EP2183467A1 - Rotoranordnung von einer turbine - Google Patents
Rotoranordnung von einer turbineInfo
- Publication number
- EP2183467A1 EP2183467A1 EP08775236A EP08775236A EP2183467A1 EP 2183467 A1 EP2183467 A1 EP 2183467A1 EP 08775236 A EP08775236 A EP 08775236A EP 08775236 A EP08775236 A EP 08775236A EP 2183467 A1 EP2183467 A1 EP 2183467A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- recesses
- blades
- blade
- surface portions
- 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
- 238000003780 insertion Methods 0.000 claims abstract description 18
- 230000037431 insertion Effects 0.000 claims abstract description 18
- 238000007789 sealing Methods 0.000 claims abstract description 7
- 230000002093 peripheral effect Effects 0.000 claims description 27
- 238000000034 method Methods 0.000 claims description 17
- 241000191291 Abies alba Species 0.000 claims description 11
- 238000001816 cooling Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 2
- 230000001419 dependent effect Effects 0.000 description 2
- 230000002730 additional effect Effects 0.000 description 1
- 238000004873 anchoring Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 239000003566 sealing material Substances 0.000 description 1
- 238000005476 soldering Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
- F05D2240/55—Seals
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/13—Two-dimensional trapezoidal
-
- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/182—Two-dimensional patterned crenellated, notched
-
- 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
- Y10T29/49316—Impeller making
Definitions
- the present invention relates to a method for improving the seal between the rotor and a plurality of anchored in the rotor, arranged in the form of a rotating rim blades according to the preamble of claim 1. Furthermore, the present invention also relates to the correspondingly designed rotors or blades.
- the individual blades are fastened to a rotor in a ring, in which the rotor is mounted on its outer circumference via a plurality of axially and has parallel in the circumferential direction juxtaposed recesses, which are formed for example as a die of a Christmas tree profile.
- the blades which are to be installed have a blade root corresponding in shape, which is designed as a corresponding male part of the Christmas tree profile with respect to the corresponding dies in the rotor.
- the blades are successively inserted in the axial direction in these recesses of the rotor, and for sealing between the adjacent blades push while the lower shrouds of the adjacent blades side by side.
- the fact must be taken into account that on the one hand between the adjacent shrouds at all times the best possible seal must be present, on the other hand, but also that the thermal expansion of the individual Components must be considered.
- the invention is therefore inter alia the object of providing a simple method for improving the seal on constructions of rotors of the type mentioned above.
- it is therefore a matter of proposing such an improved method for a rotor having a plurality of blades anchored in the rotor and arranged in the form of a rotating rim.
- the rotor has a plurality of substantially axially extending, profiled with a profiled recesses into which a ring of blades, which have corresponding with the profile blade root profiles, in a substantially axial insertion direction are preferably inserted positively and / or non-positively ,
- the rotor between the recesses over extending in the axial direction and circumferential direction tangential surface portions or peripheral surface portions, which are covered by lower shrouds of circumferentially adjacent blades arranged in the radial direction substantially at least indirectly.
- the solution to this problem is achieved in that at least one of the tangential surface portions respectively peripheral surface portions is provided with a gradation in the radial direction and in the underside of the shroud of the blade arranged above a corresponding recess is provided.
- the core of the invention thus consists, to some extent in the sense of a labyrinth seal, of improving the seal between rotor and blade or shroud of the blade. As a side effect, this results in a clever arrangement of gradations that the blade is pushed when pushed against a stop. In other words, the right axial position for the fixation is specified by the gradation.
- This stopper is not provided, as known from the prior art for example in US 5,067,877 and from many other documents in the field of such rotors, via a revolving construction (stopper ring), but only over the proposed one, only the one Range of peripheral surface sections arranged gradations, which at the same time allows the required sealing effect or very targeted flow of cooling air.
- a first preferred embodiment of the method is characterized in that the steps are provided on all circumferentially arranged circumferential surface sections of the rotor and corresponding recesses are provided on all the blades.
- the steps are provided on all circumferentially arranged circumferential surface sections of the rotor and corresponding recesses are provided on all the blades.
- the steps are designed as ring sections on the peripheral surface sections with an axial section rectangular or square cross-section (but other shapes such as triangle, trapezoid or corresponding rounded shapes are possible) is formed.
- the steps are advantageously over less than 50% of the axial extent of the peripheral surface sections, preferably over less than 20%, more preferably formed over less than 10% of the axial extent of the peripheral surface portions.
- Stages formed with a radial height which serves each of the final purpose and is dependent on the respective designed gradations. As already explained, are advantageously the
- the present invention relates to a blade, in particular for use in a method as described above.
- the blade is preferably characterized in that it has an airfoil and a blade root formed thereon, wherein the blade root has a blade root profile and a lower shroud, and on the underside of the shroud there is a recess open in the direction of insertion and towards the rotor, wherein the Recess preferably extends over the entire tangential respectively circumferential width of the underside of the shroud on both sides of the airfoil.
- the blade root profile is designed as a dovetail profile or as a Christmas tree profile.
- the present invention relates to a rotor, in particular for use in one of the methods as described above, and preferably for common use with a blade, as described above.
- the rotor is preferably characterized in that it is used for anchoring a peripheral ring of
- Shovels is formed, for which the rotor has a plurality of substantially axially extending, profiled recesses, in which the ring of blades, which have corresponding blade root profiles, in a substantially axial insertion direction in this Recesses can be inserted preferably positive fit and / or non-positive, and wherein the rotor between the recesses in the axial direction and circumferential direction extending tangential surface portions or peripheral surface portions which are covered by lower shrouds of circumferentially adjacent arranged blades in the radial direction substantially at least indirectly ,
- at least one of the tangential surface sections respectively peripheral surface sections is provided with a gradation in the radial direction.
- the profiled recesses are designed as dovetail profiles or Christmas tree profiles.
- FIG. 1 different views of a rotor with the corresponding
- Section is shown perpendicular to the axis of the rotor, in b) an axial section just before the insertion of the blade and in c) the finished inserted blade in the rotor;
- FIG. 2 corresponding views of a rotor or a blade according to the present invention in corresponding representations;
- FIG. 3 corresponding views of a rotor according to the prior art with a blade according to the present invention in corresponding
- the rotor 1 comprises a central part which has a peripheral surface substantially in the form of a cylindrical surface.
- a recesses 4 are formed.
- the recesses are designed as Christmas tree profiles.
- the recesses 4 extend in the radial direction R inwardly to the axis of the rotor.
- the Tannenbaumprofile each have alternately arranged grooves 10 and ribs 11, which are arranged in the axial direction.
- the recesses 4 are used for axially receiving the blades 2, which are formed with a corresponding male profile on the blade root.
- the recesses 4 are uniformly distributed around the circumference of the rotor 1, and between the individual recesses 4 remain portions of the substantially cylindrical peripheral surface. These peripheral surface portions 5 are, when the blades 2 are inserted, usually covered by the blade root 3, or concretely from the lower shroud 7 of the blade 2. Between adjacent blades 2 there is correspondingly an axial plane of symmetry 6, and between two adjacent recesses 4 divides the peripheral surface so in each case two peripheral surface portions 5 and 5 '.
- the sections 5, 5 ' can either actually be formed as curved sections of a cylinder surface, but they can also be designed in each case as tangential planes, wherein 5 and 5' can be arranged in the same plane or can be tilted relative to each other.
- Figure 1 b) the process of inserting a blade is shown schematically. This in a section in the plane of the axis of the rotor, that is, in a radial direction.
- a blade 2 comprises an airfoil 9, which optionally may additionally have a shroud on the radially outer side (not shown in this figure).
- the blade root 3 formed on the lower side comprises, on the one hand, a lower shroud 7 and, on the radial side, it is integrally formed downward over the blade root profile 16.
- the blade root profile 16 corresponds to a certain extent a negative of the recesses 4, that is, it is also formed as a corresponding Christmas tree profile.
- the Christmas tree profile of the blade root profile 16 corresponds as closely as possible to the Christmas tree profile of the recesses 4 in order to ensure a full seat of 16 in FIG.
- the blade is inserted into the recesses 4 in the insertion direction 8 in an axial direction A, with the lower shroud generally resting substantially flush against the peripheral surface sections 5.
- FIG. 2 now shows a modification according to the invention of such a device
- Shovel 2 shown.
- corresponding representations to Figure 1 are shown, that is, in a) a section perpendicular to the axis of the rotor, in b) a view when inserting a blade and in c) to some extent lateral view of an inserted shovel.
- an elevation 13, which can be designated as a stop element 13, is arranged on the front end of the rotor 1 in the insertion direction 8 (on the stop side 14).
- this stop element 13 extends in the circumferential direction in each case between two adjacent recesses 4 over the entire tangential extent of the circumferential surface portions 5 and 5 '.
- stop elements 13 it is also possible to apply the stop elements 13 to some extent as ring sections on the peripheral surface portions 5, for example by screws, welding or soldering (metallic feature).
- the stop element 13 typically has the shape which is rectangular in an axial section as shown in FIG. 2b). But it is also possible to form the stop element 13 as a trapezoid or, to a certain extent, as a triangle, wherein the inclined flank of the blade 2 may face, and thereby results in a further wedge with deferred blade 2.
- the blade 2 in turn has on the underside of the shroud 7 via a recess 12 corresponding to the stop element 13.
- the recess 12 is arranged at the front end of the blade 2 in the direction of insertion 8.
- the recess 12 has the corresponding female profile to a certain extent male stop element 13th
- the stop element 13 defines the End position of the blade, since the blade is inserted until the recess 12 has the stop member 13 completely absorbed in itself and impinges on the axial direction of the facing surface.
- the design according to the invention thus leads to the correct axial positioning of the blade.
- the stepped shape can also be used in a very targeted manner to allow exactly a desired amount of air to flow through the gap, for example, for cooling.
- the stopper member 13 is preferably formed with a width in the axial direction A in the range of 3-20 mm, and with a height in the radial direction R in the range from 1-20 mm.
- the advantage of the proposed embodiment is that a blade designed in accordance with the invention can also be pushed onto an existing rotor 1, that is to say a rotor without stop element 13. Accordingly, the presence of the recess 12 does not disturb the compatibility of new blades with existing rotors. New blades can be easily installed on existing rotors (bucket retrofit). The resulting achievable and available flexibility allows a tremendous degree of freedom in retrofit applications. LIST OF REFERENCE NUMBERS
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH12582007 | 2007-08-08 | ||
PCT/EP2008/059507 WO2009019126A1 (de) | 2007-08-08 | 2008-07-21 | Rotoranordnung von einer turbine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP2183467A1 true EP2183467A1 (de) | 2010-05-12 |
EP2183467B1 EP2183467B1 (de) | 2015-11-18 |
EP2183467B2 EP2183467B2 (de) | 2023-10-18 |
Family
ID=39865717
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08775236.6A Active EP2183467B2 (de) | 2007-08-08 | 2008-07-21 | Rotoranordnung von einer turbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US9435213B2 (de) |
EP (1) | EP2183467B2 (de) |
JP (1) | JP2010535968A (de) |
CA (1) | CA2707510C (de) |
MX (1) | MX2010001538A (de) |
WO (1) | WO2009019126A1 (de) |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9109457B2 (en) * | 2010-09-03 | 2015-08-18 | Siemens Energy, Inc. | Axial locking seals for aft removable turbine blade |
FR3026429B1 (fr) * | 2014-09-30 | 2016-12-09 | Snecma | Aube mobile de turbomachine, comprenant un ergot engageant une entaille de blocage d'un disque de rotor |
US20160230579A1 (en) * | 2015-02-06 | 2016-08-11 | United Technologies Corporation | Rotor disk sealing and blade attachments system |
KR101689085B1 (ko) | 2015-08-03 | 2017-01-02 | 두산중공업 주식회사 | 터빈용 마지막 버켓 고정장치 및 이를 이용한 마지막 버켓의 조립 방법 |
DE102016222312A1 (de) * | 2016-11-14 | 2018-05-17 | Man Diesel & Turbo Se | Strömungsmaschinenrotor und Verfahren zum Herstellen desselben |
FR3085420B1 (fr) | 2018-09-04 | 2020-11-13 | Safran Aircraft Engines | Disque de rotor avec arret axial des aubes, ensemble d'un disque et d'un anneau et turbomachine |
FR3092865B1 (fr) * | 2019-02-19 | 2021-01-29 | Safran Aircraft Engines | Disque de rotor avec arret axial des aubes, ensemble d’un disque et d’un anneau et turbomachine |
Family Cites Families (34)
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US2751189A (en) * | 1950-09-08 | 1956-06-19 | United Aircraft Corp | Blade fastening means |
US3047268A (en) * | 1960-03-14 | 1962-07-31 | Stanley L Leavitt | Blade retention device |
US3112914A (en) * | 1960-08-01 | 1963-12-03 | Gen Motors Corp | Turbine rotor |
US3572970A (en) * | 1969-01-23 | 1971-03-30 | Gen Electric | Turbomachinery blade spacer |
BE794573A (fr) * | 1972-02-02 | 1973-05-16 | Gen Electric | Dispositif de fixation d'aubes |
US3853425A (en) * | 1973-09-07 | 1974-12-10 | Westinghouse Electric Corp | Turbine rotor blade cooling and sealing system |
GB1527074A (en) | 1974-09-28 | 1978-10-04 | Rolls Royce | Bladed rotors |
US4483661A (en) * | 1983-05-02 | 1984-11-20 | General Electric Company | Blade assembly for a turbomachine |
FR2603333B1 (fr) * | 1986-09-03 | 1990-07-20 | Snecma | Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage |
DE3743253A1 (de) | 1987-12-19 | 1989-06-29 | Mtu Muenchen Gmbh | Axial durchstroemtes laufschaufelgitter fuer verdichter oder turbinen |
US4904160A (en) * | 1989-04-03 | 1990-02-27 | Westinghouse Electric Corp. | Mounting of integral platform turbine blades with skewed side entry roots |
US5067877A (en) * | 1990-09-11 | 1991-11-26 | United Technologies Corporation | Fan blade axial retention device |
US5211407A (en) * | 1992-04-30 | 1993-05-18 | General Electric Company | Compressor rotor cross shank leak seal for axial dovetails |
US5257909A (en) * | 1992-08-17 | 1993-11-02 | General Electric Company | Dovetail sealing device for axial dovetail rotor blades |
US5302086A (en) * | 1992-08-18 | 1994-04-12 | General Electric Company | Apparatus for retaining rotor blades |
US5281097A (en) * | 1992-11-20 | 1994-01-25 | General Electric Company | Thermal control damper for turbine rotors |
FR2700807B1 (fr) * | 1993-01-27 | 1995-03-03 | Snecma | Système de rétention et d'étanchéité d'aubes engagées dans des brochages axiaux d'un disque de rotor. |
GB2294732A (en) * | 1994-11-05 | 1996-05-08 | Rolls Royce Plc | Integral disc seal for turbomachine |
US5573375A (en) * | 1994-12-14 | 1996-11-12 | United Technologies Corporation | Turbine engine rotor blade platform sealing and vibration damping device |
US5501575A (en) * | 1995-03-01 | 1996-03-26 | United Technologies Corporation | Fan blade attachment for gas turbine engine |
GB9517369D0 (en) * | 1995-08-24 | 1995-10-25 | Rolls Royce Plc | Bladed rotor |
JPH1193005A (ja) | 1997-09-18 | 1999-04-06 | Takikiyo Kk | パジャマ |
US6077035A (en) * | 1998-03-27 | 2000-06-20 | Pratt & Whitney Canada Corp. | Deflector for controlling entry of cooling air leakage into the gaspath of a gas turbine engine |
US6030178A (en) * | 1998-09-14 | 2000-02-29 | General Electric Co. | Axial entry dovetail segment for securing a closure bucket to a turbine wheel and methods of installation |
US6109877A (en) * | 1998-11-23 | 2000-08-29 | Pratt & Whitney Canada Corp. | Turbine blade-to-disk retention device |
US6190131B1 (en) * | 1999-08-31 | 2001-02-20 | General Electric Co. | Non-integral balanced coverplate and coverplate centering slot for a turbine |
US6634863B1 (en) * | 2000-11-27 | 2003-10-21 | General Electric Company | Circular arc multi-bore fan disk assembly |
DE50211431D1 (de) | 2001-09-25 | 2008-02-07 | Alstom Technology Ltd | Dichtungsanordnung zur dichtspaltreduzierung innerhalb einer strömungsrotationsmaschine |
US6846159B2 (en) * | 2002-04-16 | 2005-01-25 | United Technologies Corporation | Chamfered attachment for a bladed rotor |
US6786696B2 (en) * | 2002-05-06 | 2004-09-07 | General Electric Company | Root notched turbine blade |
US6827554B2 (en) * | 2003-02-25 | 2004-12-07 | General Electric Company | Axial entry turbine bucket dovetail with integral anti-rotation key |
GB2411697B (en) * | 2004-03-06 | 2006-06-21 | Rolls Royce Plc | A turbine having a cooling arrangement |
GB0405679D0 (en) * | 2004-03-13 | 2004-04-21 | Rolls Royce Plc | A mounting arrangement for turbine blades |
US20070128363A1 (en) * | 2005-12-07 | 2007-06-07 | Honeywell International, Inc. | Platinum plated powder metallurgy turbine disk for elevated temperature service |
-
2008
- 2008-07-21 JP JP2010519409A patent/JP2010535968A/ja active Pending
- 2008-07-21 WO PCT/EP2008/059507 patent/WO2009019126A1/de active Application Filing
- 2008-07-21 MX MX2010001538A patent/MX2010001538A/es active IP Right Grant
- 2008-07-21 EP EP08775236.6A patent/EP2183467B2/de active Active
- 2008-07-21 CA CA2707510A patent/CA2707510C/en not_active Expired - Fee Related
-
2010
- 2010-02-08 US US12/701,852 patent/US9435213B2/en not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO2009019126A1 * |
Also Published As
Publication number | Publication date |
---|---|
US9435213B2 (en) | 2016-09-06 |
EP2183467B1 (de) | 2015-11-18 |
JP2010535968A (ja) | 2010-11-25 |
EP2183467B2 (de) | 2023-10-18 |
CA2707510A1 (en) | 2009-02-12 |
MX2010001538A (es) | 2010-03-15 |
CA2707510C (en) | 2016-09-27 |
US20100166563A1 (en) | 2010-07-01 |
WO2009019126A1 (de) | 2009-02-12 |
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