US3481532A - Compressor - Google Patents

Compressor Download PDF

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Publication number
US3481532A
US3481532A US692252A US3481532DA US3481532A US 3481532 A US3481532 A US 3481532A US 692252 A US692252 A US 692252A US 3481532D A US3481532D A US 3481532DA US 3481532 A US3481532 A US 3481532A
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United States
Prior art keywords
stage
stages
compressor
rotors
male
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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
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US692252A
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English (en)
Inventor
Grover D Fraser
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.)
Ingersoll Rand Co
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Ingersoll Rand Co
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Publication date
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Publication of US3481532A publication Critical patent/US3481532A/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

Definitions

  • This invention relates to compressors and in particular to an improved two-stage, oil-flooded, helical lobe, gas compressor.
  • prior art two-stage, helical lobe compressors it is customary to arrange the two stages in line, forming an extended structure requiring considerable installation space.
  • Other prior art two-stage gas compressors alternatively, are arranged with the stages in surmounting relationship, creating an extremely tall structure.
  • the inline type of prior art gas compressors have structural lengths that are dictated by the sum of the extended length of each stage and, in addition, the dimension necessary between the stages for the journaling of the shafts.
  • the surmounting type or elevated type of two-stage compressors have structural heights dictated by the radii of the rotors in stacked relationship and, in addititon, the space required for the volutes for inlet and outlet chambers.
  • the prior art in-line, two-stage compressors customarily dispose the inlets and outlets at same, corresponding positions for each stage. That is, the inlet for the first stage would be on a terminal end of the stage, and its outlet at the opposite end thereof feeding to the immediately adjacent inlet of the second stage, with the second stage terminating at the opposite end of said second stage.
  • This arrangement creates an in-line, unrelieved thrust loading of thefcompressor.
  • a feature of this invention comprises the first stage male rotor in line with, and coupled to, the second stage male rotor shaft, and having the female rotors of the two stages disposed one above and the second below their respective male rotors so as to define a combination of surmounting and in-line stages; that is, offset .or bi-level stages.
  • This is the teaching of a preferred embodiment of the invention as set forth herein.
  • clearly an alternate embodiment, within the spirit of myinvention, could contemplate a compressor rotated 90, or more or less.
  • the offset stages would be laterally disposed, and the inlet, outlet, and inter-stage ducting would be disposed above and below, rather than having the latter side-mounted as taught by the bi-level configuration presented herein.
  • the practice of forming either one or the other will be dictated by the accommodations and convenient disposition of loading in the Work area or place of use.
  • Another feature of this invention comprises having the Patented Dec. 2, 1969 inelts for the first and second stages at the opposite, terminal ends of the machine, and the outlets centrally located therebetween.
  • FIGURE 1 is a plan view of the gas compressor according to the invention.
  • FIGURE 2 is an elevational view, in cross-section, of the gas compressor of FIG. l.
  • the novel compressor has a first stage 1, and a second stage 2, with side-mounted inlet and outlet ports.
  • FIG. 2 more clearly illustrates the two stages in off-set, bi-level relationship-
  • the female rotor 3 of the first stage is shown mounted above the first stage male rotor 4.
  • the male rotor 5 of the off-set second stage is shown coupled, in line, with the male rotor 4 of the first stage, and its mating female rotor 6 is shown mounted there below.
  • the two male rotors 4, 5 are mounted together, in line, on male rotor shaft 7.
  • Male rotor shaft 7 is integral with second stage male rotor 5, in this embodiment.
  • First stage male rotor 4 is mounted on a portion of shaft 7 extending from rotor 5, and is secured thereto by a fastener 8.
  • This mounting arrangement of the male rotors 4 and 5 is wholly arbitrary. Other arrangements, equally within the spirit of my invention, will occur to others.
  • the shaft 7 can be totally separate of the rotors, there being provided means for fastening each rotor thereto; alternatively, the shaft 7 could be integral with first stage male rotor ⁇ 4.
  • the first stage inlet 9 is shown as a port with an associated volute 10 about the outer end of the first stage 1.
  • the first stage outlet 11 is seen venting out of the central area of the machine.
  • the second stage inlet 12 is shown with its associated volute 13 at the opposite terminal end of the machine.
  • the discharge or outlet 14 of second stage 2 is disposed adjacent the inner end of rotor 6.
  • Apertures 15 are provided in bearing caps 16 for the feeding of high-pressure oil to the second stage rotors 5 and 6, to counter the axial thrust of the second stage and to lubricate the shaft bearings 17.
  • Apertures 15 have check valves, or the like (not shown), to prohibit a reverse flow of oil outward therefrom.
  • Port 18, formed in housing 19 adjacent the inner journaled end of second stage female rotor 6, is an oil inlet for shaft bearing 20; port 18 also, like apertures 15, has a check valve, or the like (not shown).
  • Means not shown, but widely known and practiced in the art, provide for oil injection, directly into the first stage compression chamber l 21, for sealing and cooling, and for lubrication of bearings 22 through 25. Oil put into the compressor is carried out with the discharging compressed gas and can be removed therefrom by means of a separator.
  • the first stage outlet 11 is conducted to the second stage inlet 12, in the direction of the arcuate arrow (FIG. l) by means of piping (not shown) throughconnecting therebetween and secured to flanges 26 and 27.
  • Shims 28 are disposed within the bearing and end caps 1-6, 29 of each stage to provide for proper adjustment of rotor-to-housing axial clearance.
  • the end caps 29 and 30 of the first stage and the bearing caps 1-6 of the second stage close and seal the rotor chambers 21 Iand 31. Also,
  • thrust bearings 32 are disposed between bearing caps 16 and the shaft ends of rotors 5 and l6. Finally, a source of high-pressured oil 33 is coupled to apertures 15, and drive means (not shown) power the compressor by rotating an extending section 7 of shaft 7.
  • each stage develops a thrust toward the opposite terminal ends of the machine but, as the discharge for each is centrally located, the thrust loading of the male rotor shafts is partly compensated; the axial urgings of each of the male rotors are in opposition.
  • This provides a novel dynamic balance of much of the normally developed thrust loading.
  • the high pressure oil supplied to the secand stage via bearing caps 16 additionally overcomes some of the thrust developed in the second stage.
  • This in combination, provides a largely dynamically balanced, two-stage, axial compressor.
  • the geometric packaging taught by the instant disclosure provides -a compressor offering a less gross conguration.
  • My disclosure teaches the coupling of outwardly thrusted male rotors 4 and S on a common shaft 7, to derive therefrom ya mutual counter-action of the individually developed thrust loading of each individual male rotors.
  • an alternate embodiment of my novel compressor can contemplate inwardly thrusted male rotors, on a common shaft, providing mutually canceling thrust loading.
  • the gas inputs would be disposed centrally of the compressor, and the outputs would be near the terminal ends thereof.
  • such an alternate embodiment would be, clearly, within the spirit of my invention as described herein.
  • a gas compressor comprising: an elongate housing; iirst and second compressor stages disposed therein; said stages together having ⁇ a pair of means for the inlet of gas to, and a pair of means for the outlet of gas from, said stages; wherein one of said pair of means is disposed adjacent the ends of said housing; land said other pair of means is disposed centrally of said housing; and further including rst means coupled to one of said stages for countering axial thrust developed by said one stage and for lubricating said one stage;
  • said rst means comprising means for impelling pressurized oil against said one stage; and wherein said rst and second stages each have male and female rotors, said male rotors are coupled together in line, said female rotors are parallel to each other, each of 4 said male rotors is in meshing engagement with only one of said female rotors, and said male rotors are disposed on a common shaft which is intermediate of said female rotors.
  • a gas compressor according to claim 1, wherein: said one pair is said pair of inlet means.
  • a gas compressor according to claim 1, wherein: one of said stages is disposed to develop axial thrust in a given direction, and the other of said stages is disposed to develop axial thrust in a direction other than said given direction.
  • a gas compressor according to claim 1, wherein: one of said stages is disposed to develop axial thrust in a given direction, and the other of said stages is disposed to develop Iaxial thrust in a direction counter to said given direction.
  • a gas compressor according to claim 1, further including second means coupled to said one stage for countering said axial thrust.
  • a gas compressor according to claim 5, wherein: said second means comprise the other of said stages.
  • a gas compressor according to claim 1, wherein: said first and second stages have a given axis common to both and are coupled together therealong; said first stage has a further axis other than said given axis; and said second stage has a further yaxis distinct from said given and said other axis.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Applications Or Details Of Rotary Compressors (AREA)
  • Rotary-Type Compressors (AREA)
US692252A 1967-12-20 1967-12-20 Compressor Expired - Lifetime US3481532A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US69225267A 1967-12-20 1967-12-20

Publications (1)

Publication Number Publication Date
US3481532A true US3481532A (en) 1969-12-02

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Application Number Title Priority Date Filing Date
US692252A Expired - Lifetime US3481532A (en) 1967-12-20 1967-12-20 Compressor

Country Status (6)

Country Link
US (1) US3481532A (ja)
JP (1) JPS4835803B1 (ja)
BE (1) BE725847A (ja)
DE (1) DE1815163A1 (ja)
FR (1) FR1596245A (ja)
GB (1) GB1218130A (ja)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3658452A (en) * 1969-11-18 1972-04-25 Shimadzu Corp Gear pump or motor
US3848422A (en) * 1972-04-27 1974-11-19 Svenska Rotor Maskiner Ab Refrigeration plants
US4044562A (en) * 1974-05-02 1977-08-30 Will Clarke England Multirotary energy conversion valve
US4487176A (en) * 1982-07-29 1984-12-11 Kosheleff Patrick A Rotary positive displacement motor
DK151056B (da) * 1972-04-27 1987-10-19 Svenska Rotor Maskiner Ab Fremgangsmaade til drift af et koeleanlaeg
US4792294A (en) * 1986-04-11 1988-12-20 Mowli John C Two-stage screw auger pumping apparatus
US4944657A (en) * 1989-03-01 1990-07-31 Mowli John C Two-stage pumping apparatus with low shear first stage
US5267837A (en) * 1992-09-23 1993-12-07 Mowli John C Two-stage pumping apparatus with non-meshing first stage augers
US20040191092A1 (en) * 2003-03-28 2004-09-30 Donoho Michael R. Multiple pump housing
US20070071625A1 (en) * 2002-11-21 2007-03-29 International Dispensing Corporation Blending pump assembly
US20090000680A1 (en) * 2002-11-21 2009-01-01 International Dispensing Corporation Blending pump assembly
US20090288648A1 (en) * 2008-05-21 2009-11-26 Gm Global Technology Operations, Inc. Superchargers with dual integral rotors
US20100098572A1 (en) * 2008-10-16 2010-04-22 Giuseppe Rago High speed gear pump
US20100275634A1 (en) * 2008-02-06 2010-11-04 Tetsuya Okamoto Refrigeration apparatus
CN102597522A (zh) * 2009-11-20 2012-07-18 加特可株式会社 螺旋齿轮泵
US20130146035A1 (en) * 2011-12-09 2013-06-13 Eaton Corporation Air supply system with two-stage roots blower
CN103410729A (zh) * 2013-08-26 2013-11-27 天津商业大学 卧式全封闭双级螺杆制冷压缩机
US20130319153A1 (en) * 2012-06-05 2013-12-05 Hamilton Sundstrand Corporation Flow and pressure ripple reduction with advance dual gear and bearing face cut
TWI512201B (zh) * 2013-02-06 2015-12-11 Fu Sheng Ind Co Ltd 流體機械的多段式螺旋轉子機構
CN110388320A (zh) * 2019-08-26 2019-10-29 珠海格力电器股份有限公司 具有平衡轴向力功能的双级螺杆压缩机及空调机组
WO2022179130A1 (zh) * 2021-02-26 2022-09-01 珠海格力电器股份有限公司 转子组件、压缩机及空调

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4846645B2 (ja) * 2007-03-30 2011-12-28 株式会社神戸製鋼所 スクリュ圧縮機
DE102008023594A1 (de) 2008-05-14 2009-11-19 Wabco Gmbh Kompressoreinheit

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698802A (en) * 1924-04-07 1929-01-15 Montelius Carl Oscar Josef Device for transferring energy to or from alpha fluid
US2100560A (en) * 1933-12-02 1937-11-30 Laval Steam Turbine Co Deep well pump
US2581451A (en) * 1949-09-14 1952-01-08 Laval Steam Turbine Co Mixing pump
US2659239A (en) * 1949-10-07 1953-11-17 Jarvis C Marble Independent synchronization
US2804260A (en) * 1949-07-11 1957-08-27 Svenska Rotor Maskiner Ab Engines of screw rotor type
US3279682A (en) * 1963-02-23 1966-10-18 Howden James & Co Ltd Screw air compressors

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1698802A (en) * 1924-04-07 1929-01-15 Montelius Carl Oscar Josef Device for transferring energy to or from alpha fluid
US2100560A (en) * 1933-12-02 1937-11-30 Laval Steam Turbine Co Deep well pump
US2804260A (en) * 1949-07-11 1957-08-27 Svenska Rotor Maskiner Ab Engines of screw rotor type
US2581451A (en) * 1949-09-14 1952-01-08 Laval Steam Turbine Co Mixing pump
US2659239A (en) * 1949-10-07 1953-11-17 Jarvis C Marble Independent synchronization
US3279682A (en) * 1963-02-23 1966-10-18 Howden James & Co Ltd Screw air compressors

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3658452A (en) * 1969-11-18 1972-04-25 Shimadzu Corp Gear pump or motor
US3848422A (en) * 1972-04-27 1974-11-19 Svenska Rotor Maskiner Ab Refrigeration plants
DK151056B (da) * 1972-04-27 1987-10-19 Svenska Rotor Maskiner Ab Fremgangsmaade til drift af et koeleanlaeg
US4044562A (en) * 1974-05-02 1977-08-30 Will Clarke England Multirotary energy conversion valve
US4108198A (en) * 1974-05-02 1978-08-22 Will Clarke England Multirotary energy conversion valve
US4487176A (en) * 1982-07-29 1984-12-11 Kosheleff Patrick A Rotary positive displacement motor
US4792294A (en) * 1986-04-11 1988-12-20 Mowli John C Two-stage screw auger pumping apparatus
US4944657A (en) * 1989-03-01 1990-07-31 Mowli John C Two-stage pumping apparatus with low shear first stage
US5267837A (en) * 1992-09-23 1993-12-07 Mowli John C Two-stage pumping apparatus with non-meshing first stage augers
US20070071625A1 (en) * 2002-11-21 2007-03-29 International Dispensing Corporation Blending pump assembly
US7404705B2 (en) * 2002-11-21 2008-07-29 International Dispensing Corporation Blending pump assembly
US20090000680A1 (en) * 2002-11-21 2009-01-01 International Dispensing Corporation Blending pump assembly
US8303277B2 (en) 2002-11-21 2012-11-06 International Dispensing Corporation Blending pump assembly
US20040191092A1 (en) * 2003-03-28 2004-09-30 Donoho Michael R. Multiple pump housing
US7682136B2 (en) * 2003-03-28 2010-03-23 Caterpillar Inc. Multiple pump housing
US20100275634A1 (en) * 2008-02-06 2010-11-04 Tetsuya Okamoto Refrigeration apparatus
US20090288648A1 (en) * 2008-05-21 2009-11-26 Gm Global Technology Operations, Inc. Superchargers with dual integral rotors
US20100098572A1 (en) * 2008-10-16 2010-04-22 Giuseppe Rago High speed gear pump
US8292597B2 (en) * 2008-10-16 2012-10-23 Pratt & Whitney Canada Corp. High-speed gear pump
CN102597522A (zh) * 2009-11-20 2012-07-18 加特可株式会社 螺旋齿轮泵
US20130146035A1 (en) * 2011-12-09 2013-06-13 Eaton Corporation Air supply system with two-stage roots blower
CN103256115A (zh) * 2011-12-09 2013-08-21 伊顿公司 带有两级罗茨鼓风机的空气供应系统
CN103256115B (zh) * 2011-12-09 2017-03-01 伊顿公司 带有两级罗茨鼓风机的空气供应系统
US9074524B2 (en) * 2011-12-09 2015-07-07 Eaton Corporation Air supply system with two-stage roots blower
CN103486024A (zh) * 2012-06-05 2014-01-01 哈米尔顿森德斯特兰德公司 利用超前的双齿轮和轴承端面切削部的流量和压力波动降低
US8944793B2 (en) * 2012-06-05 2015-02-03 Hamilton Sundstrand Corporation Flow and pressure ripple reduction with advance dual gear and bearing face cut
US20130319153A1 (en) * 2012-06-05 2013-12-05 Hamilton Sundstrand Corporation Flow and pressure ripple reduction with advance dual gear and bearing face cut
CN103486024B (zh) * 2012-06-05 2017-04-12 哈米尔顿森德斯特兰德公司 主齿轮泵、伺服齿轮泵及使用二者的飞行器
TWI512201B (zh) * 2013-02-06 2015-12-11 Fu Sheng Ind Co Ltd 流體機械的多段式螺旋轉子機構
CN103410729B (zh) * 2013-08-26 2015-07-01 天津商业大学 卧式全封闭双级螺杆制冷压缩机
CN103410729A (zh) * 2013-08-26 2013-11-27 天津商业大学 卧式全封闭双级螺杆制冷压缩机
CN110388320A (zh) * 2019-08-26 2019-10-29 珠海格力电器股份有限公司 具有平衡轴向力功能的双级螺杆压缩机及空调机组
WO2022179130A1 (zh) * 2021-02-26 2022-09-01 珠海格力电器股份有限公司 转子组件、压缩机及空调

Also Published As

Publication number Publication date
DE1815163A1 (de) 1969-07-24
BE725847A (ja) 1969-05-29
JPS4835803B1 (ja) 1973-10-31
FR1596245A (ja) 1970-06-15
GB1218130A (en) 1971-01-06

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