US3795458A - Multistage compressor - Google Patents

Multistage compressor Download PDF

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Publication number
US3795458A
US3795458A US00218161A US3795458DA US3795458A US 3795458 A US3795458 A US 3795458A US 00218161 A US00218161 A US 00218161A US 3795458D A US3795458D A US 3795458DA US 3795458 A US3795458 A US 3795458A
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US
United States
Prior art keywords
flow
rotor
section
working fluid
multistage compressor
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
US00218161A
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English (en)
Inventor
R Strub
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.)
Brown Boveri Sulzer Turbomaschinen AG
Sulzer Escher Wyss AG
Original Assignee
Brown Boveri Sulzer Turbomaschinen AG
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 Brown Boveri Sulzer Turbomaschinen AG filed Critical Brown Boveri Sulzer Turbomaschinen AG
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Publication of US3795458A publication Critical patent/US3795458A/en
Assigned to SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND reassignment SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: BROWN BOVERI-SULZER TURBOMACHINERY LIMITED, JAKOB WYDLER, LIQUIDATOR
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
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/02—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal
    • F04D17/025—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps having non-centrifugal stages, e.g. centripetal comprising axial flow and radial flow stages
    • 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

Definitions

  • F0411 15/00, F04d 27/00, F04d 29/58 outwardly from the rotor, spread fanwise in a channel [58] Field of Search 415/177, 178, 179, 149 around and perpendicularly of the rotor, then flected towards the rotor and fed perpendicularly [56] References Cited through a channel to the compressor axis. in addition, UNITED STATES PATENTS a cooling element is disposed in one of the channels 2,396,484 3/1946 Allen et al.
  • multistage compressors have been known to have a rotor 'on which an axial-flow lowpressure section is disposed with stages for compressing a working fluid without cooling to a maximum permissible temperature.
  • the low-pressure section has been followed by a radial-flow (or diagonal-flow) highpressure section while a recooler has been disposed in the fluid flow path between the low-pressure section and high-pressure section.
  • Compressors, of this kind are known, for instance from Motortechnische Zeitschrift, 1967, Jrgang 13, Nr. 2, February 1952.
  • the invention provides a multistage compressor having a rotor, an axial-flow low-pressure section and a radial-flow high pressure section with a means for deflecting a working fluid leaving the low-pressure section first away from the rotor and then towards the rotor for entry perpendicularly into the radial-flow high pressure section as well as a cooling element for cooling the working fluid flowing into the high-pressure section.
  • the means for guiding the working fluid between the low-pressure and high-pressure sections includes a first deflector section, a first channel, a second deflector section and a second channel, in that order. The first deflector section deflects the working-fluid flow outwardly away from the rotor.
  • the first channel spreads the flow out fanwise around and perpendicularly to the compressor axis.
  • the second deflector section deflects the flow back towards the shaft and the second channel supplies the flow to the high-pressure section entry perpendicularly to the compressor axis.
  • At least one-of the two channels has at least one cooling element disposed therein.
  • the drawing illustrates a cross-sectional view of a multistage compressor according to the invention.
  • adjustable guide blades 15-21 which are adjustable around a radial axis are followed by at least one axial-flow stage having an adjustable exit guide blade 21 and a non-adjustable entry guide blade for the channel 29.
  • a deflector part 28 Disposed between the last set 21 of axial-flow rotor blades and the first radial-flow rotor 8 is a deflector part 28 which is connected to the casing l1 and in which the axial flow from the first section of the compressor is converted into an outwardly directed radial flow.
  • a channel 29 which is directed radially outwards and which acts as a diffusor and through which the fluid flows to go through a second deflector section 30 into a second channel 31.
  • the second channel 31 extends radially inwards. After further deflection, the flow enters the first radial flow rotor 8.
  • the inwardly directed channel 31 has cooling elements 32 which reduce the heat of compression acquired by the fluid in the axial-flow section of the compressor.
  • Thecooling-elements 32 together have a larger cooling area than do the elements 33, 34, since the axialflow section of the compressor compresses the fluid to the maximum permissible temperature, whereas in a radial-flow stage only the greatest pressure difference, with a reduced temperature rise occurs.
  • the diffusor type radial-flow channel 29 can have appropriate guide elements which can also be devised as cooling elements.
  • the invention thus provides a compressor which can be constructed of relatively short lengths. Because of this, the rotor bearings can be closely spaced with a resultant reduction of whirling. Also, a number of radialflow stages can be used as there is no axial reversal of the working fluid flow.
  • a multistage compressor comprising a casing
  • an axial-flow low-pressure section having a plurality of stages about said rotor for compressing a working fluid without cooling to a maximum permissible temperature
  • first deflector section for deflecting the working fluid perpendicularly outwardly away from said rotor, a first channel for thereafter spreading out the working fluid flow fanwise around and perpendicularly to said rotor, at second deflector section for deflecting the fluid perpendicular to said rotor towards said rotor and thereafter into said highpressure section;

Landscapes

  • 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)
US00218161A 1971-01-20 1972-01-17 Multistage compressor Expired - Lifetime US3795458A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH84471A CH533768A (de) 1971-01-20 1971-01-20 Mehrstufiger Verdichter

Publications (1)

Publication Number Publication Date
US3795458A true US3795458A (en) 1974-03-05

Family

ID=4196520

Family Applications (1)

Application Number Title Priority Date Filing Date
US00218161A Expired - Lifetime US3795458A (en) 1971-01-20 1972-01-17 Multistage compressor

Country Status (9)

Country Link
US (1) US3795458A (fr)
JP (1) JPS5636314B1 (fr)
CA (1) CA941807A (fr)
CH (1) CH533768A (fr)
DE (1) DE2103407B2 (fr)
FR (1) FR2122901A5 (fr)
GB (1) GB1373177A (fr)
IT (1) IT946642B (fr)
NL (1) NL149887B (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3892499A (en) * 1972-07-13 1975-07-01 Sulzer Ag Multistage turbocompressor having an intermediate cooler
US4362462A (en) * 1979-03-12 1982-12-07 M.A.N. Uternehmensbereich G.H.H. Sterkrade Method of intermediate cooling of compressed gases
DE3424925C1 (de) * 1984-05-16 1985-10-17 Sulzer-Escher Wyss GmbH, 7980 Ravensburg Turbomaschine mit wenigstens einem radial durchströmten Laufrad
US5042970A (en) * 1989-11-28 1991-08-27 Sundstrand Corporation Fast recharge compressor
US10012107B2 (en) 2011-05-11 2018-07-03 Dresser-Rand Company Compact compression system with integral heat exchangers
CN109751282A (zh) * 2019-02-02 2019-05-14 沈阳透平机械股份有限公司 一种轴向进气的轴流-离心式空气压缩机
US20220228593A1 (en) * 2019-08-07 2022-07-21 Carrier Corporation Axial and downstream compressor assembly

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6313110U (fr) * 1986-06-02 1988-01-28
JPS63137629U (fr) * 1987-03-02 1988-09-09
GB2312929B (en) * 1996-05-07 2000-08-23 Inst Francais Du Petrole Axial-flow and centrifugal pump system
GB0718846D0 (en) 2007-09-27 2007-11-07 Cummins Turbo Tech Ltd Compressor

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH215474A (de) * 1938-07-21 1941-06-30 Sulzer Ag Mehrstufige, achsial arbeitende Turbomaschine.
US2396484A (en) * 1944-07-24 1946-03-12 Allis Chalmers Mfg Co Intercooled compressing apparatus
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2619279A (en) * 1948-07-16 1952-11-25 Sulzer Ag Axial flow compressor
US2925954A (en) * 1956-03-29 1960-02-23 Escher Wyss Ag Compressor group with intercooler
US3303989A (en) * 1963-03-02 1967-02-14 Gutehoffnungshuette Sterkrade Axial-and radial-flow, multistage centrifugal compressor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH215474A (de) * 1938-07-21 1941-06-30 Sulzer Ag Mehrstufige, achsial arbeitende Turbomaschine.
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2396484A (en) * 1944-07-24 1946-03-12 Allis Chalmers Mfg Co Intercooled compressing apparatus
US2619279A (en) * 1948-07-16 1952-11-25 Sulzer Ag Axial flow compressor
US2925954A (en) * 1956-03-29 1960-02-23 Escher Wyss Ag Compressor group with intercooler
US3303989A (en) * 1963-03-02 1967-02-14 Gutehoffnungshuette Sterkrade Axial-and radial-flow, multistage centrifugal compressor

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3892499A (en) * 1972-07-13 1975-07-01 Sulzer Ag Multistage turbocompressor having an intermediate cooler
US4362462A (en) * 1979-03-12 1982-12-07 M.A.N. Uternehmensbereich G.H.H. Sterkrade Method of intermediate cooling of compressed gases
DE3424925C1 (de) * 1984-05-16 1985-10-17 Sulzer-Escher Wyss GmbH, 7980 Ravensburg Turbomaschine mit wenigstens einem radial durchströmten Laufrad
US5042970A (en) * 1989-11-28 1991-08-27 Sundstrand Corporation Fast recharge compressor
US10012107B2 (en) 2011-05-11 2018-07-03 Dresser-Rand Company Compact compression system with integral heat exchangers
CN109751282A (zh) * 2019-02-02 2019-05-14 沈阳透平机械股份有限公司 一种轴向进气的轴流-离心式空气压缩机
US20220228593A1 (en) * 2019-08-07 2022-07-21 Carrier Corporation Axial and downstream compressor assembly
US11965514B2 (en) * 2019-08-07 2024-04-23 Carrier Corporation Axial and downstream compressor assembly

Also Published As

Publication number Publication date
CH533768A (de) 1973-02-15
NL149887B (nl) 1976-06-15
JPS5636314B1 (fr) 1981-08-22
DE2103407B2 (de) 1975-10-30
DE2103407A1 (de) 1972-08-03
FR2122901A5 (fr) 1972-09-01
NL7102262A (fr) 1972-07-24
IT946642B (it) 1973-05-21
CA941807A (en) 1974-02-12
GB1373177A (en) 1974-11-06

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Legal Events

Date Code Title Description
AS Assignment

Owner name: SULZER-ESCHER WYSS AG, A CORP OF SWITZERLAND, SWIT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:BROWN BOVERI-SULZER TURBOMACHINERY LIMITED, JAKOB WYDLER, LIQUIDATOR;REEL/FRAME:005221/0890

Effective date: 19890530