US2619318A - Turbomachine rotor - Google Patents

Turbomachine rotor Download PDF

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Publication number
US2619318A
US2619318A US753230A US75323047A US2619318A US 2619318 A US2619318 A US 2619318A US 753230 A US753230 A US 753230A US 75323047 A US75323047 A US 75323047A US 2619318 A US2619318 A US 2619318A
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US
United States
Prior art keywords
blades
blade
grooves
rotor
root
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
US753230A
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English (en)
Inventor
Schaer Franz
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 AG
Original Assignee
Sulzer AG
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Filing date
Publication date
Application filed by Sulzer AG filed Critical Sulzer AG
Application granted granted Critical
Publication of US2619318A publication Critical patent/US2619318A/en
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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical

Definitions

  • the present invention relates to an axial flow turbomachine such as a compressor, blower, or turbine, and more particularly to a rotor and the blading of such a machine.
  • An object of the invention is the provision of a turbomachine in which the runner and/ or guide blades are mounted serially in helical grooves on the peripheral surface of a suitable cylindrical or conic body.
  • a blade of one blade row is mounted in the same groove as a blade of another blade row.
  • the blades are arranged in groups constituting stages of the turbomachine and the blades of each group are arranged in a plane which is at a right angle to the longitudinal axis of the cylindrical body, the latter forming with the blades thereon the rotor of the turbomachine.
  • the blades of difierent groups or rows are spaced or separated by spacer members inserted in the grooves between the blades of different rows.
  • Another object of the invention resides in the provision of a method of producing the blades as well as blade spacer members as needed for a construction as specified in the paragraph next above.
  • This method is characterized by the fact that a plurality of blades or spacer members are cut from helical portions left, of a rotund body after a plurality of helical grooves have been milled into the surface of said body.
  • the angle of inclination of the helices employed in the aforesaid machine and manufacturing method is preferably substantially like the angle enclosed by the chord of the base section of a blade and a plane which is at right angle to the axis of the machine in which the blades are used.
  • the roots of at least a portion of the blades extend longitudinally substantially parallel to said chord and the thickness of the neck interconnecting the root and the blade proper is about equal to the greatest height of the section of the blade proper at its base.
  • the blades are machined from a tubular or conic and hollow body the wall thickness of which is at least equal to the height of the blade root plus that of the blade proper.
  • the outside diameter of said body corresponds to the outside diameter of the blade rows fitted on the rotor.
  • the spacer members or blocks are made similarly from a round hollow body Whose wall thickness is at least equal to the height of the blocks and whose outside diameter corresponds substantially to that of the blade drum 1. e. the aforesaid cylindrical body, on which the spacers are used.
  • the walls of the grooves on the body for holding the blades follow helical or screw lines and the foot portions of the blades fit snugly into the grooves, the walls of the grooves, as well as the surfaces of the foot portions, are curved in three directions in contradistinction to conven- 2 tional designs in which such walls and surface are either straight or curved in two direction only.
  • Fig. l is a side view of a turbine rotor according to the invention with a number of blades removed and showing one blade in section;
  • Fig. 2 is an end view of the rotor shown in Fig. 1 with an end cover and a number of turbine blades removed;
  • Fig. 3 is a transverse sectional view of a turbomachine blade according to the invention, the section being taken adjacent to the neck of the blade, the neck being the portion between the root and the blade proper.
  • Fig. 4 is a perspective view of a blank with a plurality of spiral grooves milled thereinto for producing blanks of turbomachine blades according to the invention
  • Fig. 5 is a perspective view of an individual blade blank according to the invention.
  • Fig. 6 is a perspective view of a finished blade according to the invention, with the outline of the blank from which it was made in dash and dot lines;
  • Fig. '7 is a perspective view of a finished spacer member according to the invention with the web portion with which it was connected to the body from which it was made indicated in dash and dot lines.
  • the rotor of the machine accordin to the invention is provided with helical or screw-shaped grooves l into which the roots of the blades 2 forming blade groups or rows 3 are inserted.
  • grooves l there are as many grooves as there are blades in a row and all rows have the same number of blades. Neighboring blades in the same groove are separated by spacer members 4 which determine at the same time the distance between two blade rows.
  • the ends of the grooves are closed by annular members 5 connected to the faces of the rotor drum.
  • the pitch angle a of the helical grooves is about equal to the angle s between the chord B of the section at the base of the blade and a plane 8 which is positioned at a right angle to the rotor axis 1, as is illustrated in Figs. 1 and 3.
  • This makes it possible to place the blade roots of at least some of the blades substantially parallel to the chord of the section of the blades at their bases whereby the width or thickness b of the root is not much greater than the greatest height h of said base section.
  • a blade root of this type can be made very light without sacrificing strength of its connection with the blade proper.
  • the neck which connects the root with the blade proper is subjected primarily to tensile stresses.
  • the sections transverse to the longitudinal axis at the outer'parts of the blade are twisted relatively to the section at the base of the blade.
  • Fig. 4 illustrates a blank 9 having a central bore from which blades according to the invention are machined according to the process forming part of my invention.
  • the outside diameterof the tubular body 9 is slightly larger than the outer diameter of a'blade row in which the finished blades will be used.
  • Helical or screwshaped grooves l l are milled into the outer surface of body 9.
  • the configuration of the milling cutters and of the produced grooves is such that the-remaining helical or screw-shaped portions 12 have the final shape of the neck 20 and of the root 2
  • the remaining helical portions are then divided by cutting the body in planes I4 which are at 'a'right angle with respect to the axis 13 of the body. By cutting through the bridge portions [5, the blade blanks are separated from their supporting drum [6. The so produced blanks must then be machined down to the desired final blade configuration.
  • Fig.5 shows a blade blank as separated from the drum- I 6.
  • the rest of the bridge portion 15 is removed for obtaining the final configuration of blade root 2l.
  • This root can now be used for clamping the rough blade into the milli-ngmachine for forming the final shape of theblade proper. This is preferably done on a copying milling machine where the portions shown in dash-dot lines in Fig. 6 are removed. What remains is the finished blade comprising the blade proper l8, the neck and the foot or root 2!.
  • the spacer members are made similarly as the blades, from a tubular body.
  • the spacer member has, like the blade, a neck-23 and a root 24 from which, after separation of the spacer member from its drum, the bridge or web portion [5 only must be removed.
  • the guide blades which are inserted into the interior of the housing may be made in a similar manner'as the rotor blades. They are cut out of the interior of a tubular body instead of the exterior and are inserted in spiral grooves in the inner surface of the casing of the turbomachine. This way of mounting the blades and spacer members produces a very strong connection because the roots of the blades extend along the chord of the sections of the blades at their bases.
  • the guide blades as well as the moving blades according to the present invention are light and yet very strong because the connection between the blade proper and its root amounts to a full section of the blade at its base and there is an almost straightfiow of the stresses.
  • the blade support is weakened by only very small grooves leaving substantial portions of supporting material therebetween.
  • the blade roots, .as well as the grooves into which they are fitted, are formed along cylindrical helical lines .;of constant pitch. If the lengths of the blades of different stages of the turbomachine differs considerably, the hollow body from which they are made may have the form of a cone. The body from which rotor blades are made need not be hollow but could be solid.
  • a rotor for an axial flow turbomachine comprising a cylindrical, one piece blade holder bodyhaving a cylindrical surface portion, a'plurality of continuous, parallel, and circumferentially spaced grooves in said surface portion; said grooves having walls following screw lines of constant pitch in said surface portion, and a plurality of blades individually having root portions having surfaces curved to conform with the screw lines followed by the walls of said grooves, a plurality of said blades being serially fitted with their root portions into each of said continuous grooves, the pitch of said groove being substantially the same as that defined for said blades by the flow conditions of the medium flowing through the turbomachine.
  • a rotor for an axial flow turbomachine comprising a cylindrical, one-piece blade holder body having a cylindrical surface portion, a plurality of continuous, parallel, and spaced grooves in said surface portion, said grooves having walls following screwlines of constant pitch in said surface portion, and a plurality of blades individually having root portions having surfaces conforming with portions of the Walls of said grooves, a plurality of said blades being serially fitted with their root portions into each of said continuous grooves, said blades being arranged in parallel rows on the cylindrical surface of the rotor, each row being placed in a plane extending at a right angle to the rotation axis of the rotor, and the blades of one row being individually fitted into different continuous grooves.
  • a rotor as defined in claim 2 comprising spacer members conforming with the root portions of said blades and being serially fitted into said grooves alternately with the blades in the grooves for axially spacing said blade rows.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US753230A 1946-06-07 1947-06-07 Turbomachine rotor Expired - Lifetime US2619318A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH626181X 1946-06-07

Publications (1)

Publication Number Publication Date
US2619318A true US2619318A (en) 1952-11-25

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ID=4524406

Family Applications (1)

Application Number Title Priority Date Filing Date
US753230A Expired - Lifetime US2619318A (en) 1946-06-07 1947-06-07 Turbomachine rotor

Country Status (7)

Country Link
US (1) US2619318A (es)
BE (1) BE473515A (es)
CH (1) CH251495A (es)
DE (1) DE838191C (es)
FR (1) FR946406A (es)
GB (1) GB626181A (es)
NL (1) NL65041C (es)

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931625A (en) * 1956-12-17 1960-04-05 Gen Electric Compressor rotor
US3112914A (en) * 1960-08-01 1963-12-03 Gen Motors Corp Turbine rotor
US3692429A (en) * 1971-02-01 1972-09-19 Westinghouse Electric Corp Rotor structure and method of broaching the same
US4016636A (en) * 1974-07-23 1977-04-12 United Technologies Corporation Compressor construction
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
US4483658A (en) * 1979-12-11 1984-11-20 Levine Elliott M Rotational wake reaction steps for Foils
US4483659A (en) * 1983-09-29 1984-11-20 Armstrong Richard J Axial flow impeller
EP0274978A1 (en) * 1986-12-29 1988-07-20 United Technologies Corporation Multiple lug blade to disk attachment
US4852235A (en) * 1988-08-19 1989-08-01 Trease Dwaine A Bearing puller
US4887940A (en) * 1987-07-23 1989-12-19 Hitachi, Ltd. Multistage fluid machine
US5067876A (en) * 1990-03-29 1991-11-26 General Electric Company Gas turbine bladed disk
US5073087A (en) * 1990-04-13 1991-12-17 Westinghouse Electric Corp. Generator blower rotor structure
US5174720A (en) * 1990-12-14 1992-12-29 Ottomar Gradl Arrangement for attaching blades on the wheel of a rotor
US5310318A (en) * 1993-07-21 1994-05-10 General Electric Company Asymmetric axial dovetail and rotor disk
US5328326A (en) * 1991-04-19 1994-07-12 Gec Alsthom Sa Impulse turbine with a drum rotor, and improvements to such turbines
US5961286A (en) * 1996-12-27 1999-10-05 Asea Brown Boveri Ag Arrangement which consists of a number of fixing slots and is intended for fitting a rotor or a stator of a fluid-flow machine with blades
GB2412948A (en) * 2004-04-08 2005-10-12 Alfred Learmonth Wind or water-driven generator
WO2007097659A1 (fr) * 2006-02-20 2007-08-30 Kapachinskikh Dmitry Anatoliev Vis et turbine
EP2441921A1 (en) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Turbomachine rotor blade roots with adjusting protrusions
DE102012016202A1 (de) * 2012-08-16 2014-02-20 Christian Siglbauer Kraftmaschine zur Umwandlung kinetischer Energie eines strömenden Mediums in Rotationsenergie eines Laufrades
US20140322026A1 (en) * 2012-04-19 2014-10-30 Snecma Cone of entry of blower of turboshaft engine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CZ406592A3 (en) * 1992-01-08 1993-08-11 Alsthom Gec Drum rotor for steam action turbine and steam action turbine comprising such rotor
FR2686650B1 (fr) * 1992-01-29 1994-03-18 Gec Alsthom Sa Rotor tambour pour turbine a vapeur a action avec montage des ailettes dans des rainures longitudinales et turbine a vapeur a action comportant un tel rotor.
FR2903138B1 (fr) * 2006-06-28 2017-10-06 Snecma Aube mobile et disque de rotor de turbomachine, et dispositif d'attache d'une telle aube sur un tel disque
CN107420132A (zh) * 2017-06-15 2017-12-01 翁志远 多级螺旋结构的转子、汽轮机和汽轮机设备
CN111644814B (zh) * 2020-06-03 2021-10-08 大连华锐重工铸业有限公司 风电转子加工方法

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE123965C (es) *
US138953A (en) * 1873-05-13 Improvement in soap-crutching machines
US512751A (en) * 1894-01-16 Mikle schmaltz
US1073413A (en) * 1910-09-30 1913-09-16 Hermann Faehrmann Propeller.
US1793468A (en) * 1929-05-28 1931-02-24 Westinghouse Electric & Mfg Co Turbine blade
US1967962A (en) * 1933-09-09 1934-07-24 John F Metten Steam turbine rotor
US2240742A (en) * 1937-11-26 1941-05-06 Allis Chalmers Mfg Co Turbine blade attachment and method and apparatus therefor
US2313413A (en) * 1940-07-02 1943-03-09 John R Weske Axial flow fan
US2415847A (en) * 1943-05-08 1947-02-18 Westinghouse Electric Corp Compressor apparatus
US2422193A (en) * 1944-06-12 1947-06-17 Westinghouse Electric Corp Method of making cast turbine blading
US2436246A (en) * 1944-10-21 1948-02-17 Earl W Braga Air-cooled explosion turbine
US2461402A (en) * 1944-10-06 1949-02-08 Power Jets Res & Dev Ltd Rotor for multistage axial flow compressors and turbines

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE123965C (es) *
US138953A (en) * 1873-05-13 Improvement in soap-crutching machines
US512751A (en) * 1894-01-16 Mikle schmaltz
US1073413A (en) * 1910-09-30 1913-09-16 Hermann Faehrmann Propeller.
US1793468A (en) * 1929-05-28 1931-02-24 Westinghouse Electric & Mfg Co Turbine blade
US1967962A (en) * 1933-09-09 1934-07-24 John F Metten Steam turbine rotor
US2240742A (en) * 1937-11-26 1941-05-06 Allis Chalmers Mfg Co Turbine blade attachment and method and apparatus therefor
US2313413A (en) * 1940-07-02 1943-03-09 John R Weske Axial flow fan
US2415847A (en) * 1943-05-08 1947-02-18 Westinghouse Electric Corp Compressor apparatus
US2422193A (en) * 1944-06-12 1947-06-17 Westinghouse Electric Corp Method of making cast turbine blading
US2461402A (en) * 1944-10-06 1949-02-08 Power Jets Res & Dev Ltd Rotor for multistage axial flow compressors and turbines
US2436246A (en) * 1944-10-21 1948-02-17 Earl W Braga Air-cooled explosion turbine

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931625A (en) * 1956-12-17 1960-04-05 Gen Electric Compressor rotor
US3112914A (en) * 1960-08-01 1963-12-03 Gen Motors Corp Turbine rotor
US3692429A (en) * 1971-02-01 1972-09-19 Westinghouse Electric Corp Rotor structure and method of broaching the same
US4016636A (en) * 1974-07-23 1977-04-12 United Technologies Corporation Compressor construction
US4483658A (en) * 1979-12-11 1984-11-20 Levine Elliott M Rotational wake reaction steps for Foils
US4483054A (en) * 1982-11-12 1984-11-20 United Technologies Corporation Method for making a drum rotor
US4483659A (en) * 1983-09-29 1984-11-20 Armstrong Richard J Axial flow impeller
EP0274978A1 (en) * 1986-12-29 1988-07-20 United Technologies Corporation Multiple lug blade to disk attachment
US4767274A (en) * 1986-12-29 1988-08-30 United Technologies Corporation Multiple lug blade to disk attachment
US4887940A (en) * 1987-07-23 1989-12-19 Hitachi, Ltd. Multistage fluid machine
US4852235A (en) * 1988-08-19 1989-08-01 Trease Dwaine A Bearing puller
US5067876A (en) * 1990-03-29 1991-11-26 General Electric Company Gas turbine bladed disk
US5073087A (en) * 1990-04-13 1991-12-17 Westinghouse Electric Corp. Generator blower rotor structure
US5174720A (en) * 1990-12-14 1992-12-29 Ottomar Gradl Arrangement for attaching blades on the wheel of a rotor
US5328326A (en) * 1991-04-19 1994-07-12 Gec Alsthom Sa Impulse turbine with a drum rotor, and improvements to such turbines
US5310318A (en) * 1993-07-21 1994-05-10 General Electric Company Asymmetric axial dovetail and rotor disk
US5961286A (en) * 1996-12-27 1999-10-05 Asea Brown Boveri Ag Arrangement which consists of a number of fixing slots and is intended for fitting a rotor or a stator of a fluid-flow machine with blades
GB2412948A (en) * 2004-04-08 2005-10-12 Alfred Learmonth Wind or water-driven generator
GB2412948B (en) * 2004-04-08 2007-02-28 Alfred Learmonth Wind or water motor
WO2007097659A1 (fr) * 2006-02-20 2007-08-30 Kapachinskikh Dmitry Anatoliev Vis et turbine
EP2441921A1 (en) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Turbomachine rotor blade roots with adjusting protrusions
WO2012048957A1 (en) * 2010-10-12 2012-04-19 Siemens Aktiengesellschaft Turbomachine rotor with blade roots with adjusting protrusions
US9664054B2 (en) 2010-10-12 2017-05-30 Siemens Aktiengesellschaft Turbomachine rotor with blade roots with adjusting protrusions
US20140322026A1 (en) * 2012-04-19 2014-10-30 Snecma Cone of entry of blower of turboshaft engine
US9371839B2 (en) * 2012-04-19 2016-06-21 Snecma Nose dome for a turbomachine blower
DE102012016202A1 (de) * 2012-08-16 2014-02-20 Christian Siglbauer Kraftmaschine zur Umwandlung kinetischer Energie eines strömenden Mediums in Rotationsenergie eines Laufrades

Also Published As

Publication number Publication date
CH251495A (de) 1947-10-31
NL65041C (es)
DE838191C (de) 1952-03-27
FR946406A (fr) 1949-06-02
GB626181A (en) 1949-07-11
BE473515A (es)

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