US3914842A - Steam turbine assembly process - Google Patents

Steam turbine assembly process Download PDF

Info

Publication number
US3914842A
US3914842A US324441A US32444173A US3914842A US 3914842 A US3914842 A US 3914842A US 324441 A US324441 A US 324441A US 32444173 A US32444173 A US 32444173A US 3914842 A US3914842 A US 3914842A
Authority
US
United States
Prior art keywords
turbine
parts
portions
section
casing
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
US324441A
Other languages
English (en)
Inventor
Gerd Bruckhoff
Rudolf Wickl
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Application granted granted Critical
Publication of US3914842A publication Critical patent/US3914842A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/912—Interchangeable parts to vary pumping capacity or size of pump
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining

Definitions

  • Fluid-powered turbines such as steam turbines
  • the steam pressures may range between 2 and 140 bar
  • the steam input temperatures may range between 200 and 540C.
  • the exhaust pressures may vary between 0.05 and 70 bar
  • turbine rotor speeds may vary between 3,000 to 25,000 rpm and develop power ranging from 1 to 50 MW.
  • the object of the present invention is to provide a method for manufacturing turbine casings which avoids the expense of custom-designed turbine casings while providing much if not all of their advantages, but at the same time avoiding the inflexibility of the so-called standard turbine casings.
  • This object is attained by the present invention through a method for making fluid turbine casings having lengthwise extending functionally differing portions such as the inlet and exhaust portions, and the intermediate portions therebetween which may include portions encasing either single or multiple turbine stages and which may be encased by casing portions of either the same or successively increasing diameters.
  • these portions have differing parameters of length and cross-sectional contour and size, in at least one or more instances, which differ for different types of turbines, by this invention these portions are made in the form of separate interfitting parts. These parts are cast separately and may be stocked by the turbine manufacturer in the form of an inventory. The parts for each portion are made with differing parameters as required for differing types of turbines.
  • a turbine or turbine casing manufacturer may select from the stocks of parts those required to form a turbine casing of a particular type such as may be indicated.
  • the parts may be interfltting in the sense that, for assembly, for any given inlet or front portion of the desired turbine casing, the portion which is to be joined with it as the next or intermediate or succeeding portion has a standardized contour, the next portion being interfitted and connected with this intermediate or succeeding portion and so on until the exhaust portion of the turbine is selected and applied to complete what might be called a stack of parts.
  • the interconnections of the parts selected may be by flanges which are bolted together, or welding, and in some cases two or more of the portions required may be produced as integral units or single castings.
  • the intermediate portion and the exhaust portion cast as one piece which will subsequently be connected, by welding or bolted flanges, to the inlet portion.
  • several intermediate portions may be cast together as a single unit and connected to the inlet portion as welding or the like.
  • the exhaust portion may be cast as a separate unit and connected to the balance of the construction through bolted flange connections.
  • the portions between the inlet and exhaust portions may comprise cylindrical intermediate portions and transition portions having differing front, and back, or inlet and outlet diameters. These portions may have mounting webs for the guide blade carriers.
  • FIG. 1 is an overall flow diagram showing the manner in which the various turbine portions are made and combined
  • FIG. 2 is a longitudinal section showing an example of the manner in which the portions are combined in the case of a back-pressure type of turbine;
  • FIG. 3 is a corresponding view showing the manner in which the portions are combined to produce a casing for a condensation type turbine
  • FIG. 4 in the same way shows the manner in which the portions are combined to produce the casing for a back-pressure type turbine.
  • FIG. 1 illustrates the various standardized casing portions comprising two front or inlet portions 50 and 51, seven exhaust portions 60 to 66, and eleven intermediate portions in the form of lengthening sections 80 to 85 which have fronts and backs of the same diameter, and diameter transition sections 70 to 74, each having a back diameter the same as the front diameter of the next to provide a casing of expanding diameter.
  • the portion 50 is shown as a low pressure inlet portion while the portion 51 is illustrated as a high pressure inlet portion, and with the other portions illustrated, permit making forty-one different turbine housings, for forty-one different types of turbines, which can be manufacturedby selection of the appropriate portions illustrated and fitting them together and interconnecting them as required for the type of turbine desired and as shown by this FIG. 1 flow diagram.
  • the need for running forty-one different casing designs through the pattern-making shop and the foundry shop have been replaced by the need for only twenty designs to go through these departments.
  • the turbine manufacturer having an inventory of parts as to each portion involving the different parts, the parts may be produced by methods approaching or equaling mass production methods.
  • FIG. 2 where the turbine consists only of the front or inlet portion 50, selected from the inventory of front or inlet portions 50 and 51, and the exhaust portion 60 appropriately selected from the inventory of exhaust portions 60 through 66, so that a turbine casing suitable for a turbine of Type 1 results, this Type 1 being indicated in FIG. 1 where the uniformly broken line leads from 50 through 60 to the numeral 1 representing this Type 1.
  • FIG. 2 there are also shown the turbine rotor shaft seals 1 10, 111 and 112 and also the nozzle housing block 113 as well as the guide blade carriers 114 and 115 held in a mounting web 120 in the front portion 50 and, a further mounting web 121, for the same purpose, in the exhaust portion 60.
  • FIG. 3 the casing required for a condensation type turbine is shown.
  • an intermediate lengthening portion 80 is inserted to provide an intermediate turbine stage and a condensation exhaust steam portion 64 is used so that a casing for a turbine type 26 results.
  • the selecting of the parts for this assembly is shown in FIG. 1 by the line.
  • the lengthening portion 80 By use of the lengthening portion 80, a greater number of rows of turbine blades is made possible and by the transition portion 73 also included, the larger diameter of the condensation exhaust steam portion 64 is accommodated. It can be seen that by the use of the transition portion 73 the front or inlet portion 50 shown by FIG.
  • the portion 80 and the portion 73 respectively provide mounting webs 121, 122 and 123 for the necessary guide blade carriers required for the type of turbine shown by this FIG. 3.
  • the various portions have been described as being manufactured as separate parts, it is advantageous in some instances to combine what may be called separate portions into one part.
  • the two portions 80 and 73 shown as being interfitted and welded together may advantageously be cast as a single part with the portion 80 joined to the front or inlet portion 50 by welding and with the back end of larger diameter of the transition portion 73 simply bolted to the condensation exhaust portion which is 64 in FIG. 3 via the surface 102.
  • the portion 80 whether or not the portions 80 and 83 are cast together as an integral piece, may be fitted to the portion 50 shown by FIG. 2 as well as FIG. 3.
  • FIG. 4 a back pressure turbine is shown with its necessary casing. This is particularly interesting since it shows the possibilities of the variations permitted by this new turbine casing making method.
  • FIG. 4 the casing is assembled from the portions which in FIG. 1 are connected by the line.
  • the high pressure front or inlet portion 51 is used together with the intermediate lengthening portion 70, the transition portion 71, the intermediate lengthening portion 81 and the back pressure exhaust portion 61.
  • a turbine casing is produced consisting of five different portions joined together at the various locations indicated at 100, 103, I04 and 105.
  • the intermediate portion it is possible and may be advisable for the intermediate portion to be cast together with the front or inlet portion 51 as a single casting, and the intermediate portion 71 and 81 maybe cast together as a single unit together with the exhaust portion 61, so that these two cast parts meet together and as units may be welded at the line 103.
  • the transition portion 71 and 72 and possibly others may be standardized as to length and diameter sizes in such a manner that they include guide blade carriers of one turbine type and as to the same turbine type, a turbine of the next larger size.
  • the front or inlet portion of one turbine type may be connected with the exhaust portion of a next larger tubine model of the same type to produce a new turbine size.
  • the rotative orientation of the exhaust portion may be varied as required to bring the exhaust line conduits out at various rotative angles.
  • the present invention contemplates a method for making fluid turbine casings having length-wise extending differing portions with parameters of length and crosssectional contour and size of one or more of these differing portions for different types of turbines.
  • the various portions of the turbine casing are made in the form of separate interfitting parts which for each portion comprise an inventory of parts, or groups of parts, with the parts of each group having the parameters described differing from those of each other as required for the parts of each group to form the corresponding portion of different types of turbines.
  • the manufacturer may select from the parts those required for the corresponding portions of the casing of the particular type of turbine which must be manufactured.
  • the parts are made so that they interfit and the manufacturer simply interfits and interconnects the selected parts to form the casing desired.
  • These parts include as many as is necessary of the front or inlet portions of the turbine casing, correspondingly as to the exhaust or outlet portions of the casings, and this being equally true as to the intermediate portions of the two kinds.
  • These intermediate portions include the lengthening or spacing portions which are typically cylindrical in contour as, for example, those shown at 80 in the drawings. Transition portions may be included wherein the front of the portion fits the back of the preceding portion, with the back of this portion being enlarged to fit a succeeding portion of larger diameter such as is shown in the case of parts 71 and 73 in FIGS. 4 and 3 of the drawings.
  • a turbine housing for use with steam which is comprised of a plurality of axially adjoining sections, said sections including an inlet section, an exhaust section and at least one intermediate and transition section, the
  • said housing is formed based on the basic turbine design required as reflected by the input and output performance requirements and turbine speed by selecting said inlet section, said exhaust section and at least one intermediate and transition section from corresponding groupings of each, said groupings of each having a plurality of pieces varying one from the other in at least one of the parameters of length, cross-sectional contour, cross-sectional size at input and/or output of each section and material of construction and mechanically joining said inlet section, said intermediate section, and transition section and said outlet section together to thereby form said housing.
  • sections cast as one piece include at least two of said intermediate sections and where said cast intermediate sections are welded to said inlet section and bolted to said outlet section.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
US324441A 1972-04-21 1973-01-17 Steam turbine assembly process Expired - Lifetime US3914842A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE2219661A DE2219661A1 (de) 1972-04-21 1972-04-21 Verfahren zur herstellung von gehaeusen fuer dampfturbinen

Publications (1)

Publication Number Publication Date
US3914842A true US3914842A (en) 1975-10-28

Family

ID=5842876

Family Applications (1)

Application Number Title Priority Date Filing Date
US324441A Expired - Lifetime US3914842A (en) 1972-04-21 1973-01-17 Steam turbine assembly process

Country Status (9)

Country Link
US (1) US3914842A (sh)
JP (1) JPS5347843B2 (sh)
CA (1) CA1004985A (sh)
CH (1) CH556969A (sh)
DE (1) DE2219661A1 (sh)
FR (1) FR2181283A5 (sh)
GB (1) GB1411269A (sh)
IT (1) IT973125B (sh)
NL (1) NL7305581A (sh)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4189813A (en) * 1976-06-04 1980-02-26 Aeg-Kanis Turbinenfabrik Gmbh Method for manufacturing single stage geared turbines
US4789301A (en) * 1986-03-27 1988-12-06 Goulds Pumps, Incorporated Low specific speed pump casing construction
EP1033478A3 (de) * 1999-03-02 2002-04-17 Alstom Gehäuse für eine thermische Turbomaschine
EP1314859A1 (en) * 2001-11-22 2003-05-28 Siemens Aktiengesellschaft Method for manufacturing steam turbines
US6691519B2 (en) * 2000-02-18 2004-02-17 Siemens Westinghouse Power Corporation Adaptable modular gas turbine power plant
US20110070064A1 (en) * 2009-09-22 2011-03-24 Glynn Brian K System and Method for Accommodating Changing Resource Conditions for a Steam Turbine
EP2549066A1 (en) * 2011-07-19 2013-01-23 Alstom Technology Ltd Turbine casing and method of manufacturing thereof
US20150337685A1 (en) * 2014-05-26 2015-11-26 Alstom Technology Ltd Method and device for mounting and removing a turbine component
US10606245B2 (en) 2017-11-27 2020-03-31 International Business Machines Corporation Parts matching for improved manufacturing assembly

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5267407A (en) * 1975-12-01 1977-06-03 Toshiba Corp Turbine casing
US6030176A (en) * 1995-07-19 2000-02-29 Siemens Aktiengesellschaft Structural member for an exhaust-gas connection of a turbomachine, in particular a steam turbine, and set of at least two structural members
DE19615011A1 (de) * 1995-07-19 1997-01-23 Siemens Ag Bauteil für einen Abgasstutzen einer Strömungsmaschine, insbesondere einer Dampfturbine

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1517234A (en) * 1923-07-24 1924-11-25 Gen Electric Elastic-fluid turbine
US2971334A (en) * 1955-01-04 1961-02-14 Solar Aircraft Co Gas turbine engine adaptable for multi-purpose use
US3188967A (en) * 1961-05-26 1965-06-15 Solar Aircraft Co Fluid pressure booster

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1517234A (en) * 1923-07-24 1924-11-25 Gen Electric Elastic-fluid turbine
US2971334A (en) * 1955-01-04 1961-02-14 Solar Aircraft Co Gas turbine engine adaptable for multi-purpose use
US3188967A (en) * 1961-05-26 1965-06-15 Solar Aircraft Co Fluid pressure booster

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4189813A (en) * 1976-06-04 1980-02-26 Aeg-Kanis Turbinenfabrik Gmbh Method for manufacturing single stage geared turbines
US4789301A (en) * 1986-03-27 1988-12-06 Goulds Pumps, Incorporated Low specific speed pump casing construction
EP1033478A3 (de) * 1999-03-02 2002-04-17 Alstom Gehäuse für eine thermische Turbomaschine
US6691519B2 (en) * 2000-02-18 2004-02-17 Siemens Westinghouse Power Corporation Adaptable modular gas turbine power plant
EP1314859A1 (en) * 2001-11-22 2003-05-28 Siemens Aktiengesellschaft Method for manufacturing steam turbines
US20050039333A1 (en) * 2001-11-22 2005-02-24 Michael Wechsung Method for manufacturing steam turbines
CN100347414C (zh) * 2001-11-22 2007-11-07 西门子公司 用于制造蒸汽轮机的方法
US8313292B2 (en) * 2009-09-22 2012-11-20 Siemens Energy, Inc. System and method for accommodating changing resource conditions for a steam turbine
US20110070064A1 (en) * 2009-09-22 2011-03-24 Glynn Brian K System and Method for Accommodating Changing Resource Conditions for a Steam Turbine
EP2549066A1 (en) * 2011-07-19 2013-01-23 Alstom Technology Ltd Turbine casing and method of manufacturing thereof
CN102889100A (zh) * 2011-07-19 2013-01-23 阿尔斯通技术有限公司 涡轮外壳及其制造方法
US20130064651A1 (en) * 2011-07-19 2013-03-14 Alstom Technology Ltd Turbine casing and method of manufacturing thereof
CN102889100B (zh) * 2011-07-19 2015-06-17 阿尔斯通技术有限公司 涡轮外壳及其制造方法
RU2556727C2 (ru) * 2011-07-19 2015-07-20 Альстом Текнолоджи Лтд Способ изготовления кожуха турбинной установки, литейная форма для изготовления и кожух турбинной установки
US10001031B2 (en) * 2011-07-19 2018-06-19 General Electric Technology Gmbh Turbine casing and method of manufacturing thereof
US20150337685A1 (en) * 2014-05-26 2015-11-26 Alstom Technology Ltd Method and device for mounting and removing a turbine component
US10606245B2 (en) 2017-11-27 2020-03-31 International Business Machines Corporation Parts matching for improved manufacturing assembly

Also Published As

Publication number Publication date
CH556969A (de) 1974-12-13
NL7305581A (sh) 1973-10-23
JPS4920505A (sh) 1974-02-23
GB1411269A (en) 1975-10-22
CA1004985A (en) 1977-02-08
IT973125B (it) 1974-06-10
FR2181283A5 (sh) 1973-11-30
JPS5347843B2 (sh) 1978-12-23
DE2219661A1 (de) 1973-10-31

Similar Documents

Publication Publication Date Title
US3914842A (en) Steam turbine assembly process
CN1325761C (zh) 用于流体机械的动叶片以及流体机械
US5295789A (en) Turbomachine flow-straightener blade
US3745629A (en) Method of determining optimal shapes for stator blades
EP0735239B1 (en) Gas turbine system and method of manufacturing
US6174133B1 (en) Coolable airfoil
US4948333A (en) Axial-flow turbine with a radial/axial first stage
EP0353498A2 (en) Compressor diaphragm assembly
DE1130646B (de) Diagonalgasturbinen-Energieanlage
GB1272200A (en) Axial-flow turbomachine rotors
EP3284907B1 (en) Multi-wall blade with cooled platform
US3339833A (en) Axial fluid flow machine such as a compressor or turbine
US2809493A (en) Centrifugal flow compressor and gas turbine power plant with a centrifugal flow compressor, toroidal combustion chamber, and centripetal flow turbine
DE10016068C2 (de) Dampfturbine
EP3034196B1 (en) Reinforced ceramic core for component casting
US10975722B2 (en) Outlet guide vane for an aircraft turbomachine, comprising a lubricant cooling passage equipped with flow disturbing studs with simplified manufacturing
DE102019104814B4 (de) Mit einem Einsatzträger ausgestattete Turbinenschaufel
US3869220A (en) Rotary machines
US6851927B2 (en) Fluid-flow machine with high-pressure and low-pressure regions
US3496628A (en) Method of joining thin-walled members,particularly in casings for gas turbine engines
US6406252B2 (en) Steam turbine having an exhaust-steam casing
EP3808473B1 (en) Casting core assembly comprising a bumper surrounding a metal pin and associated method of manufacture.
EP1840337A1 (de) Nut-Feder-Verbindung zwischen zwei Turbinenkomponenten einer Turbine
US3867059A (en) Reversible multi-stage hydraulic machine
US6270315B1 (en) Highly loaded turbine blading