[go: up one dir, main page]

US3892499A - Multistage turbocompressor having an intermediate cooler - Google Patents

Multistage turbocompressor having an intermediate cooler Download PDF

Info

Publication number
US3892499A
US3892499A US378428A US37842873A US3892499A US 3892499 A US3892499 A US 3892499A US 378428 A US378428 A US 378428A US 37842873 A US37842873 A US 37842873A US 3892499 A US3892499 A US 3892499A
Authority
US
United States
Prior art keywords
housing
compressor
duct
flow
cooler
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
US378428A
Other languages
English (en)
Inventor
Rene 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.)
Sulzer Escher Wyss AG
Sulzer AG
Original Assignee
Sulzer 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 Sulzer AG filed Critical Sulzer AG
Application granted granted Critical
Publication of US3892499A publication Critical patent/US3892499A/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

Links

Images

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
    • F04D29/58—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
    • 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

Definitions

  • multistage turbocompressors have been known to use an intermediate cooler between various compressors in order to cool a gaseous working medium, e.g. steam, flowing between the compressors.
  • a gaseous working medium e.g. steam
  • the gaseous working medium may cool to such an extent, either temporarily or for a relatively long time, as to allow the water vapor therein to begin to condense. Should this occur, the condensed water vapor would be delivered as water droplets to the blading channels of the turbocompressor and would cause damage through erosion and depositing of impurities contained in the gas flow.
  • Axial blading is particularly endangered because higher speeds of the working medium to be compressed are generated relative to the blade surfaces driving the medium than is the case with the blading of a radial compressor.
  • the invention provides a multistage turbocompressor comprised of a compressor housing and an intermediate cooler outside the housing with a casing duct between the housing and cooler and a central duct enclosed within the casing duct and between the cooler and housing.
  • the casing duct is connected to pass a flow of heated compressed gas from the housing, for example, from an initial compressor therein, to the cooler for cooling to suitable temperature for subsequent use.
  • the central duct is connected to pass the flow of cooled compressed gas back to the housing, for example, to a second compressor.
  • the heated gas heats the wall of the central duct.
  • the resultant heat in the wall of the central duct then heats any condensate in the countercurrent flow of cooled gas within the central duct to vaporize the condensate.
  • the return flow of gas becomes free of condensate.
  • Gas turbine equipment such as described in Swiss Pat. Nos. 2 l4,837 and 22 l ,377 have been known to use piping systems with a central duct disposed within a casing duct.
  • these piping systems have been used to conduct a high-temperature gas through the central duct.
  • a cooler gas has been conducted in the outer casing duct. ln this way, it has been possible to obtain thermal relief of the wall loaded by the high internal pressure, avoiding strength problems and leak-proofing difficulties.
  • the hot gas is conducted in the outer casing duct and the cool gas in the central duct.
  • the tube wall dividing the casing duct from the central duct can be maintained at a hightemperature by means of the flow of not-yet-cooled gas.
  • the flow of cool gas laden with drops of condensate is surrounded on all sides by a hightemperature wall.
  • the drops become 2 vaporized before reaching the blading of the compres' sor.
  • the compressor may have an axial stage upstream of the exit point to the cooler of the medium being compressed, and may have a radial stage following the reentry of the cooler medium.
  • the invention is of special importance for compressors with use axial stages following the re-entry of the cooled medium.
  • the function of the casing duct can be substantially facilitated by forming a bend in the casing duct as well as in the central duct since the drops of condensate will impact against the wall, and produce a greater surface area of contact. Thus revaporization can be accelerated.
  • the casing duct and central duct can advantageously be connected to the lower half of the housing where the housing is split in two halves. Also, it is possible to have two casing ducts disposed symmetrically of the perpendicular axial plane of the turborotor with each connected to the housing. Finally, a means may be disposed between the casing duct and the central duct to selectively introduce a variable amount of heated gas from the casing duct into the flow of cooled gas in the central duct in order to further promote the vaporization of the condensate drops.
  • FIG. 1 illustrates an axial cross-sectional view of a turbocompressor according to the invention
  • FIG. 2 illustrates a cross-sectional view taken on the plane llll of FIG. 1.
  • FIG. 3 illustrates an axial cross-sectional view of a further turbocompressor construction according to the invention made as a purely axial compressor
  • FIG. 4 illustrates a cross-sectional view through a compressor with separate intermediate coolers disposed at both sides according to the invention.
  • an axial-radial turbocompressor includes in a housing 1 in which a rotor 2 is mounted and which has an inlet A for receiving air or a gas.
  • the rotor 2 carries axial rotor rings 3 to 10 to compress air or a gas to a pressure at which the temperature rises to such an extent that intermediate cooling is necessary.
  • the rotor 2 also carries radial stages ll and 12 of a radial compressor to compress the gas further to a final pressure after cooling.
  • the housing I also has an outlet B at the end of the radial compressor for the exhaust of the compressed gas.
  • a casing duct 13 is connected to the housing 1 between the axial stages 3 to 10 and the radial stages 11, 12 (FIG. 1) and extends to a cooler 14 (FIG. 2) to conduct the flow of heated compressed gas to the cooler 14.
  • a central duct 15 is enclosed within the casing duct 13 and extends from the cooler 14 to the housing 1 to conduct the flow of cooled compressed gas back to the housing and to the radial stages ll, 12.
  • both ducts l3, 15 have a curved or bent position to deflect the respective flows of gas for purposes as described below.
  • the gas may be cooled in the intermediate cooler 14 to such an extent that the water contained in the gas before compression (or some other condens able inclusion) becomes condensed into drops.
  • These drops are carried along by the gas flowing back into the compressor, and would, without an introduction of heat, only revaporize during the compression in the radial stage 11, and deposit non-vaporized impurities on the blade surfaces. Non-vaporized residues might even arrive in stage 12.
  • erosion and premature wear of these parts may occur.
  • the wall of the central duct 15 is supplied with heat from the gas heated through compression in stages 3 to and flowing into the casing duct 13.
  • the drops of liquid carried along by the cooled gas receive so much heat that they revaporize and, as vapor, can no longer cause damage to the radial rotors 11 and 12.
  • the solid constituents are now dry, and are forced through the compressor without becoming deposited on the blades.
  • the vaporization of the drops of liquid in the central duct 15 can occur, in part, in the suspended state through the radiation of heat from the wall and also, in part, through contact with the duct wall. Because of the turbulence of the gas and the curved portions of the duct 15 some of the drops strike the heated duct wall and thereby become broken up. This gives the drops an enlarged surface area, thereby promoting more rapid vaporization. If there is a danger of a particularly great formation of liquid drops, then it is possible to install guide elements in the central duct to separate the drops out of the gas flow and conduct the drops against the wall. Such guide elements could also aid in the vaporization of the drops of condensate if heated to a suff' cient temperature by radiation from the duct walls.
  • an axial compressor having axial stages 16 to 21 follow the intermediate cooler (not shown).
  • Axial stages are more endangered by drops in the gaseous working medium being com pressed and by deposits than are radial stages, and in their flow, undergo greater deviations than radial compressors.
  • the most endangered parts are the blades of the introduction-stator 22 first reached by the intermediately cooled gas. These blades do not receive the flow of gas from the central duct 15 as uniformly as do the blades of the following rotors 16 to 21 and stators 23 to 28.
  • aa turbocompressor can be provided at each side of the housing 1 with an intermediate cooler 14.
  • the housing 1 is split into two halves. with the connection of each cooler 14 made in the lower housing half 29 by flanges 30. This facilitates access to the rotor 2 for maintenance and overhauling work.
  • a means 31-33 is also provided between the casing duct 13 and the central duct 15 in order to selectively introduce a small variable amount of not-yetcooled medium being compressed from the casing duct 13 into the central duct 15.
  • This means includes a pipe 31 connecting the casing duct 13 to the central duct 15, a series of outlets 32 in the pipe 31 to introduce the heated gas into the central duct 15 and a valve 33 for controlling the amount of flow through the pipe 31. This conducts so much heat to the cool gas in the central duct 15, which still contains drops, that any drops not reaching the wall and not sufficiently heat-irradiated by the wall become vaporized. An undesirable reheating of the cooled gas is not to be expected because the brought-in heat is used chiefly to vaporize the drops.
  • a multistage turbocompressor having a compressor housing including an inlet and an outlet and an intermediate cooler outside said housing;
  • a casing duct connected between said housing and said cooler downstream of said inlet for passing a flow of heated compressed gas from said housing to said cooler for cooling therein,
  • a central duct enclosed within said casing duct and connected between said cooler and said housing upstream of said outlet for passing the flow of cooled compressed gas from said cooler to said housing for passage out of said outlet.
  • a multistage turbocompressor comprising a housing including an inlet and an outlet;
  • a first compressor in said housing downstream of said inlet for heating and compressing a flow of gas to a first pressure
  • a second compressor in said housing downstream of said first compressor and upstream of said outlet for compressing the flow of gas to a higher pressure than said first pressure
  • a cooler outside said housing for cooling the flow of heated gas
  • a central duct enclosed within said casing duct and connected between said cooler and said housing for passing the flow of cooled gas from said cooler to said second compressor.
  • each duct has a bend therein for deflecting a respective flow of gas therein.
  • a multistage turbocompressor as set forth in claim 6 further comprising a means connected between said casing duct and said central duct for selectively introducing a variable amount of heated gas from said 6 casing duct into the flow of cooled gas in said central to said cooler, duct. a central duct concentric to said casing duct and conll.
  • a multistage turbocompressor comprising nected between said cooler and said housing for a compressor housing having an inlet and an outlet, passing the flow of cooled gas from said cooler to a first plurality of compressor stages in said housing 5 said housing downstream of said compressor adjacent and downstream of said inlet to receive stages.
  • a second plurality of compressor stages in said housa cooler outside said housing for cooling the flow of ing downstream of said first compressor stages and compressed gas, upstream of said outlet for compressing the flow of a casing duct connected between said housing and 10 gas from said cooler and central duct.
  • said cooler for passing the flow of compressed gas

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)
US378428A 1972-07-13 1973-07-12 Multistage turbocompressor having an intermediate cooler Expired - Lifetime US3892499A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1051772A CH553923A (de) 1972-07-13 1972-07-13 Mehrstufiger turboverdichter mit zwischenkuehlung des zu verdichtenden mittels.

Publications (1)

Publication Number Publication Date
US3892499A true US3892499A (en) 1975-07-01

Family

ID=4364058

Family Applications (1)

Application Number Title Priority Date Filing Date
US378428A Expired - Lifetime US3892499A (en) 1972-07-13 1973-07-12 Multistage turbocompressor having an intermediate cooler

Country Status (8)

Country Link
US (1) US3892499A (xx)
JP (1) JPS5217881B2 (xx)
CH (1) CH553923A (xx)
DE (1) DE2235125B2 (xx)
FR (1) FR2193427A5 (xx)
GB (1) GB1383453A (xx)
IT (1) IT991158B (xx)
NL (1) NL7210851A (xx)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3424925C1 (de) * 1984-05-16 1985-10-17 Sulzer-Escher Wyss GmbH, 7980 Ravensburg Turbomaschine mit wenigstens einem radial durchströmten Laufrad
US4592204A (en) * 1978-10-26 1986-06-03 Rice Ivan G Compression intercooled high cycle pressure ratio gas generator for combined cycles
US4936109A (en) * 1986-10-06 1990-06-26 Columbia Energy Storage, Inc. System and method for reducing gas compressor energy requirements
WO2000039441A1 (en) * 1998-12-24 2000-07-06 Alliedsignal Inc. Apparatus and method to increase turbine power
US20090087298A1 (en) * 2007-09-28 2009-04-02 Takanori Shibata Compressor and heat pump system
US20100189551A1 (en) * 2009-01-29 2010-07-29 General Electric Company Systems and Methods of Reducing Heat Loss from a Gas Turbine During Shutdown
US20100303605A1 (en) * 2009-05-27 2010-12-02 Dresser-Rand Company Removal of moisture from process gas
US20110129332A1 (en) * 2008-07-01 2011-06-02 Snecma Axial-centrifugal compressor having system for controlling play
US20120034067A1 (en) * 2009-04-28 2012-02-09 Concepts Eti, Inc. Turbocompressor and System for a Supercritical-Fluid Cycle
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
US4804885A (en) * 1982-02-04 1989-02-14 Tektronix, Inc. X-ray attenuating ceramic materials
JPH076518B2 (ja) * 1987-07-23 1995-01-30 三菱重工業株式会社 遠心圧縮機
GB2291130B (en) * 1994-07-12 1998-09-30 Rolls Royce Plc A gas turbine engine
DE19531562A1 (de) * 1995-08-28 1997-03-06 Abb Management Ag Verfahren zum Betrieb einer Kraftwerksanlage

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US2563745A (en) * 1942-03-06 1951-08-07 Lockheed Aircraft Corp Variable area nozzle for power plants
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
US3795458A (en) * 1971-01-20 1974-03-05 Bbc Sulzer Turbomaschinen Multistage compressor

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2540991A (en) * 1942-03-06 1951-02-06 Lockheed Aircraft Corp Gas reaction aircraft power plant
US2563745A (en) * 1942-03-06 1951-08-07 Lockheed Aircraft Corp Variable area nozzle for power plants
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
US3795458A (en) * 1971-01-20 1974-03-05 Bbc Sulzer Turbomaschinen Multistage compressor

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4592204A (en) * 1978-10-26 1986-06-03 Rice Ivan G Compression intercooled high cycle pressure ratio gas generator for combined cycles
DE3424925C1 (de) * 1984-05-16 1985-10-17 Sulzer-Escher Wyss GmbH, 7980 Ravensburg Turbomaschine mit wenigstens einem radial durchströmten Laufrad
US4936109A (en) * 1986-10-06 1990-06-26 Columbia Energy Storage, Inc. System and method for reducing gas compressor energy requirements
WO2000039441A1 (en) * 1998-12-24 2000-07-06 Alliedsignal Inc. Apparatus and method to increase turbine power
US6363706B1 (en) 1998-12-24 2002-04-02 Alliedsignal Apparatus and method to increase turbine power
US8192144B2 (en) * 2007-09-28 2012-06-05 Hitachi, Ltd. Compressor and heat pump system
US20090087298A1 (en) * 2007-09-28 2009-04-02 Takanori Shibata Compressor and heat pump system
US8764385B2 (en) * 2008-07-01 2014-07-01 Snecma Axial-centrifugal compressor having system for controlling play
US20110129332A1 (en) * 2008-07-01 2011-06-02 Snecma Axial-centrifugal compressor having system for controlling play
US20100189551A1 (en) * 2009-01-29 2010-07-29 General Electric Company Systems and Methods of Reducing Heat Loss from a Gas Turbine During Shutdown
US8210801B2 (en) * 2009-01-29 2012-07-03 General Electric Company Systems and methods of reducing heat loss from a gas turbine during shutdown
US9039349B2 (en) * 2009-04-28 2015-05-26 Concepts Eti, Inc. Turbocompressor and system for a supercritical-fluid cycle
US20120034067A1 (en) * 2009-04-28 2012-02-09 Concepts Eti, Inc. Turbocompressor and System for a Supercritical-Fluid Cycle
US8075245B2 (en) 2009-05-27 2011-12-13 Dresser-Rand Company Removal of moisture from process gas
WO2010138403A1 (en) * 2009-05-27 2010-12-02 Dresser-Rand Company Removal of moisture from process gas
US20100303605A1 (en) * 2009-05-27 2010-12-02 Dresser-Rand Company Removal of moisture from process gas
AU2010254296B2 (en) * 2009-05-27 2015-12-17 Dresser-Rand Company Removal of moisture from process gas
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
IT991158B (it) 1975-07-30
DE2235125C3 (xx) 1978-10-05
CH553923A (de) 1974-09-13
JPS5217881B2 (xx) 1977-05-18
GB1383453A (en) 1974-02-12
FR2193427A5 (xx) 1974-02-15
NL7210851A (xx) 1974-01-15
DE2235125B2 (de) 1974-07-04
JPS4958406A (xx) 1974-06-06
DE2235125A1 (de) 1974-02-07

Similar Documents

Publication Publication Date Title
US3892499A (en) Multistage turbocompressor having an intermediate cooler
US4507914A (en) Steam cooled gas generator
US2549819A (en) Axial flow compressor cooling system
US4550562A (en) Method of steam cooling a gas generator
US4178129A (en) Gas turbine engine cooling system
US3526092A (en) Gas turbine engine having improved bearing support means for concentric shafts
EP0379880A1 (en) A system and method for cooling in a gas turbine
GB2039352A (en) Process and apparatus for cooling natural gas
Church Steam turbines
EP0607232A1 (en) GAS TURBINE CYCLE.
Elliot Theory and tests of two-phase turbines
US7137784B2 (en) Thermally loaded component
US2724545A (en) Discharge casings for axial flow engines
GB2034822A (en) Gas turbine engine cooling air supply
US2748599A (en) Method and installation for operating a wind tunnel, more especially for high mach numbers
US5967743A (en) Blade carrier for a compressor
GB584580A (en) Improvements in or relating to turbine blades
US3933008A (en) Multistage heat exchanger
CN113454321B (zh) 在次级路径中包括热交换器的涡轮机
JPS60184992A (ja) 再生タ−ボマシン
US2543923A (en) Radial air compressor
JPS593120A (ja) ガス・タ−ビン
US1896809A (en) Multistage turbine
US3342406A (en) Method for preventing damage by corrosion of the adjustable mechanism of guide blading of turbomachines and turbomachine with corrosion prevention device
GB1284596A (en) Improvements in or relating to hydraulic seals

Legal Events

Date Code Title Description
STCF Information on status: patent grant

Free format text: PATENTED FILE - (OLD CASE ADDED FOR FILE TRACKING PURPOSES)

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