WO2001046562A1 - Machine a vis - Google Patents

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Publication number
WO2001046562A1
WO2001046562A1 PCT/US2000/034198 US0034198W WO0146562A1 WO 2001046562 A1 WO2001046562 A1 WO 2001046562A1 US 0034198 W US0034198 W US 0034198W WO 0146562 A1 WO0146562 A1 WO 0146562A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
rotors
end faces
screw machine
depressions
Prior art date
Application number
PCT/US2000/034198
Other languages
English (en)
Inventor
Xin Liu
Steven Shoulders
Daedra Studniarz
Original Assignee
Carrier Corporation
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 Carrier Corporation filed Critical Carrier Corporation
Priority to AU25813/01A priority Critical patent/AU2581301A/en
Publication of WO2001046562A1 publication Critical patent/WO2001046562A1/fr

Links

Classifications

    • 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
    • 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
    • F01C19/00—Sealing arrangements in rotary-piston machines or 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
    • F01C19/00—Sealing arrangements in rotary-piston machines or engines
    • F01C19/08—Axially-movable sealings for working fluids
    • F01C19/085—Elements specially adapted for sealing of the lateral faces of intermeshing-engagement type machines or engines, e.g. gear machines or engines

Definitions

  • a male rotor and a female rotor disposed in respective parallel overlapping bores defined within a rotor housing, coact to trap and compress volumes of gas. While such two rotor configurations are the most common design, screw machines are also known in the art having three, or more, rotors housed in respective overlapping bores so as to coact in pairs. Paired male and female rotors differ in their lobe profiles and in the number of lobes and flutes. For example, the female rotor may have six lobes separated by six flutes, the while conjugate male rotor may have five lobes separated by five flutes. Accordingly, each possible combination of lobe and flute coaction between the rotors occurs on a cyclic basis.
  • the rotors of a typical screw machine are mounted in bearings at each end so as to provide both radial and axial restraint. Nevertheless, in conventional practice, a certain amount of clearance in the axial direction must be provided between the end face of the rotors and the facing surface of the housing.
  • the need to provide an end running clearance is primarily the result of thermal growth of the rotors as a result of gas being heated in the compression process. Maintaining the desired end running clearance at an amount sufficient to ensure that contact does not occur between the end face of the rotors and the facing surface of the housing is important to reliable operation of the screw machine. Additionally, during operation, the pressure gradient in the fluid being compressed normally acts on the rotors in an axial direction tending to force the rotors toward the suction end of the screw machine, thereby tending to increase the end running clearance.
  • the rotors grow in the axial direction toward the end casing at the discharge end of the housing due to thermal growth resulting from the fluid being heated in the compression process. This thermal growth of the rotors tends to reduce the end-running clearance.
  • the aforenoted axial pressure gradient tends to push the rotors in an axial direction towards the suction end of the screw machine, thereby tending to increase the end running clearance.
  • the interface surface area between the rotor end faces and the end casing is reduced by reason of a reduction in the surface area of at least either the rotor end faces or the facing surface of the outlet casing.
  • discrete, non-interconnected, relatively large depressions are formed in the rotor end faces.
  • the rotor end faces may have a textured surface providing a multiplicity of interconnected, relatively small depressions.
  • the surface of the outlet casing facing the rotor end faces is textured or otherwise provided with depressions.
  • Figure 1 is a transverse section through a screw machine
  • Figure 2 is a partially sectioned view of the screw machine of Figure 1;
  • Figure 3 is an enlarged view of a portion of the discharge end of the screw machine of Figure 1;
  • Figure 4 is an end view of the rotors taken along line 4-4 of Figure 3 showing one embodiment of the end faces of the rotors;
  • Figure 5 is an end view of the rotors showing an alternate embodiment of the end faces of the rotors:
  • Figure 6 is an end view of the rotors showing a further alternate embodiment of the end faces of the rotors.
  • a screw machine 10 such as a screw compressor, having a rotor housing or casing 12 with a pair of overlapping bores 13 and 15 located therein.
  • Female rotor 14 is located in bore 13 and male rotor 16 is located in bore 15.
  • the bores 13 and 15 generally extend along parallel axes, A and B, respectively.
  • female rotor 14 has six lobes 14A separated by six flutes, while male rotor 16 has five lobes separated by five flutes. Accordingly, the rotational speed of rotor 16 will be 6/5 or 120% of that of rotor 14.
  • Either the female rotor 14 or the male rotor 16 may be connected to a prime mover (not illustrated) and serve as the driving rotor. Other combinations of the number of female and male lands and grooves may also be used.
  • rotor 14 has a shaft portion 23 with an end face 24 formed on the end of the rotor 14 radially outward of the shaft portion 23.
  • Shaft portion 23 of rotor 14 is supported in outlet or discharge casing 53 by one, or more, bearing(s) 30.
  • rotor 16 has a shaft portion 25 with an end face 26 formed on the end of the rotor 16 radially outward of the shaft portion 26.
  • Shaft portion 25 of rotor 16 is supported in outlet casing 53 by one, or more bearing(s) 31.
  • Suction side shaft portions 27 and 29 of rotors 14 and 16, respectively, are supportingly received in rotor housing 12 by roller bearings 32 and 33, respectively.
  • rotor 16 rotates engaging rotor 14 and causing its rotation.
  • This end running clearance 60 is defined as the region between the closest interface surfaces of the rotor end faces 24 and 26 and the facing surface 51 of the end plate 55. This end running clearance 60 establishes a potential gas leakage path, both circumferential and radial, between rotor end faces 24 and 26 and the end plate 55 of the outlet casing 53. As in conventional oil-flooded compressors, lubrication oil that naturally flows into the end- running clearance 60 serves as a seal to reduce gas leakage through the end-running clearance.
  • the interface surface area defining the end running clearance 60 between the rotor end faces 24 and 26 and the facing surface 51 of the end plate 55 of the outlet casing 53 is reduced by removing material from the rotor end faces 24 and 26 or the facing surface 51 of the end plate 55.
  • the friction losses caused by viscous forces due to the oil in the region between the rotor end faces 24 and 26 of the respective rotors and the facing surface 51 of the end plate 51 of the outlet casing 53 is reduced.
  • depressions 44, 44A and 46, 46A are formed in the rotor end faces 24 and 26, respectively.
  • Depression 44 is provided in the central region of the end face 24 of the female rotor 14 to extend about the shaft 23 and depressions 44A are formed in the lobes 14A.
  • depression 46 is provided in the central region of the end face 26 of the male rotor 16 to extend about the shaft 25 and depressions 46A are formed in the lobes 16A.
  • the shoulders 45 separate the respective depressions 44 and 44A in the rotor end face 24 and the shoulders 47 separate the respective depressions 46 and 46A in the rotor end face 26.
  • the depressions 44, 44A, 46 and 46A comprise discrete, unconnected depressions and the interface surface area is reduced to the surface area of the shoulders 45 and 47.
  • the depth of the depressions 44, 44A, 46 and 46A although not critical to the invention, advantageously lies in the range from about 0.002 inch to about 0.50 inch.
  • discrete depressions 54 and 56 are formed in the rotor end faces 24 and 26, respectively, in a petal- like pattern.
  • each of the plurality of depressions 54 and 56 are discrete, unconnected depressions separated by shoulder portions 55 and 57, respectively, and the interface surface area is reduced to the surface area of the shoulder portions.
  • the depth of the depressions 54 and 56 although not critical to the invention, again advantageously lies in the range from about 0.002 inch to about 0.50 inch.
  • each of the rotor end faces 24 and 26 comprises a textured surface having a plurality of small depressions 64 formed between rises 66 and dispersed extensively across substantially the entire surface of the rotor end faces.
  • the interface surface area is reduced to the surface area of the rises rather than the surface area of the overall rotor end face.
  • the depth of the depressions 64 are not critical to the invention, but advantageously have a depth in the range from about 0.001 inch to about 0.20 inch.
  • the interface area between the rotor end faces 24 and 26 and the facing surface 51 of the outlet casing 53 may be reduced in accordance with the present invention by providing depressions in or a textured surface on the facing surface 51.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Applications Or Details Of Rotary Compressors (AREA)

Abstract

L'invention concerne une machine à vis (10) comprenant un logement pour rotor (12) définissant des alésages superposés (13, 15). Un rotor femelle (14) est placé dans un alésage (13) et un rotor mâle (16) est placé dans un alésage (15). Les faces frontales (24, 26) des rotors femelle et mâle présentent, respectivement, des évidements (44, 46, 54, 56, 64) formés dans leur surface, de cet fait, la zone d'interface avec la surface opposée (51) du boîtier de sortie (53) est réduite.
PCT/US2000/034198 1999-12-20 2000-12-15 Machine a vis WO2001046562A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU25813/01A AU2581301A (en) 1999-12-20 2000-12-15 Screw machine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US17276799P 1999-12-20 1999-12-20
US60/172,767 1999-12-20

Publications (1)

Publication Number Publication Date
WO2001046562A1 true WO2001046562A1 (fr) 2001-06-28

Family

ID=22629148

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2000/034198 WO2001046562A1 (fr) 1999-12-20 2000-12-15 Machine a vis

Country Status (3)

Country Link
US (1) US20010031213A1 (fr)
AU (1) AU2581301A (fr)
WO (1) WO2001046562A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1111187A2 (fr) * 1999-12-20 2001-06-27 Carrier Corporation Machine à rotors à vis
BE1017582A3 (nl) * 2007-03-05 2009-01-13 Atlas Copco Airpower Nv Vloeistofgeinjecteerd schroefcompressorelement.

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP7096044B2 (ja) * 2018-03-30 2022-07-05 株式会社日立産機システム スクリューロータ及び流体機械本体
WO2019188322A1 (fr) * 2018-03-30 2019-10-03 株式会社日立産機システム Rotor à vis, corps principal de machine à fluide, et machine à fluide
WO2020044715A1 (fr) * 2018-08-29 2020-03-05 株式会社日立産機システム Rotor à vis et corps principal de machine à fluide du type à vis

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2232592A1 (de) * 1972-07-03 1974-01-24 Wankel Felix Vom abgas angetriebener lader fuer brennkraftmaschinen
GB2100353A (en) * 1981-06-17 1982-12-22 Zimmern Bernard Rotary positive-displacement fluidmachines
GB2131487A (en) * 1979-10-04 1984-06-20 Praner Frank Casimir Sealing the running fit between relatively movable surfaces
JPS59176487A (ja) * 1983-03-25 1984-10-05 Hitachi Ltd スクリユ−圧縮機のロ−タ
DE3609996A1 (de) * 1986-03-25 1987-10-01 Mahle Gmbh Schraubenverdichter
US5350286A (en) * 1990-11-30 1994-09-27 Kabushiki Kaisha Naekawa Seisakusho Liquid injection type screw compressor with lubricant relief chamber

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2232592A1 (de) * 1972-07-03 1974-01-24 Wankel Felix Vom abgas angetriebener lader fuer brennkraftmaschinen
GB2131487A (en) * 1979-10-04 1984-06-20 Praner Frank Casimir Sealing the running fit between relatively movable surfaces
GB2100353A (en) * 1981-06-17 1982-12-22 Zimmern Bernard Rotary positive-displacement fluidmachines
JPS59176487A (ja) * 1983-03-25 1984-10-05 Hitachi Ltd スクリユ−圧縮機のロ−タ
DE3609996A1 (de) * 1986-03-25 1987-10-01 Mahle Gmbh Schraubenverdichter
US5350286A (en) * 1990-11-30 1994-09-27 Kabushiki Kaisha Naekawa Seisakusho Liquid injection type screw compressor with lubricant relief chamber

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 009, no. 034 (M - 357) 14 February 1985 (1985-02-14) *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1111187A2 (fr) * 1999-12-20 2001-06-27 Carrier Corporation Machine à rotors à vis
EP1111187A3 (fr) * 1999-12-20 2002-05-02 Carrier Corporation Machine à rotors à vis
BE1017582A3 (nl) * 2007-03-05 2009-01-13 Atlas Copco Airpower Nv Vloeistofgeinjecteerd schroefcompressorelement.

Also Published As

Publication number Publication date
AU2581301A (en) 2001-07-03
US20010031213A1 (en) 2001-10-18

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