EP1092081A1 - Rotor for a turbomachine - Google Patents
Rotor for a turbomachineInfo
- Publication number
- EP1092081A1 EP1092081A1 EP99939943A EP99939943A EP1092081A1 EP 1092081 A1 EP1092081 A1 EP 1092081A1 EP 99939943 A EP99939943 A EP 99939943A EP 99939943 A EP99939943 A EP 99939943A EP 1092081 A1 EP1092081 A1 EP 1092081A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- flange
- rotor according
- disk
- bolts
- rotor
- 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.)
- Granted
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
- F01D5/02—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
Definitions
- the invention relates to a rotor for a turbomachine, with at least two bladed stages, the disks are releasably connected to one another.
- Turbomachine rotors generally have several stages provided with blades, the disks of which are different, e.g. by welding or releasably by screwing together. In the present case, only stages that are releasably connected are considered.
- the disks In the case of a known rotor, the disks have cylindrical or conical shells which extend essentially in the axial direction, at the end sections of which disk-ring-shaped flanges are provided, on which adjacent disks are connected with screws, stud bolts or the like. If an intermediate stage seal is not integrated in the shells, it is clamped between the flanges.
- Such a type of connection can only be used for components with a relatively low peripheral speed, e.g. Use long-running low-pressure turbines, since the centrifugal forces that occur in the case of disks designed for high circumferential speeds produce excessive circumferential stresses in the flange connection.
- the holes in the flanges represent notch points that cause local stress increases and severely limit the cyclical life of the component.
- a disk has bores by means of which it is screwed to adjacent disks which have cylindrical or conical shells with flanges.
- the washer body limits the radial expansion of the connection point due to centrifugal force. It is problematic, however, that the bores in the heavily loaded disc body represent life-limiting notches.
- a connection of rotor elements of a gas turbine is known from US Pat. No. 4,844,694, in which the disk located at the connection point has a bore for inserting a bolt, the bores in the highly loaded disk body representing notch points which limit the service life.
- the last-mentioned disadvantage is also present in the pin connection between rotor elements of a gas turbine disclosed in US Pat. No. 5,052,891, in which a hole is provided for the pin connection in the disk located at the connection point.
- the invention has for its object to provide a rotor for a turbomachine of the type described in the opening paragraph, in which the disks are detachably connected to one another without extreme increases in tension due to notches in the disk occurring.
- a first disk has at least one of its two side surfaces a first flange which is connected or clamped to a second flange of an adjacent disk by bolts.
- the first flange preferably extends radially inward at an axial distance from the side face of the first disk, forming an intermediate space.
- the first flange is designed as a disk ring which has cutouts along its inner end or peripheral edge.
- the cutouts are preferably opened inwards so that the centrifugal force generated by the bolts can be absorbed by the edge surface of the cutouts.
- the recesses are arranged equidistantly along the peripheral edge.
- a hole, an elongated hole or a further recess can be provided between the recesses.
- a flange section of an intermediate stage seal is most preferably clamped between the first and second flange, the flange section of the intermediate stage seal preferably having bores which are aligned with the cutouts of the first flange and fix the bolts in the radial direction during assembly.
- the bolts at their ends facing the first disk have a transverse section extending at right angles to their longitudinal axis, with which they are supported on an inner side surface of the first flange a.
- the bolts are preferably T-head bolts.
- the distance between the first flange and the side surface of the first disk is preferably as small as possible, but larger than the thickness of the transverse section of the bolt, in order to avoid a pressure point on the highly loaded first disk.
- the flange of an adjacent washer has at its radially inner end an essentially axially extending support section on which the transverse section of the bolts is supported in order to secure the bolts against rotation.
- the first disk has a first flange on both side surfaces, so that the disks of rotors can also be detachably connected with more than two stages in this way.
- FIG. 1 is a view in longitudinal section of an embodiment of the rotor according to the invention, which has no hatching for a better overview.
- Fig. 2 is a broken cross-sectional view along line II-II of Fig. 1 and
- FIG. 3 shows a broken view in longitudinal section of a further exemplary embodiment of the rotor according to the invention.
- Fig. 1 shows a longitudinal section of an embodiment of the rotor according to the invention for a turbomachine, which has three stages.
- the steps are each provided with a shovel 1, 2 and 3 and a first disk 4 and two adjacent disks 5, 6.
- the first disc 4 has a flange 9 and 10 on its two side surfaces 7, 8.
- the flanges 9, 10 extend at an axial distance A from their inner side surfaces 11, 12 to the side surfaces 7, 8 the first disc 4. In this way, between the first disc 4 and the flanges 9, 10 there is an intermediate space Z which is open inwards in the radial direction.
- the distance A is to be kept as small as possible in order to begin with the radial expansion of the flanges 9, 10 or the flange connection through the body of the disk 4.
- a transverse section 13 engages a (screw) bolt 14 in the intermediate space Z and is supported on the inner side surface, e.g. 12, the flange 10.
- the disks 5, 6 adjacent to the middle, first disk 4 each have cylindrical shells 16 which extend essentially in the axial direction and which can also be conical.
- the shells 16 have at their ends remote from the disks 5, 6 each a second flange 17, which is connected to the flanges 9, 10 of the first disk 4 by means of (screw) bolts 14 or the like. is firmly clamped.
- At the second flanges 17 of the disks 5,6 each adjoins a substantially axially extending support section 18, on which the transverse sections 13 of the bolts 14 can be supported, thereby preventing the bolts 14 from rotating. This ensures that no pressure points occur on the highly loaded, first disks 4 when mounting or tightening the (screw) bolts 14.
- an intermediate stage seal 19 with its flange section 20 is clamped and releasably attached.
- the intermediate stage seals 19 can alternatively also be arranged integrally on the disks 5, 6 or their shells 16.
- FIG. 2 shows a cut out and broken cross-sectional view according to line II-II from FIG. 1, in the upper partial section of which the flange 9 is shown in a top view.
- the flange 9 is designed as a disk ring, on the inner end face or peripheral edge 21 of which is open in the radial direction and slit-like Recesses 15 are provided.
- a (screw) bolt 14 is inserted, the cross section 13 is shown in dashed lines. After mounting, it is supported on the inner side surface 11 of the flange 9.
- its transverse section 13 is also supported on the support section 18 of the shell 16 of the adjacent disk 5.
- the bores 22 can also be used as elongated holes, further cutouts or the like. be trained.
- the disk-ring-shaped flange section 20 of the intermediate stage seal 19 is shown, which has bores 23.
- the bores 23 are aligned with the cutouts 15 in the flanges 9, 10 of the first disk 4, as are corresponding bores 24 in the second flanges 17 from the disks 5, 6 adjacent to the first disk 4.
- the bores 23 in the flange section 20 of the intermediate stage seal 19 are opened radially inward, their opening dimension being smaller than their diameter, so as to radially fix the (screw) bolts 14 during assembly guarantee.
- the bores 23 can also be designed as closed bores.
- every second stage is provided with a first disc 4 having at least one flange 9 or 10.
- Fig. 3 shows a further embodiment of the rotor according to the invention, in which the radius R at the transition between the inner side surface 8 of the first disc 4 and the flange 10 or its inner side surface 12 is increased for reasons of strength.
- the distance A between the side surface 8 of the first disk 4 and the inner side surface 12 of the flange 10 is greater, the (screw) bolt 14 has a shear ring or collar 25 which rests on an outer side surface 26 of the flange 10 and prevents axial displacement of the (screw) bolt 14, so that the cross sections 13 during assembly not be pressed against the first disc 4 and lose their security against twisting.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19828817A DE19828817C2 (en) | 1998-06-27 | 1998-06-27 | Rotor for a turbo machine |
DE19828817 | 1998-06-27 | ||
PCT/DE1999/001840 WO2000000719A1 (en) | 1998-06-27 | 1999-06-24 | Rotor for a turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1092081A1 true EP1092081A1 (en) | 2001-04-18 |
EP1092081B1 EP1092081B1 (en) | 2003-07-30 |
Family
ID=7872288
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99939943A Expired - Lifetime EP1092081B1 (en) | 1998-06-27 | 1999-06-24 | Rotor for a turbomachine |
Country Status (6)
Country | Link |
---|---|
US (1) | US6499957B1 (en) |
EP (1) | EP1092081B1 (en) |
JP (1) | JP2002519564A (en) |
CA (1) | CA2335964A1 (en) |
DE (2) | DE19828817C2 (en) |
WO (1) | WO2000000719A1 (en) |
Families Citing this family (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ITMI20011961A1 (en) * | 2001-09-20 | 2003-03-20 | Nuovo Pignone Spa | IMPROVED COUPLING FLANGE BETWEEN AXIAL COMPRESSOR AND GROUP OF HIGH PRESSURE ROTOR DISCS IN A GAS TURBINE |
FR2857419B1 (en) * | 2003-07-11 | 2005-09-23 | Snecma Moteurs | IMPROVED CONNECTION BETWEEN DISCS AND ROTOR LINES OF A COMPRESSOR |
DE102004016244B4 (en) | 2004-04-02 | 2007-08-23 | Mtu Aero Engines Gmbh | Rotor for a turbomachine |
FR2868814B1 (en) * | 2004-04-09 | 2009-12-18 | Snecma Moteurs | DEVICE FOR ASSEMBLING ANNULAR FLANGES, PARTICULARLY IN A TURBOMACHINE |
FR2931873B1 (en) * | 2008-05-29 | 2010-08-20 | Snecma | A TURBINE DISK ASSEMBLY OF A GAS TURBINE ENGINE AND A BEARING BRIDGE SUPPORT CIRCUIT, COOLING CIRCUIT OF A TURBINE DISK OF SUCH AN ASSEMBLY. |
US8043062B2 (en) * | 2008-09-04 | 2011-10-25 | Mitsubishi Heavy Industries, Ltd. | Turbine rotor and turbine having the same |
DE102008048006B4 (en) | 2008-09-19 | 2019-02-21 | MTU Aero Engines AG | Shaft power engine, in particular for an aircraft, with a cooling gas guide system in the region of the mounting flanges of the rotor disks |
FR2961249B1 (en) * | 2010-06-10 | 2014-05-02 | Snecma | DEVICE FOR COOLING ALVEOLS OF A TURBOMACHINE ROTOR DISC |
US9004871B2 (en) * | 2012-08-17 | 2015-04-14 | General Electric Company | Stacked wheel assembly for a turbine system and method of assembling |
US9279325B2 (en) * | 2012-11-08 | 2016-03-08 | General Electric Company | Turbomachine wheel assembly having slotted flanges |
US11073044B2 (en) * | 2013-01-21 | 2021-07-27 | Raytheon Technologies Corporation | Adjustable floating oil channel for gas turbine engine gear drive |
US10465519B2 (en) * | 2013-10-17 | 2019-11-05 | Pratt & Whitney Canada Corp. | Fastening system for rotor hubs |
US10502059B2 (en) * | 2015-02-02 | 2019-12-10 | United Technologies Corporation | Alignment tie rod device and method of utilization |
US10316681B2 (en) * | 2016-05-31 | 2019-06-11 | General Electric Company | System and method for domestic bleed circuit seals within a turbine |
FR3062415B1 (en) * | 2017-02-02 | 2019-06-07 | Safran Aircraft Engines | ROTOR OF TURBINE TURBINE ENGINE WITH VENTILATION BY LAMINATION |
DE102017214058A1 (en) * | 2017-08-11 | 2019-02-14 | MTU Aero Engines AG | Rotor for a turbomachine |
US11428124B2 (en) | 2018-11-21 | 2022-08-30 | Raytheon Technologies Corporation | Flange stress-reduction features |
CN112360886B (en) * | 2020-10-28 | 2022-03-25 | 中国航发湖南动力机械研究所 | Disc shaft connecting structure |
CN115614324B (en) * | 2022-11-22 | 2023-05-05 | 中国航发四川燃气涡轮研究院 | Compressor rotor multistage wheel disc connection structure based on variable cross-section bolted connection |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2614796A (en) * | 1950-03-30 | 1952-10-21 | Westinghouse Electric Corp | Rotor construction |
US3688371A (en) * | 1970-04-30 | 1972-09-05 | Gen Electric | The method of manufacturing compositely formed rotors |
FR2552159B1 (en) * | 1983-09-21 | 1987-07-10 | Snecma | DEVICE FOR CONNECTING AND SEALING TURBINE STATOR BLADE SECTIONS |
CA1209482A (en) * | 1983-12-22 | 1986-08-12 | Douglas L. Kisling | Two stage rotor assembly with improved coolant flow |
FR2607866B1 (en) * | 1986-12-03 | 1991-04-12 | Snecma | FIXING AXES OF TURBOMACHINE ROTORS, MOUNTING METHOD AND ROTORS THUS MOUNTED |
US5052891A (en) * | 1990-03-12 | 1991-10-01 | General Motors Corporation | Connection for gas turbine engine rotor elements |
US5350278A (en) | 1993-06-28 | 1994-09-27 | The United States Of America As Represented By The Secretary Of The Air Force | Joining means for rotor discs |
US5388963A (en) * | 1993-07-02 | 1995-02-14 | United Technologies Corporation | Flange for high speed rotors |
GB2303188B (en) * | 1995-07-13 | 1999-04-28 | Bmw Rolls Royce Gmbh | An assembly of two turbine rotor discs |
-
1998
- 1998-06-27 DE DE19828817A patent/DE19828817C2/en not_active Expired - Lifetime
-
1999
- 1999-06-24 JP JP2000557062A patent/JP2002519564A/en active Pending
- 1999-06-24 EP EP99939943A patent/EP1092081B1/en not_active Expired - Lifetime
- 1999-06-24 WO PCT/DE1999/001840 patent/WO2000000719A1/en active IP Right Grant
- 1999-06-24 CA CA002335964A patent/CA2335964A1/en not_active Abandoned
- 1999-06-24 US US09/720,504 patent/US6499957B1/en not_active Expired - Lifetime
- 1999-06-24 DE DE59906444T patent/DE59906444D1/en not_active Expired - Lifetime
Non-Patent Citations (1)
Title |
---|
See references of WO0000719A1 * |
Also Published As
Publication number | Publication date |
---|---|
CA2335964A1 (en) | 2000-01-06 |
WO2000000719A1 (en) | 2000-01-06 |
DE19828817A1 (en) | 1999-12-30 |
JP2002519564A (en) | 2002-07-02 |
DE59906444D1 (en) | 2003-09-04 |
US6499957B1 (en) | 2002-12-31 |
DE19828817C2 (en) | 2000-07-13 |
EP1092081B1 (en) | 2003-07-30 |
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