WO2009100748A1 - Mehrteiliger beschaufelter rotor für eine strömungsmaschine - Google Patents
Mehrteiliger beschaufelter rotor für eine strömungsmaschine Download PDFInfo
- Publication number
- WO2009100748A1 WO2009100748A1 PCT/EP2008/010557 EP2008010557W WO2009100748A1 WO 2009100748 A1 WO2009100748 A1 WO 2009100748A1 EP 2008010557 W EP2008010557 W EP 2008010557W WO 2009100748 A1 WO2009100748 A1 WO 2009100748A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- groove
- rotor
- rotor according
- blade
- parting plane
- Prior art date
Links
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
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- 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
- F01D5/02—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
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- 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
- F01D5/3069—Fixing blades to rotors; Blade roots ; Blade spacers between two discs or rings
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
-
- 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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
Definitions
- the invention relates to a multi-part bladed rotor for a turbomachine, in particular a gas or steam turbine or an axial compressor, according to the preamble of claim 1, as well as a turbomachine with such a rotor.
- Bladed rotors such as those used as a compressor rotor in the compressor range of a gas turbine rotor, are often constructed in several parts from individual, interconnected disks, with a separate disk being provided for each stage of the compressor or a plurality of blade rows forming one stage on a disk. a so-called multidisk can be arranged.
- Such multi-part bladed rotors according to the preamble of claim 1 are known for example from EP 1 728 973 A1 or DE-OS 26 43 886, in which the individual discs axially clamped together via tie rods and Hirth serrations formed axially between the blade rows are, centered to each other and rotationally fixed to each other.
- Such a face gear is usually arranged on mechanical reasons and to avoid disturbances of the flow on a diameter which is smaller than the outer diameter of the rotor.
- a clearance for the tool outlet must be provided. This adversely increases the material manufacturing and assembly costs, since this space must be closed during assembly of the rotor with a corresponding filler to prevent disturbance of the flow.
- FIG. 2 shows, in partial cross section, the parting plane 7a of a multi-part rotor according to the prior art, in which a spur toothing 3a is arranged on a diameter which is smaller than the outer diameter of the rotor.
- a free space 10a provided for the tool outlet, which is closed with a filler 11.
- the object of the present invention is to provide an improved rotor for a turbomachine.
- a rotor according to the preamble of claim 1 is further developed by its characterizing features.
- Claim 13 provides a turbomachine with a rotor according to the invention, the subclaims preferred developments under protection.
- a blade root of the corresponding blade in a correspondingly shaped groove in the axial or circumferential direction of the rotor, which preferably has one or more undercuts Radial direction is determined form fit.
- 2 shows a blade 8, the blade root is inserted into an axial groove, and a blade 9, the blade root is mounted in a circumferential groove, in a direction of insertion into the groove, the blade root can be secured by intermediate or closure pieces or adjacent blade feet, for example, wedged or screwed.
- a multi-part bladed rotor according to the present invention for a turbomachine in particular a gas or steam turbine or an axial compressor, two or more discs, the mutually facing end faces in a parting plane rotatably connected to each other, wherein formed in this parting plane a groove, which receives one or more blade feet.
- a weakening of the structure tur of the rotor in particular an interruption of the flow of force in the rotor, but also a disturbance of the flow can be avoided by an additional free space in addition to the required for receiving the blade roots anyway groove.
- Another advantage may be that the production, in particular a chip-making production, and a control of the so far axially divisible groove formed by the parting plane is facilitated.
- the two discs can be releasably, in particular form-fitting, rotatably connected to each other.
- a face toothing in particular a Hirth toothing or a Gleason toothing
- the at least two disks can then be connected together axially by one or more tie rods.
- the two panes can also be connected inseparably to one another in the parting plane, for example by welding. Both forms can also be combined with each other by a disc with an adjacent disc releasably connected, in particular via a spur gear teeth, inextricably connected to an opposite adjacent disc, in particular welded.
- grooves for blade roots may extend in the axial direction of the rotor, as known for example from DE-OS-1 182 474.
- each tooth root of a spur gear ends in such an axial groove, which thus enables the required tool outlet.
- the groove is preferably a groove extending in the circumferential direction of the rotor for receiving a plurality of blade roots distributed over the circumference.
- the groove may have a Christmas tree cross section.
- a Christmas tree cross-section is in the sense of the present invention characterized in that it has one or more undercuts in the radial direction, which can be engaged behind by corresponding projections of the blade root and fix it in a form-locking manner in the radial direction.
- a spur gear extends radially into a groove bottom of the groove. That is, the spur gear is radially within the on Outside perimeter formed groove disposed on a diameter which is smaller than the outer diameter of the rotor.
- the blade roots prior to joining the two disks, can be arranged between the two groove halves separated by the parting plane, so that they engage behind undercuts of the then closed groove in the case of bonded disks.
- the groove may have a substantially constant cross section in the circumferential direction of the rotor.
- the parting plane can be formed axially at any point of the groove. Preferably, it extends substantially through the center of area of a groove cross-section, so that the blade root is supported approximately equally in both disks.
- the groove may be formed substantially symmetrically to the parting plane.
- symmetry is understood to mean not only a mathematical symmetry in which the contour of one disc in an axial section corresponds to the complementary contour of the other disc, but also a functional symmetry, for example the formation of corresponding undercuts, but in particular in the radial direction relative to other disc can be offset. This is particularly advantageous in gas turbine compressor rotors in which the outer radius of the rotor hub generally increases in the flow direction in order to take account of the increasingly compressed fluid.
- One or more further rows of blades may be provided on one or both disks parallel to the parting plane, so that such a disk forms several stages of the turbomachine.
- Such further blade rows can likewise be fastened in a form-fitting manner by means of blade roots held in further grooves or formed integrally with the disk, ie they can be connected to this urge-formed or permanently bonded, for example welded or riveted.
- a combination is also possible in which one or both discs have both notched and integrally formed vanes.
- two or more disks may each be non-rotatably connected to each other in a parting plane, in which a groove for receiving one or more blade roots is formed.
- FIG. 1 shows a gas turbine according to an embodiment of the present invention in axial half section.
- Fig. 2 two blades connected to each other in a parting plane
- FIG. 3 in Fig. 2 corresponding representation of two partially connected in a parting plane slices of a rotor according to an embodiment of the present invention.
- FIG. 1 shows in axial half section the upper half of a gas turbine according to an embodiment of the present invention.
- a compressor rotor 1 of the gas turbine is designed as a rotor or rotor in disk construction, each disc 2 as a so-called multi-disk several axially successively arranged rows of circumferentially distributed blades 5 carries whose blade roots are held for this purpose in corresponding grooves 6 in the circumferential direction of the rotor 1 ,
- the grooves 6 have mounting holes that allow insertion of the blades (not shown).
- the discs 2 are positioned to each other by means of Hirth serrations 3 or Gleason gears and are braced by screws or tie rods 4 to a rotor assembly.
- the parting planes 7a of the multi-discs between grooves of two adjacent blade rows 8 and 9 are arranged. Since the Hirth spur gearing 3a is arranged on a diameter which is smaller than the outer diameter of the compressor disks, must for the manufacturing process of the gearing 3a a corresponding space 10a are provided for the outlet of the tool. This clearance 10a must be closed during assembly of the rotor with corresponding filler pieces 11 in order to ensure a continuous hub contour and thus a continuous course of the inner wall 12 of the flow channel 13 of the gas turbine.
- the parting plane 7 of adjacent multi-discs is placed in the plane of symmetry of a groove 10 for receiving blade roots 14 of blades 5.
- the Hirth spur gear 3 is arranged radially below this axially divided groove 10. This arrangement has the advantage that the groove 10 can be used at the same time as a free space for the outlet of the tool for producing the Hirth spur gear teeth 3.
- the groove 10 is closed during assembly of the rotor by the feet 14 of the compressor rotor blades 5 of the corresponding stage.
- This arrangement has the advantage that it is possible to dispense with the additional filler 11. Furthermore, the manufacture and control of the surfaces 15 in the axially split groove 10 is facilitated.
- the blades of the steps between the parting planes are formed as an integral component of the discs (bladed disc BLISK).
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)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CA2709167A CA2709167C (en) | 2008-02-13 | 2008-12-11 | Multi-component bladed rotor for a turbomachine |
EP08872286.3A EP2245272B1 (de) | 2008-02-13 | 2008-12-11 | Mehrteiliger beschaufelter rotor für eine strömungsmaschine |
JP2010546221A JP5393704B2 (ja) | 2008-02-13 | 2008-12-11 | 流体機械のための複数部材型翼付きロータ |
US12/812,862 US8784064B2 (en) | 2008-02-13 | 2008-12-11 | Multi-component bladed rotor for a turbomachine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102008008887A DE102008008887A1 (de) | 2008-02-13 | 2008-02-13 | Mehrteiliger beschaufelter Rotor für eine Strömungsmaschine |
DE102008008887.0 | 2008-02-13 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009100748A1 true WO2009100748A1 (de) | 2009-08-20 |
Family
ID=40790950
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2008/010557 WO2009100748A1 (de) | 2008-02-13 | 2008-12-11 | Mehrteiliger beschaufelter rotor für eine strömungsmaschine |
Country Status (6)
Country | Link |
---|---|
US (1) | US8784064B2 (de) |
EP (1) | EP2245272B1 (de) |
JP (1) | JP5393704B2 (de) |
CA (1) | CA2709167C (de) |
DE (1) | DE102008008887A1 (de) |
WO (1) | WO2009100748A1 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3346140A4 (de) * | 2015-11-27 | 2018-10-17 | Mitsubishi Heavy Industries Compressor Corporation | Haltebolzen für stationäres element und radialverdichter |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008008887A1 (de) | 2008-02-13 | 2009-08-27 | Man Turbo Ag | Mehrteiliger beschaufelter Rotor für eine Strömungsmaschine |
DE102009004926A1 (de) * | 2009-01-16 | 2010-07-22 | Mtu Aero Engines Gmbh | Schaufelintegrierte geteilte Scheibe einer Turbinen- oder Verdichterstufe |
US10077663B2 (en) * | 2011-09-29 | 2018-09-18 | United Technologies Corporation | Gas turbine engine rotor stack assembly |
US20140030084A1 (en) * | 2012-07-24 | 2014-01-30 | General Electric Company | Article of manufacture for turbomachine |
KR101835992B1 (ko) * | 2016-09-22 | 2018-03-08 | 두산중공업 주식회사 | 가스 터빈용 로터 디스크 조립체 |
US10934863B2 (en) * | 2018-11-13 | 2021-03-02 | Rolls-Royce Corporation | Turbine wheel assembly with circumferential blade attachment |
IT201900014724A1 (it) | 2019-08-13 | 2021-02-13 | Ge Avio Srl | Elementi di trattenimento delle pale per turbomacchine. |
IT201900014736A1 (it) | 2019-08-13 | 2021-02-13 | Ge Avio Srl | Elementi di tenuta integrali per pale trattenute in un rotore a tamburo esterno anulare girevole in una turbomacchina. |
IT201900014739A1 (it) | 2019-08-13 | 2021-02-13 | Ge Avio Srl | Elementi di trattenimento delle pale per turbomacchine. |
EP4150217A1 (de) | 2020-05-14 | 2023-03-22 | Siemens Energy Global GmbH & Co. KG | Verdichterrotorstruktur |
EP4162164B1 (de) * | 2020-07-08 | 2024-06-26 | Siemens Energy Global GmbH & Co. KG | Verdichterrotor mit dichtelementen |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB359350A (en) * | 1930-03-03 | 1931-10-22 | Ltd Co Formerly Skoda Works | Connection of rotarys for combustion turbines |
US1876067A (en) * | 1926-09-20 | 1932-09-06 | Bendix Aviat Corp | Blade structure for turbines |
GB622626A (en) * | 1947-04-02 | 1949-05-04 | Armstrong Siddeley Motors Ltd | Manufacture of a bladed turbine disc |
GB710119A (en) * | 1951-08-27 | 1954-06-09 | Rolls Royce | Improvements in or relating to turbines and compressors and the like machines |
GB723549A (en) * | 1952-01-14 | 1955-02-09 | Rolls Royce | Improvements in or relating to torque-transmitting couplings for interconnecting thediscs of a gas-turbine engine rotor |
US5743713A (en) * | 1995-09-21 | 1998-04-28 | Ngk Insulators, Ltd. | Blade, turbine disc and hybrid type gas turbine blade |
Family Cites Families (19)
Publication number | Priority date | Publication date | Assignee | Title |
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GB394001A (en) * | 1931-12-18 | 1933-06-19 | Parsons C A & Co Ltd | Improvements in and relating to built-up rotors, suitable for steam turbines |
US2573621A (en) * | 1946-03-21 | 1951-10-30 | English Electric Co Ltd | Elastic fluid turbine |
US2650017A (en) * | 1948-11-26 | 1953-08-25 | Westinghouse Electric Corp | Gas turbine apparatus |
GB706730A (en) * | 1951-04-11 | 1954-04-07 | Vickers Electrical Co Ltd | Improvements relating to turbine rotors |
DE1182474B (de) | 1961-10-25 | 1964-11-26 | Siemens Ag | Gasturbine der Scheibenbauart mit die verspannten Scheiben gegeneinander abstuetzenden Zwischenringen sowie einer Schaufelfusskuehlung durch ein gasfoermiges Medium |
NO121183B (de) * | 1968-11-25 | 1971-01-25 | Kongsberg Vapenfab As | |
GB1349170A (en) * | 1970-07-09 | 1974-03-27 | Kraftwerk Union Ag | Rotor for a gas turbine engine |
US3689177A (en) * | 1971-04-19 | 1972-09-05 | Gen Electric | Blade constraining structure |
GB1364120A (en) * | 1971-11-26 | 1974-08-21 | Rolls Royce | Axial flow compressors |
US4021138A (en) * | 1975-11-03 | 1977-05-03 | Westinghouse Electric Corporation | Rotor disk, blade, and seal plate assembly for cooled turbine rotor blades |
DE2643886C2 (de) * | 1976-09-29 | 1978-02-09 | Kraftwerk Union AG, 4330 Mülheim | Gasturbinentäufer in Scheibenbauart |
JPS57168005A (en) * | 1981-04-10 | 1982-10-16 | Hitachi Ltd | Rotor structue for axial machines |
GB9606963D0 (en) * | 1996-04-02 | 1996-06-05 | Rolls Royce Plc | A root attachment for a turbomachine blade |
DE102004052483A1 (de) * | 2004-10-28 | 2006-05-11 | Man Turbo Ag | Vorrichtung zum Einspritzen von Wasser oder Wasserdampf in das Arbeitsmittel einer Gasturbinenanlage |
US7261518B2 (en) * | 2005-03-24 | 2007-08-28 | Siemens Demag Delaval Turbomachinery, Inc. | Locking arrangement for radial entry turbine blades |
EP1728973A1 (de) | 2005-06-01 | 2006-12-06 | Siemens Aktiengesellschaft | Verfahren zum Sperren eines Spaltes einer Strömungsmaschine und Strömungsmaschine zum Durchführen eines solchen Verfahrens |
US7341431B2 (en) * | 2005-09-23 | 2008-03-11 | General Electric Company | Gas turbine engine components and methods of fabricating same |
DE102008008887A1 (de) | 2008-02-13 | 2009-08-27 | Man Turbo Ag | Mehrteiliger beschaufelter Rotor für eine Strömungsmaschine |
FR2951224B1 (fr) * | 2009-10-13 | 2011-12-09 | Turbomeca | Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque |
-
2008
- 2008-02-13 DE DE102008008887A patent/DE102008008887A1/de not_active Withdrawn
- 2008-12-11 US US12/812,862 patent/US8784064B2/en active Active
- 2008-12-11 CA CA2709167A patent/CA2709167C/en active Active
- 2008-12-11 JP JP2010546221A patent/JP5393704B2/ja active Active
- 2008-12-11 WO PCT/EP2008/010557 patent/WO2009100748A1/de active Application Filing
- 2008-12-11 EP EP08872286.3A patent/EP2245272B1/de active Active
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1876067A (en) * | 1926-09-20 | 1932-09-06 | Bendix Aviat Corp | Blade structure for turbines |
GB359350A (en) * | 1930-03-03 | 1931-10-22 | Ltd Co Formerly Skoda Works | Connection of rotarys for combustion turbines |
GB622626A (en) * | 1947-04-02 | 1949-05-04 | Armstrong Siddeley Motors Ltd | Manufacture of a bladed turbine disc |
GB710119A (en) * | 1951-08-27 | 1954-06-09 | Rolls Royce | Improvements in or relating to turbines and compressors and the like machines |
GB723549A (en) * | 1952-01-14 | 1955-02-09 | Rolls Royce | Improvements in or relating to torque-transmitting couplings for interconnecting thediscs of a gas-turbine engine rotor |
US5743713A (en) * | 1995-09-21 | 1998-04-28 | Ngk Insulators, Ltd. | Blade, turbine disc and hybrid type gas turbine blade |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3346140A4 (de) * | 2015-11-27 | 2018-10-17 | Mitsubishi Heavy Industries Compressor Corporation | Haltebolzen für stationäres element und radialverdichter |
US10801506B2 (en) | 2015-11-27 | 2020-10-13 | Mitsubishi Heavy Industries Compressor Corporation | Fixing bolt for stationary member, and centrifugal compressor |
Also Published As
Publication number | Publication date |
---|---|
JP5393704B2 (ja) | 2014-01-22 |
CA2709167C (en) | 2013-04-02 |
EP2245272A1 (de) | 2010-11-03 |
US8784064B2 (en) | 2014-07-22 |
EP2245272B1 (de) | 2016-04-06 |
JP2011511900A (ja) | 2011-04-14 |
US20110052371A1 (en) | 2011-03-03 |
DE102008008887A1 (de) | 2009-08-27 |
CA2709167A1 (en) | 2009-08-20 |
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