worm fluid compression-expansion machine
US3151806A (en) Screw type compressor having variable volume and adjustable compression
US2174522A (en) Rotary screw apparatus
US4508496A (en) Rotary, positive-displacement machine, of the helical-rotor type, and rotors therefor
US2481527A (en) Rotary multiple helical rotor machine
US2975963A (en) Rotor device
US2473234A (en) Helical asymmetrical thread forms for fluid devices
US4028026A (en) Screw compressor with involute profiled teeth
EP0009916B1 (en) Rotary positive displacement machines
US3945778A (en) Compressors and expansion machines of the single worm type
US4963079A (en) Screw fluid machine with high efficiency bore shape
US3565558A (en) Rotary pump with sliding vanes
US3777723A (en) Rotary internal combustion engine
US3722480A (en) Rotary combustion engine with improved firing channel
US3279682A (en) Screw air compressors
US4492546A (en) Rotor tooth form for a screw rotor machine
US3138110A (en) Helically threaded intermeshing rotors
Lysholm A new rotary compressor
US2491365A (en) Balanced gear pump
US4673344A (en) Screw rotor machine with specific lobe profiles
US6719547B2 (en) Offset thread screw rotor device
US2441771A (en) Yieldable drive for rotors
US2001800A (en) Rotor for rotary engines