US3829235A - Turbocharger compressor with dual collector chambers - Google Patents

Turbocharger compressor with dual collector chambers Download PDF

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Publication number
US3829235A
US3829235A US00202136A US20213671A US3829235A US 3829235 A US3829235 A US 3829235A US 00202136 A US00202136 A US 00202136A US 20213671 A US20213671 A US 20213671A US 3829235 A US3829235 A US 3829235A
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US
United States
Prior art keywords
frontal
vanes
adjoining
chambers
vane portions
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
US00202136A
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English (en)
Inventor
W Woollenweber
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.)
Wallace Murray Corp
Original Assignee
Wallace Murray Corp
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
Priority to BE791867D priority Critical patent/BE791867A/xx
Application filed by Wallace Murray Corp filed Critical Wallace Murray Corp
Priority to US00202136A priority patent/US3829235A/en
Priority to CA157,002A priority patent/CA981644A/en
Priority to ZA728247A priority patent/ZA728247B/xx
Priority to GB5403272A priority patent/GB1401486A/en
Priority to AU49280/72A priority patent/AU470945B2/en
Priority to FR7241885A priority patent/FR2163075A5/fr
Priority to AR245304A priority patent/AR197789A1/es
Priority to SE7215394A priority patent/SE389171B/sv
Priority to NL7215972A priority patent/NL7215972A/xx
Priority to JP47117275A priority patent/JPS4864507A/ja
Priority to BR008275/72A priority patent/BR7208275D0/pt
Priority to DE2257793A priority patent/DE2257793A1/de
Priority to ES409273A priority patent/ES409273A1/es
Priority to IT32134/72A priority patent/IT971247B/it
Application granted granted Critical
Publication of US3829235A publication Critical patent/US3829235A/en
Priority to JP1981103485U priority patent/JPS6128077Y2/ja
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/16—Combinations of two or more pumps ; Producing two or more separate gas flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/285—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/403—Casings; Connections of working fluid especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5826—Cooling at least part of the working fluid in a heat exchanger
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/584—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling or heating the machine
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • FIGS. 1 and 2 there is illus-
  • the desirability of reducing the temperature of su- 5 trated an exhaust gas driven turbocharger which is percharging air before its introduction into the intake of an internal combustion engine is well known.
  • US. Pat. No. 3,143,103 discloses a multi-stage turbocharger compressor having a separate, axial-flow stage for providing cooling air to an external heat exchanger through which passes the high pressure, high temperature air for charging the engine.
  • the concept of the present invention is embodied in a compact, single stage, centrifugal compressor in which the compressor wheel vanes are formed to provide a flow of relatively cool air at relatively low pressure, this flow being maintained separate from the flow of high temperature, high pressure air induced by the main portion of the vanes.
  • the separate air flows induced by the two portions of the wheel vanes are, normally, placed in heat exchange relation to each other in an external heat exchanger, however, since heat exchange can begin immediately, within the compressor wheel cover, the external heat exchanger may be of reduced size.
  • the frontal portions of the vanes, providing the cooling air flow may be separate from the adjoining vane portions and carried on a hub separate from that carrying the adjoining vane portions.
  • FIG. 1 is a side view of a turbocharger embodying the present invention with the compressor component shown in sections.
  • FIG. 2 is an end view of the turbocharger shown in FIG. 1.
  • FIG. 3 is a fragmentary, top view of the blades of the compressor wheel shown in FIG. 1.
  • FIG. 4 is a schematic illustration of the turbocharger shown in FIG. 1 incorporated into a system utilizing an exchanger and providing for the turbocharging of an internal combustion engine.
  • FIG. 5 is a fragmentary view of a portion of the compressor wheel and cover such as shown in FIG. 2 but illustrating a modified form of the construction.
  • FIG. 6 is a top plan view of a fragment of a modified form of the compressor wheel.
  • the turbine housing composed of a turbine housing 10 enclosing a conventional bladed turbine wheel (not shown) which drives the shaft 14.
  • the turbine housing is provided with a flanged inlet passage 18 which transmits engine exhaust gases to the turbine wheel.
  • the turbine component itself is of conventional construction. High pressure gases, entering the turbine, are expanded through the turbine wheel, causing the shaft 14 to rotate at high speed. The spent gases are discharged through the turbine outlet passage 19.
  • the casting 21 is nonsymmetrical in configuration and includes a central portion 24 and an outwardly flanged portion 27.
  • the central portion 24 of the casting 21 is provided with a central aperture 34 through which the shaft 14 extends. Within this aperture the portion 24 carries rotary and thrust bearings indicated generally at 36 which permit free rotation of the shaft.
  • a compressor cover casting indicated generally at 38.
  • Extending within, and integral with the cover casting 38 is a curved wall 39.
  • the wall has extending portions 39a which define the circular, common boundary 3% between two chambers 41 and 42.
  • Chamber 41 encircles the compressor wheel, to be subsequently described in detail, and forms a generally annular collector area whose outlet is formed at the tangentially extending outlet passage 43 (FIG. 2).
  • the chamber 42 forms a volutetype collector and diffuser passage.
  • An extending portion 39c of the wall 39 provides the narrow diffuser passage 43 extending generally radially from the tips of the compressor wheel vanes, to be subsequently described.
  • the volute chamber or passage 42 has its outlet at the tangentially extending outlet passage 44 (FIG. 2).
  • the extending, reduced diameter portion of the shaft 14 supports a centrifugal type compressor wheel indicated generally at 46 carrying a plurality of radially extending vanes.
  • the vanes each have a frontal portion 47 leading, or in front of, the adjoining vane portions 48.
  • the frontal portion 47 of each of the vanes has a radially extending portion 47a which extends radially beyond the adjoining vane portion 48 and, it will be noted, the circular common boundary between the chambers 41 and 42 is located adjacent the junction of the radially extending frontal portions 47a and the adjoining vane sections 48.
  • the frontal vane portions 47 are carried by a hub portion 51 supported on the shaft 14, the hub portion 51 being pressed against the adjacent hub member 52 which carries the adjoining vane portions 48.
  • the hub 51 and the hub portion 52 are held in place by the tightening down of the lock nut 53 on the threaded end of the shaft 14. It will be understood that the edges of the vane frontal portions 47 engage the edges of the adjoining vane portions 48 and, as may best be seen in FIG. 3, the bucket-forming curvature of the vanes extends continuously and smoothly across both the radially extending frontal vane portions 47 and the adjoining vane portions 48.
  • the rear face of the hub 51 and the trailing edges of the frontal vane portions 47 are slightly undercut, preferably in conical configuration as indicated by broken line 56, so that as the hub 51 is pressed against the hub portion 52 by tightening of the locknut 53, the frontal vane portions 4-7 apply a vibration damping force to the corresponding adjoining vane portions 48, the damping force being concentrated adjacent the outer marginal edges of the adjoining vanes 48.
  • broken line 56 illustrates the rear face of the hub 51 and the frontal vane portions 47 before the hub is tightened against the portion 52.
  • the high temperature high pressure air moving through the volute passage 42 exits through the outlet 44 and is conducted to the heat exchanger 61. Because of the heat exchange between the two discrete air flows, the temperature of the air from the chamber 42 is lowered before it is introduced into the intake manifold 62 of the internal combustion engine shown schematically at 63.
  • FIG. 5 a modified form of the turbocharger compressor component is illustrated.
  • the structure of FIG. 5 differs from that described above in that means are provided to extend the surface of wall 68, the counterpart of wall 39 of FIG. 1, within the chamber 41.
  • This means may take the form of integral fins 69 which aid in heat transfer across wall 68.
  • FIG. 6 discloses a modified form of vane design for the compressor wheel. 1n this design all of the bucketforming curvature extends across the radially extending frontal portion 71 of the vanes, the adjoining vane por-- tions '72 being uncurved. Since the uncurved adjoining vane portions 72 and the hub portion from which they extend are formed separately from the curved frontal vane portions '71, simpler casting and manufacturing methods may be used in producing this uncurved portion of the wheel.
  • the compressor wheel and cover or housing construction of the present invention permits heat exchange between the high temperature air and the lower temperature and pressure air to begin within the compressor housing itself. While in FIG. 4 an external heat exchanger is illustrated for completing the temperature reduction of the air charge for the engine, by use of means for extending the heat exchange surfaces within the compressor housing (by means of fins 69 of FIG. 5, for example) the size and capacity of the external heat exchanger may be reduced. Where air charge cooling requirements are relatively low, use of the structure of the present invention can eliminate the necessity of utilizing a separate, external heat exchanger.
  • Each of the adjoining vane portions 48 which provide the normal, single stage, centrifugal compressor wheel output, have exerted on them a vibration damping force applied to each vane primarily adjacent the circular wall edge 3%.
  • Both the high temperature, high pressure charge air and the cooler air to be used in heat exchange are supplied by a compact, single stage turbocharger compressor.
  • This permits packaging or mounting the turbocharger and heat exchanger in the engine structure itself and eliminates the necessity for locating the heat exchanger core at the engine radiator as is necessary where engine radiator fan air is used as the coolant for the charge air provided by the turbocharger.
  • the use of the turbocharger of the present invention in conjunction with a minimum size heat exchanger, as compared to location of a heat exchanger adjacent the engine radiator using the radiator fan air for cooling, is particularly advantageous for powered vehicles or machinery having extensive off-highway use. In such applications radiator fan air flow passages tend to become blocked by dust, leaves or other debris and the required cooling of the charge air cannot take place. Since in the arrangement shown in FIG. 5, clean air is supplied to both flow passages through the heat exchanger, there is no tendency for it to become obstructed.
  • a turbocharger compressor of the single stage centrifugal type having a compressor wheel rotated by a drive shaft and a cover enclosing said wheel and having an intake passage aligned with the shaft axis, said compressor wheel having radially extending vanes thereon for moving air axially through said intake passage and impelling it radially outwardly transverse to said shaft axis, said vanes each having a frontal portion extending radially beyond the adjoining vane portion, a wall within said cover defining two concentric discrete collector chambers surrounding said wheel, said wall extending to provide a circular common boundary be tween said two chambers closely adjacent the junction of said radially extending frontal portion and the said adjoining portion of said vanes, whereby said radially extending frontal portion of the vanes moves air into one of said chambers and the said adjoining portions of the vanes move air into the other of said chambers, said wall defining said collector chambers being provided with rib elements axially extending into said one of the chambers, said

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
US00202136A 1971-11-26 1971-11-26 Turbocharger compressor with dual collector chambers Expired - Lifetime US3829235A (en)

Priority Applications (16)

Application Number Priority Date Filing Date Title
BE791867D BE791867A (fr) 1971-11-26 Compresseur de turbocompresseur a double enceinte collectrice
US00202136A US3829235A (en) 1971-11-26 1971-11-26 Turbocharger compressor with dual collector chambers
CA157,002A CA981644A (en) 1971-11-26 1972-11-20 Turbocharger compressor with dual collector chambers
ZA728247A ZA728247B (en) 1971-11-26 1972-11-21 Turbocharger compressor with dual collector chambers
GB5403272A GB1401486A (en) 1971-11-26 1972-11-22 Centrifugal compressors especially for supercharging engines
SE7215394A SE389171B (sv) 1971-11-26 1972-11-24 Avgasdriven turbokompressor
FR7241885A FR2163075A5 (sv) 1971-11-26 1972-11-24
AR245304A AR197789A1 (es) 1971-11-26 1972-11-24 Compresor centrifugo monoetapico
AU49280/72A AU470945B2 (en) 1971-11-26 1972-11-24 Turbocharger compressor with dual collector chambers
NL7215972A NL7215972A (sv) 1971-11-26 1972-11-24
JP47117275A JPS4864507A (sv) 1971-11-26 1972-11-24
BR008275/72A BR7208275D0 (pt) 1971-11-26 1972-11-24 Compressor centrifugo de estagio unico
DE2257793A DE2257793A1 (de) 1971-11-26 1972-11-24 Verdichter zur aufladung einer brennkraftmaschine
ES409273A ES409273A1 (es) 1971-11-26 1972-11-25 Perfeccionamientos en los compresores centrifugos.
IT32134/72A IT971247B (it) 1971-11-26 1972-11-27 Turbocompressore di sovralimenta zione con doppie camere collettrici
JP1981103485U JPS6128077Y2 (sv) 1971-11-26 1981-07-14

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00202136A US3829235A (en) 1971-11-26 1971-11-26 Turbocharger compressor with dual collector chambers

Publications (1)

Publication Number Publication Date
US3829235A true US3829235A (en) 1974-08-13

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Family Applications (1)

Application Number Title Priority Date Filing Date
US00202136A Expired - Lifetime US3829235A (en) 1971-11-26 1971-11-26 Turbocharger compressor with dual collector chambers

Country Status (15)

Country Link
US (1) US3829235A (sv)
JP (2) JPS4864507A (sv)
AR (1) AR197789A1 (sv)
AU (1) AU470945B2 (sv)
BE (1) BE791867A (sv)
BR (1) BR7208275D0 (sv)
CA (1) CA981644A (sv)
DE (1) DE2257793A1 (sv)
ES (1) ES409273A1 (sv)
FR (1) FR2163075A5 (sv)
GB (1) GB1401486A (sv)
IT (1) IT971247B (sv)
NL (1) NL7215972A (sv)
SE (1) SE389171B (sv)
ZA (1) ZA728247B (sv)

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3953147A (en) * 1974-06-27 1976-04-27 General Motors Corporation Fluid dynamic machine
US4181466A (en) * 1977-03-17 1980-01-01 Wallace Murray Corp. Centrifugal compressor and cover
US4195473A (en) * 1977-09-26 1980-04-01 General Motors Corporation Gas turbine engine with stepped inlet compressor
US4885911A (en) * 1988-02-24 1989-12-12 Woollenweber William E Internal combustion engine turbosystem and method
US4918923A (en) * 1988-02-24 1990-04-24 Woollenweber William E Internal combustion engine turbosystem and method
US5105616A (en) * 1989-12-07 1992-04-21 Sundstrand Corporation Gas turbine with split flow radial compressor
US5215436A (en) * 1990-12-18 1993-06-01 Asea Brown Boveri Ltd. Inlet casing for steam turbine
US20020056374A1 (en) * 1998-12-16 2002-05-16 Keefer Bowie G. Gas separation with split stream centrifugal turbomachinery
US6398853B1 (en) 1998-12-16 2002-06-04 Quest Air Gases Inc. Gas separation with split stream centrifugal turbomachinery
US6526751B1 (en) 2001-12-17 2003-03-04 Caterpillar Inc Integrated turbocharger ejector intercooler with partial isothermal compression
US6557345B1 (en) 2001-12-17 2003-05-06 Caterpillar Inc Integrated turbocharger fan intercooler with partial isothermal compression
US6651431B1 (en) * 2002-08-28 2003-11-25 Ford Global Technologies, Llc Boosted internal combustion engines and air compressors used therein
US20040020477A1 (en) * 2002-08-01 2004-02-05 Vaught August Thomas Charge air conditioning system with integral intercooling
US20050196274A1 (en) * 2004-03-05 2005-09-08 Hans-Juergen Kraffzik Centrifugal pump
US20070256411A1 (en) * 2006-05-08 2007-11-08 Honeywell International, Inc. Exhaust gas particle collector
US20080138200A1 (en) * 2006-12-07 2008-06-12 Ryo Umeyama Centrifugal compressor
CN100404873C (zh) * 2005-07-07 2008-07-23 上海东方泵业(集团)有限公司 一种并列串联泵
US7469689B1 (en) 2004-09-09 2008-12-30 Jones Daniel W Fluid cooled supercharger
US20090314263A1 (en) * 2005-12-06 2009-12-24 Wabtec Holding Corp. Remote cooling system for charge-air cooled engines
US20100166539A1 (en) * 2007-04-20 2010-07-01 Seiichi Ibaraki Centrifugal compressor
US20110048003A1 (en) * 2009-09-03 2011-03-03 Hua Chen Integrated egr mixer and ported shroud housing compressor
US20120051885A1 (en) * 2009-05-11 2012-03-01 Francois Danguy Double exhaust centrifugal pump
US8142147B2 (en) 2001-02-26 2012-03-27 The Bergquist Torrington Company Centrifugal blower with partitioned scroll diffuser
CN102840169A (zh) * 2012-09-26 2012-12-26 北京理工大学 一种用于产生两种不同压比的离心压气机
CN103573705A (zh) * 2012-07-30 2014-02-12 哈米尔顿森德斯特兰德公司 座舱空气压缩机热壳体
US20140301827A1 (en) * 2013-04-09 2014-10-09 Abb Turbo Systems Ag Housing of a radial compressor
CN104308647A (zh) * 2014-10-11 2015-01-28 强胜精密机械(苏州)有限公司 气体驱动恒压泵切削液供给装置及切削液供给方法
US20150107249A1 (en) * 2013-10-22 2015-04-23 Access Energy Llc Extracting Heat From A Compressor System
US20160177806A1 (en) * 2014-12-23 2016-06-23 Caterpillar Inc. Exhaust Outlet Elbow Center Divider Connection
US20190107044A1 (en) * 2017-10-06 2019-04-11 Ford Global Technologies, Llc Methods and systems for a turbocharger
US10690136B2 (en) 2016-11-04 2020-06-23 Ford Global Technologies, Llc Supercharged internal combustion engine with compressor
US11136996B2 (en) * 2017-10-12 2021-10-05 Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. Compressor housing and turbocharger including the same
US11136997B2 (en) * 2019-07-23 2021-10-05 Ford Global Technologies, Llc Methods and systems for a compressor housing
US11274597B2 (en) 2019-06-11 2022-03-15 Perkins Engines Company Limited Two stage turbocharger with cooling arrangement
CN117716135A (zh) * 2022-05-06 2024-03-15 英格索兰工业美国公司 离心式加速稳定器

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DE2344023C2 (de) * 1973-08-31 1983-12-08 Wallace Murray Corp., 10171 New York, N.Y. Ladeluftkühlung einer abgasturbogeladenen Brennkraftmaschine
JPS57181999A (en) * 1981-05-01 1982-11-09 Mitsubishi Heavy Ind Ltd Turbo machine
DE19950425C2 (de) * 1999-10-14 2002-11-14 Johannes Dittmar Abgasturbolader mit Ladeluftkühlung
WO2007056780A1 (de) * 2005-11-15 2007-05-24 Avl List Gmbh Abgasturbolader für eine brennkraftmaschine
JP2013053524A (ja) * 2011-08-31 2013-03-21 Mitsubishi Heavy Ind Ltd 複圧式遠心ターボ機械
CN110552913A (zh) * 2018-05-31 2019-12-10 中国人民解放军陆军军事交通学院 具有冷却循环功能的电驱动式多级离心压气机装置
CN112901541A (zh) * 2019-11-19 2021-06-04 英业达科技有限公司 风扇模组
CN113374738B (zh) * 2021-06-24 2024-09-20 珠海格力电器股份有限公司 压缩机壳体、空气循环机壳体和空气循环机
CN113374734B (zh) * 2021-06-24 2024-09-27 珠海格力电器股份有限公司 一种膨胀机壳体、膨胀机和循环机
CN113374735B (zh) * 2021-06-24 2024-09-27 珠海格力电器股份有限公司 一种膨胀机壳体、膨胀机和循环机
CN114542514B (zh) * 2022-03-15 2024-07-09 势加透博（上海）能源科技有限公司 蜗壳组件
CN114526262B (zh) * 2022-03-15 2024-07-09 势加透博（上海）能源科技有限公司 蜗壳组件以及空压机

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GB761937A (en) * 1953-08-21 1956-11-21 Garrett Corp Improvements in or relating to a rotary fluid pressure converting device such as a turbine, compressor, pump or the like

Cited By (44)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3953147A (en) * 1974-06-27 1976-04-27 General Motors Corporation Fluid dynamic machine
US4181466A (en) * 1977-03-17 1980-01-01 Wallace Murray Corp. Centrifugal compressor and cover
US4195473A (en) * 1977-09-26 1980-04-01 General Motors Corporation Gas turbine engine with stepped inlet compressor
US4885911A (en) * 1988-02-24 1989-12-12 Woollenweber William E Internal combustion engine turbosystem and method
US4918923A (en) * 1988-02-24 1990-04-24 Woollenweber William E Internal combustion engine turbosystem and method
US5105616A (en) * 1989-12-07 1992-04-21 Sundstrand Corporation Gas turbine with split flow radial compressor
US5215436A (en) * 1990-12-18 1993-06-01 Asea Brown Boveri Ltd. Inlet casing for steam turbine
US20020056374A1 (en) * 1998-12-16 2002-05-16 Keefer Bowie G. Gas separation with split stream centrifugal turbomachinery
US6398853B1 (en) 1998-12-16 2002-06-04 Quest Air Gases Inc. Gas separation with split stream centrifugal turbomachinery
US8142147B2 (en) 2001-02-26 2012-03-27 The Bergquist Torrington Company Centrifugal blower with partitioned scroll diffuser
US6526751B1 (en) 2001-12-17 2003-03-04 Caterpillar Inc Integrated turbocharger ejector intercooler with partial isothermal compression
US6557345B1 (en) 2001-12-17 2003-05-06 Caterpillar Inc Integrated turbocharger fan intercooler with partial isothermal compression
US20040020477A1 (en) * 2002-08-01 2004-02-05 Vaught August Thomas Charge air conditioning system with integral intercooling
US6779515B2 (en) * 2002-08-01 2004-08-24 Ford Global Technologies, Llc Charge air conditioning system with integral intercooling
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BE791867A (fr) 1973-05-24
NL7215972A (sv) 1973-05-29
DE2257793A1 (de) 1973-05-30
AR197789A1 (es) 1974-05-10
BR7208275D0 (pt) 1973-08-21
JPS5736397U (sv) 1982-02-25
SE389171B (sv) 1976-10-25
FR2163075A5 (sv) 1973-07-20
ES409273A1 (es) 1975-10-01
AU4928072A (en) 1974-05-30
AU470945B2 (en) 1976-04-01
IT971247B (it) 1974-04-30
JPS4864507A (sv) 1973-09-06
ZA728247B (en) 1973-07-25
GB1401486A (en) 1975-07-16
CA981644A (en) 1976-01-13
JPS6128077Y2 (sv) 1986-08-20

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