US20010019697A1 - Fastening rotor blades in a turbomachine - Google Patents
Fastening rotor blades in a turbomachine Download PDFInfo
- Publication number
- US20010019697A1 US20010019697A1 US09/794,050 US79405001A US2001019697A1 US 20010019697 A1 US20010019697 A1 US 20010019697A1 US 79405001 A US79405001 A US 79405001A US 2001019697 A1 US2001019697 A1 US 2001019697A1
- Authority
- US
- United States
- Prior art keywords
- blade
- recess
- blade roots
- rotor blades
- connecting piece
- 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.)
- Abandoned
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
- 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
- F01D5/32—Locking, e.g. by final locking blades or keys
-
- 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
Definitions
- the invention relates to rotor blades with blade roots, which are fastened in peripheral grooves on the rotor of a turbomachine. It relates, in particular, to fastening them and securing them against twisting and falling out of the groove.
- a known way of assembling rotor blades on a rotor of a turbomachine is anchoring by means of blade roots in T-shaped peripheral grooves.
- a certain assembly clearance in the peripheral direction is necessary.
- This problem is solved by reducing the assembly clearance by tightly fitting intermediate pieces between the blade roots so that the assembly clearance is filled up. After fitting of the intermediate pieces, however, the remaining clearance between the blade roots is often too small to permit free thermal expansions. Because of the expansions, forces then occur which can interfere with the smooth running of the rotor and finally cause vibrations.
- the object of the invention is, therefore, to provide a fastening arrangement for rotor blades with blade roots in peripheral grooves on the rotor of a turbomachine, which arrangement prevents the blade roots from twisting and falling out and, at the same time, ensures a sufficiently large clearance for free thermal expansions.
- the blade roots which are anchored in peripheral grooves, each have, according to the invention, at least one recess or opening which extends in the peripheral direction and in each of which is arranged a connecting piece which connects at least two blade roots to one another to form a blade pack. Thereby the blade roots connected in this way are prevented from twisting.
- a connecting piece consists of a shaped piece of an arbitrary cross section and it is arranged in a recess or opening whose cross section is matched to the shaped piece.
- the recess or opening and the shaped piece are dimensioned in such a way that the shaped piece lies with little clearance in the recess or opening and that a displacement of a blade root and of the shaped piece relative to one another is still possible.
- the rotational freedom of the blade roots about the blade longitudinal axis is reduced by the connection of blade roots to such an extent that they are secured against twisting and falling out.
- Intermediate pieces are fitted between the blade roots in order to partially fill up the assembly gap. They no longer, however, incorporate the function of securing the blade roots against twisting and they do not now need to be so tightly fitted. By this means, free thermal expansion of the blade roots is ensured.
- the connecting piece consists of a shaped piece of rectangular cross section, which is laid into a similarly rectangular recess on the surface of the blade root which faces toward the rotor and bottom of the groove.
- the connecting piece consists of a round wire, which is pushed into a bore opening in the blade root.
- the diameter of the opening and that of the wire are dimensioned in such a way that a displacement of the blade root along the wire is possible.
- each of the blade roots has a recess or opening which extends in the peripheral direction.
- each of the blade roots has two recesses or openings, which extend parallel to one another in the peripheral direction and into each of which a connecting piece is laid or pushed.
- connecting piece In consideration of the thermal expansions of the turbine parts and assembly of the blade roots, various lengths of the connecting piece can be embodied.
- shorter connecting pieces are arranged in the recesses or openings, each of which connecting pieces connects two or more adjacent blade roots together to form a blade pack.
- the root of the last blade is rotated into an assembly gap provided for it in the groove and, to secure it against twisting, is locked to the adjacent blade roots by a final connecting piece, by a connecting piece being pulled into the recess or opening of the last blade root.
- a contact pressure spring is arranged in each recess on the surface of the blade root facing toward the bottom of the groove, which contact pressure spring further reduces a displacement of the blade on the rotor so that a gap formation, and aerodynamic disadvantages resulting from it, are avoided.
- FIG. 1 shows a longitudinal section through a blade root which is anchored in a peripheral groove with a connecting piece according to the invention
- FIG. 2 shows a view II of a plurality of blade roots and an example of securing against twisting by connecting a plurality of adjacent blade roots
- FIG. 3 shows, in the same view as that of FIG. 2, a further example of securing against twisting according to the invention, by connecting a plurality of blade roots,
- FIGS. 4 a - e show, in the same view as that of FIG. 2, a procedure for assembling and locking the last blade root with connecting pieces according to the invention.
- FIG. 1 shows a blade root 1 , which is anchored in an inverted T-shaped peripheral groove 2 in a rotor 3 of a turbomachine.
- the blade root 1 On the surface facing toward the bottom of the groove, the blade root 1 has a recess 4 with a rectangular cross section.
- a connecting piece 5 with a similarly rectangular cross section is laid into the recess with a small clearance.
- the cross section of the recess in the blade root and of the associated connecting piece is, fundamentally, arbitrary. Elliptical or round shapes, for example, can also be embodied instead of the rectangular cross section for the recess and the connecting piece.
- FIG. 2 shows a view II of a plurality of adjacent blade roots 1 , which are anchored in the peripheral groove and which are connected by a connecting piece 5 . They form a pack of blade roots which, because of its larger length, cannot twist in the peripheral groove even if an assembly gap occurs due to displacement of the blade roots during operation.
- the connecting piece therefore ensures securing against twisting and this makes it impossible for the blades to fall out.
- the blade roots along the total periphery of the groove are connected to one another to form a plurality of such blade root packs.
- a connection of almost all the blade roots, with the exception of the last or the last two blades, by means of a single connecting piece can likewise be embodied.
- FIG. 3 shows a plurality of blade roots anchored in a peripheral groove by means of a further arrangement, according to the invention, of connecting pieces.
- the blade roots 1 , 1 a , 1 b , 1 c , 1 d each have two parallel recesses, which are arranged on both sides of the center of the blade root.
- Short connecting pieces 5 a , 5 b , 5 c are laid in both recesses.
- Each connecting piece connects one pair of blade roots, the connecting pieces arranged parallel and adjacent to one another being respectively offset by one blade root.
- a connecting piece 5 a is, for example, laid into the first recess of the two blade roots 1 a and 1 b , connecting them and securing them against twisting.
- a second connecting piece 5 d is laid into the second parallel recess of the blade roots 1 b , 1 c so that it connects this pair of blade roots.
- the next connecting piece 5 c is, in turn, laid into the recess on the first side of the blade roots and connects the blade roots 1 c and 1 d .
- FIGS. 4 a to 4 e The assembly of the last blade of the peripheral groove and the locking of its blade root to the adjacent blade roots by means of the connecting pieces according to the invention is shown in FIGS. 4 a to 4 e .
- FIG. 4 a shows blade roots 11 and 12 , which are located at a distance from the blade roots 13 and 14 due to an assembly gap in the peripheral groove 2 .
- the blade roots 11 and 12 are connected to one another by connecting pieces 5 d and 5 e . They both extend, for example, over a plurality of blade roots.
- the blade roots 13 and 14 are connected to one another and secured by means of connecting pieces 5 f and 5 g .
- FIG. 4 b shows the same peripheral groove 2 with the last blade, whose blade root 15 has been anchored in the assembly gap of the groove 2 .
- the recesses 4 of the blade root 15 are still empty in this case and the blade root is, therefore, not yet secured against twisting.
- the locking of this last blade root takes place as follows, in accordance with FIGS.
- the blade root 12 is first pushed over the remaining gap close to the blade root 15 so that the ends of the connecting pieces 5 d and 5 e become visible.
- the connecting piece 5 d is then pulled in the same direction until its end comes to rest in the recess 4 of the blade root 12 .
- the assembly and locking is completed by the gaps between all the blade roots in the peripheral groove being slightly increased so that the gap which has remained after the assembly of the last blade is distributed over the complete peripheral groove.
- These remaining gaps are filled by means of intermediate pieces. The result is that almost all the blade roots are secured against twisting by two parallel-extending connecting pieces and the remaining blade roots are at least secured by one connecting piece. This ensures that none of the blades can twist and fall out of the groove.
- the intermediate pieces are a known component and are not shown here. They are dimensioned in such a way that they reduce the assembly clearance and, during operation of the turbine, no larger gap can form which could interfere with the smooth-running of the rotor. Because of the arrangement for securing against twisting, however, they no longer need to fill the assembly clearance completely, so that a sufficiently large free space, in which thermal expansions can be freely ensured, remains between the blade roots.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00810175A EP1130217B1 (fr) | 2000-03-01 | 2000-03-01 | Fixation des aubes dans une turbomachine |
EP00810175.0 | 2000-03-01 |
Publications (1)
Publication Number | Publication Date |
---|---|
US20010019697A1 true US20010019697A1 (en) | 2001-09-06 |
Family
ID=8174578
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/794,050 Abandoned US20010019697A1 (en) | 2000-03-01 | 2001-02-28 | Fastening rotor blades in a turbomachine |
Country Status (3)
Country | Link |
---|---|
US (1) | US20010019697A1 (fr) |
EP (1) | EP1130217B1 (fr) |
DE (1) | DE50010348D1 (fr) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2005010323A1 (fr) * | 2003-07-26 | 2005-02-03 | Alstom Technology Ltd | Systeme de fixation des emplantures d'aubes d'une turbomachine |
US20090087316A1 (en) * | 2007-10-01 | 2009-04-02 | Thomas Mueller | Rotor blade, method for producing a rotor blade, and compressor with a rotor blade |
US20090086700A1 (en) * | 2003-10-02 | 2009-04-02 | Qualcomm Incorporated | Systems and methods for communicating control data using multiple slot formats |
US20110110785A1 (en) * | 2009-11-10 | 2011-05-12 | Alstom Technology Ltd | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
US20110200441A1 (en) * | 2009-12-07 | 2011-08-18 | David Paul Blatchford | Turbine assembly |
JP2014527594A (ja) * | 2011-08-24 | 2014-10-16 | シーメンス アクティエンゲゼルシャフト | 翼構造体 |
US9382805B2 (en) | 2012-02-27 | 2016-07-05 | Rolls-Royce Plc | Balancing of rotors |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1707746A1 (fr) * | 2005-03-18 | 2006-10-04 | Siemens Aktiengesellschaft | Composant de turbomachine, turbomachine et procédé de fixation d'aubes sur un composant |
CH702203A1 (de) * | 2009-11-10 | 2011-05-13 | Alstom Technology Ltd | Rotor für eine axial durchströmte turbomaschine sowie laufschaufel für einen solchen rotor. |
US11773750B2 (en) * | 2022-01-05 | 2023-10-03 | General Electric Company | Turbomachine component retention |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE459203C (de) * | 1928-04-27 | E H Hans Holzwarth Dr Ing | Einrichtung zur Schaufelbefestigung fuer Dampf- und Gasturbinen | |
DE333353C (de) * | 1920-04-16 | 1921-03-18 | Osthoff Fa Walter | Gewebe-Gassengmaschine |
GB614678A (en) * | 1946-07-19 | 1948-12-20 | Parsons C A & Co Ltd | Improvements in or relating to turbine blading or the like |
US2809801A (en) * | 1952-04-18 | 1957-10-15 | Ingersoll Rand Co | Turbine rotor construction |
CH494341A (de) * | 1968-07-26 | 1970-07-31 | Sulzer Ag | Rotor für Turbomaschinen |
FR2680828A1 (fr) * | 1991-08-28 | 1993-03-05 | Sev Motorola | Rotor de turbomachine a positionnement angulaire ameliore des aubes. |
US5509784A (en) * | 1994-07-27 | 1996-04-23 | General Electric Co. | Turbine bucket and wheel assembly with integral bucket shroud |
-
2000
- 2000-03-01 DE DE50010348T patent/DE50010348D1/de not_active Expired - Lifetime
- 2000-03-01 EP EP00810175A patent/EP1130217B1/fr not_active Expired - Lifetime
-
2001
- 2001-02-28 US US09/794,050 patent/US20010019697A1/en not_active Abandoned
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2005010323A1 (fr) * | 2003-07-26 | 2005-02-03 | Alstom Technology Ltd | Systeme de fixation des emplantures d'aubes d'une turbomachine |
US8023474B2 (en) | 2003-10-02 | 2011-09-20 | Qualcomm Incorporated | Systems and methods for communicating control data using multiple slot formats |
US20090086700A1 (en) * | 2003-10-02 | 2009-04-02 | Qualcomm Incorporated | Systems and methods for communicating control data using multiple slot formats |
US20090087316A1 (en) * | 2007-10-01 | 2009-04-02 | Thomas Mueller | Rotor blade, method for producing a rotor blade, and compressor with a rotor blade |
US8257047B2 (en) * | 2007-10-01 | 2012-09-04 | Alstom Technology Ltd. | Rotor blade, method for producing a rotor blade, and compressor with a rotor blade |
US20110110785A1 (en) * | 2009-11-10 | 2011-05-12 | Alstom Technology Ltd | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
JP2011102586A (ja) * | 2009-11-10 | 2011-05-26 | Alstom Technology Ltd | 軸流ターボ機械のためのロータ及びロータのための動翼 |
US8770938B2 (en) | 2009-11-10 | 2014-07-08 | Alstom Technology Ltd | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
US20110200441A1 (en) * | 2009-12-07 | 2011-08-18 | David Paul Blatchford | Turbine assembly |
US8851852B2 (en) * | 2009-12-07 | 2014-10-07 | Alstom Technology Ltd. | Turbine assembly |
JP2014527594A (ja) * | 2011-08-24 | 2014-10-16 | シーメンス アクティエンゲゼルシャフト | 翼構造体 |
US9708919B2 (en) | 2011-08-24 | 2017-07-18 | Siemens Aktiengesellschaft | Blade arrangement |
US9382805B2 (en) | 2012-02-27 | 2016-07-05 | Rolls-Royce Plc | Balancing of rotors |
Also Published As
Publication number | Publication date |
---|---|
EP1130217A1 (fr) | 2001-09-05 |
EP1130217B1 (fr) | 2005-05-18 |
DE50010348D1 (de) | 2005-06-23 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US6726452B2 (en) | Turbine blade arrangement | |
US8951015B2 (en) | Rotor blade arrangement and gas turbine | |
US20010019697A1 (en) | Fastening rotor blades in a turbomachine | |
US5509784A (en) | Turbine bucket and wheel assembly with integral bucket shroud | |
US6561764B1 (en) | Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms | |
US8622708B2 (en) | Stator blade for a turbomachine which is exposable to axial throughflow, and also stator blade arrangement for it | |
US8246309B2 (en) | Rotor disk for turbomachine fan | |
US4260331A (en) | Root attachment for a gas turbine engine blade | |
US8257046B2 (en) | Turbine rotor blade, turbine rotor and steam turbine equipped with the same | |
EP1452692B1 (fr) | Aiguille d'amortisation pour aubes de turbine | |
US5242270A (en) | Platform motion restraints for freestanding turbine blades | |
EP0280246B1 (fr) | Montage des aubes dans les turbines à vapeur | |
US8851852B2 (en) | Turbine assembly | |
US20090290983A1 (en) | Turbine blade assembly and steam turbine | |
CA2613595A1 (fr) | Rotor pour une turbine et procede et dispositif pour produire ce rotor | |
US6830435B2 (en) | Fastening of the blades of a compression machine | |
EP2322761B1 (fr) | Roue aubagée de rotor | |
KR100936566B1 (ko) | 터빈의 고정 블레이드를 설치하는 방법 및 터빈 구조체 | |
JPH05248205A (ja) | 衝動蒸気タービン用ドラム形ロータ | |
US6299411B1 (en) | Fastening of moving blades of a fluid-flow machine | |
CA1297799C (fr) | Groupe de pales pour etage de commande a entree laterale | |
US6261058B1 (en) | Stationary blade of integrated segment construction and manufacturing method therefor | |
CA1279827C (fr) | Dispositif et methode pour reduire les jeux et les fuites dans une turbine a vapeur garnie d'une aube axial d'entree | |
JPS63170504A (ja) | タービン羽根の取付方法及び保護装置 | |
EP1965026A2 (fr) | Aubage dans une turbine à gaz |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AS | Assignment |
Owner name: ALSTOM POWER N.V., NETHERLANDS Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MUELLER, MICHAEL;PROSS, JORG;KNORR, MANFRED;REEL/FRAME:011580/0979 Effective date: 20010202 |
|
AS | Assignment |
Owner name: ALSTOM (SWITZERLAND) LTD, SWITZERLAND Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:ALSTOM POWER N.V.;REEL/FRAME:013016/0007 Effective date: 20020527 |
|
STCB | Information on status: application discontinuation |
Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION |