EP1697618A1 - Strömungsmaschine mit einem leitschaufelträger und verfahren zum montieren von leitschaufeln an einen leitschaufelträger - Google Patents
Strömungsmaschine mit einem leitschaufelträger und verfahren zum montieren von leitschaufeln an einen leitschaufelträgerInfo
- Publication number
- EP1697618A1 EP1697618A1 EP04797660A EP04797660A EP1697618A1 EP 1697618 A1 EP1697618 A1 EP 1697618A1 EP 04797660 A EP04797660 A EP 04797660A EP 04797660 A EP04797660 A EP 04797660A EP 1697618 A1 EP1697618 A1 EP 1697618A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide vane
- guide
- groove
- vanes
- press
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
Definitions
- the invention relates to a turbomachine, in particular a compressor, to an annular guide vane carrier for a turbomachine for fastening guide vanes according to the preamble of claim 10, and to a method for mounting guide vanes on an annular guide vane carrier of a turbomachine according to the preamble of Claim 11.
- Gas turbines coupled to generators are used to convert fossil energy into electrical energy.
- a gas turbine has a compressor, a combustion chamber and a turbine unit along its rotor shaft in the direction of flow of the gases.
- the compressor sucks in ambient air and compresses it.
- the compressor air is then mixed with a fuel and fed to the combustion chamber.
- There the mixture burns to a hot gaseous working medium and flows into the turbine unit with blades.
- the guide vanes attached to the housing of the turbine unit direct the working medium onto the rotor blades attached to the rotor, so that they set the rotor into a rotary movement.
- the rotational energy of the rotor absorbed in this way is converted into electrical energy by the generator coupled to the rotor. It is also used to drive the compressor.
- DE 44 36 731 discloses a compressor with a guide vane carrier designed as a housing for holding free-standing guide vanes.
- a circumferential groove with undercuts is provided on the inside of the guide vane carrier.
- the housing is divided into two halves, so that when the housing is open, the guide vanes can be inserted into the divided circumferential groove for assembly and moved along this. Furthermore, it is described that intermediate pieces provided between the guide show are fixed by inserted documents.
- the circumferential groove and the complementary guide vane feet of the guide vanes are inserted with radial play in the circumferential groove.
- the radial play of the free-standing guide vanes can, however, lead to flow losses in the air to be compressed.
- the object of the invention is to provide a turbomachine, in particular a compressor, with reduced flow losses. Furthermore, it is the object of the invention to provide a guide vane carrier and a method for mounting guide vanes on an annular guide vane carrier of a turbomachine.
- the solution to the problem directed to the turbomachine designed according to the preamble of claim 1 provides that the contact area and the support area are aligned in the radial direction of the rotor for each guide vane.
- the invention is based on the knowledge that at least one press segment is assigned to each guide vane or each guide vane root.
- a groove-shaped recess is provided in the groove base of the circumferential groove for receiving a press segment.
- the press segments In the assembled state, the press segments generate a prestress, which presses the guide vane foot against the undercuts of the circumferential groove, so that the guide vane has a firm and secure fit without play.
- each press segment is supported in a support area in the recess and presses the guide blade foot against the undercut via a contact area that is radially aligned therewith.
- a resilient mounting of the guide vanes as is known for example from the aforementioned US 998,820, is specifically avoided here.
- press segments ensure that no costly manual adjustment work is required when installing the guide vanes. Comparatively large tolerances of the circumferential groove and the guide vane feet are possible in a cost-reducing manner.
- press segments arranged in a recess form a press segment ring adjacent to one another in the circumferential direction, then all press segments can be of the same design and simply pushed one after the other for assembly. This reduces the manufacturing and assembly costs.
- a simple assembly of a guide vane can be achieved if each press segment comprises at least two sections in the circumferential direction, one of the sections having an excess in the radial direction to form the prestress.
- the guide vane foot is moved into an operating position via a press segment that is already provided in the recess. Since the guide vane or its platform can be wider than the guide vane root in the circumferential direction. it makes sense to provide the excess only in the section of the press segment that contacts the guide vane foot in the operating position.
- the remaining section or sections of the press segment serve in the circumferential direction as a stop surface for subsequently installed press segments which are then in the correct operating position.
- the recess expediently has an inner support region as a counter bearing, on which the press segment is supported. The excess is slightly larger than the distance from the guide vane foot to the inner support area.
- a displacement in the circumferential direction of the assembled guide vanes is prevented if at least one sealing element in the guide vane ring secures a guide vane against a displacement in the circumferential direction.
- platform elements are provided between two adjacent guide blades of a guide blade ring.
- the guide vane foot can be made more compact and narrow, so that manufacturing processes such as forging or milling are possible with little material input per raw part.
- the platform element can also be made of a cheaper material, such as ST37, when the guide vane is manufactured.
- the turbomachine is preferably a compressor.
- turbomachine also apply to the guide vane carrier and the process.
- FIG. 1 shows a section through a guide vane carrier with a guide vane
- FIG. 2 shows a section through a guide vane carrier according to II-II
- FIG. 3 shows a section through a guide vane carrier according to section III-III
- FIG. 4 shows a press segment
- FIG. 5 shows a partial longitudinal section through a gas turbine.
- FIG. 5 shows a gas turbine 1 in a partial longitudinal section. Inside, it has a rotor 3 which is rotatably mounted about an axis of rotation 2 and is also referred to as a turbine rotor or rotor shaft.
- An intake housing 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of coaxially arranged burners 7, a turbine 8 and the exhaust gas housing 9 follow one another along the rotor 3.
- annular compressor channel 10 is provided, which in the direction of the annular combustion chamber 6 in the transverse cut tapered.
- a diffuser 11 is arranged, which is in flow connection with the annular combustion chamber 6.
- the annular combustion chamber 6 forms a combustion chamber 12 for a mixture of a fuel and compressed air.
- a hot gas duct 13 arranged in the turbine 8 is in flow communication with the combustion chamber 12, the exhaust gas housing 9 being arranged downstream of the hot gas duct 13.
- Blade rings are alternately arranged in the compressor duct 10 and in the hot gas duct 13. This is followed by a guide vane ring 15 formed from guide vanes 14 and a rotor vane ring 17 formed from guide vanes 16.
- the fixed guide vanes 14 are connected to a guide vane carrier 18, whereas the guide vanes 16 are connected to the rotor 3 by means of a disk 19.
- air is drawn in by the compressor 5 through the suction housing 4 and compressed in the compressor duct 10.
- An air L provided at the burner end of the compressor 5 is guided through the diffuser 11 to the burners 7 and mixed there with a fuel.
- the mixture is then burned to form a working fluid 20 in the combustion chamber 12. From there, the working fluid 20 flows into the hot gas duct 13.
- the working fluid 20 relaxes in a pulse-transmitting manner on the guide vanes 14 arranged in the turbine 8 and on the moving blades 16, so that the rotor 3 is driven and with it a working machine coupled to it (not shown).
- the annular guide vane carrier 18 has an inner circumferential groove 21 on its wall facing the compressor duct 10.
- two groove-shaped recesses 26 are also arranged can also be designed as further circumferential grooves. The recesses 26 protrude with a radial depth into the guide vane ger 18 that is greater than the width B of its opening in the groove base 25.
- the guide vane 14 extends with its guide vane foot 27 into the circumferential groove 21.
- the guide vane root 27 is complementary to the undercuts 24 of the circumferential groove 21, that is to say T-shaped, so that the guide vane 14 is held in the circumferential groove 21.
- a platform 29 which delimits the compressor duct 10 radially outward and from which the free-standing airfoil profile 28 extends into the compressor duct 10.
- Press segments 30 are arranged in the recesses 26 and press the guide vane root 27 against the projections 23 of the circumferential groove 21 with a prestress.
- FIG. 2 shows the guide vane carrier 18 and the guide vane 14 according to section II-II of FIG. 1.
- a platform element 32 is provided which delimits the compressor duct 10 radially outward.
- the platform element 32 is hooked into the circumferential groove 21 analogously to a guide vane foot 27.
- the press segment 30 lies against the support wall 40 with a support region 31. Radially further inward, the pressing segment 30 has, in a first section 34 (FIG. 4), on its side facing the guide vane foot 27, a contact area 33 which bears against the guide vane foot 27 and presses it against the projections 23 / support area 31 and contact area 33 for each Guide vane (14, 16) on a radius and aligned. In a second section 35 (FIG. 4) there is a surface 36 which springs back with respect to the contact area 33 Facing platform element 32. In the operating position, the surface 36 is opposite to the back of a platform element 32 adjacent to the guide vane 14 without contact or with only a comparatively low pretension.
- Fig. 3 shows a section through Fig. 1 according to the section plane III-III.
- the platform element 32 is arranged between two guide blades 14.
- the circumferential groove 21 extends in the circumferential direction U, the undercuts 24 being shown on the side walls 22 thereof.
- In the bottom of the groove 25 there are two recesses 26 with support walls 40.
- a press segment 30 is arranged, the surface 36 of which is shown.
- the platform element 32 has a recess 37 on an end face facing the guide vane 14, into which a tool can be inserted with a lever in order to push the guide vane 14 toward the surface 36 for disassembly from the contact area 33 and thus to release it.
- every third platform element 32 can be fixed by a securing element 38, which is introduced into a further recess 39 on the side of the guide vane 14 facing away from the flow become.
- the press segments 30 and securing elements 38 are located between the guide vane carrier 18 and the guide vanes 14 or the platform elements 32, so that they cannot get into the compressor duct 10.
- FIG. 4 shows the press segment 30 with the first section 34 and the second section 35.
- the contact area 33 is spaced apart from the opposite support area 31 by a distance Bi.
- the surface 36 to the opposite rear is in another Distance B 2 spaced.
- the distance B x is greater than the distance B 2 .
- the curvature of the press segment 30 in the circumferential direction is not shown here.
- the distance B x corresponds to a distance S (Fig.l), which is measured between the support region 31 and the guide vane root, plus an excess of approximately 0.3 mm.
- the section 35 without oversize, on the other hand, has a distance B 2 which can approximately correspond to the distance S.
- a press segment 30 is first introduced into each groove-shaped recess 26.
- Either the guide vane 14 can then be introduced by radially moving it into the circumferential groove 21 with subsequent turning, so that the door-shaped projections provided on the guide vane foot 27 engage behind the undercut 24. Or they are inserted into the circumferential groove 21 if it has a suitable opening, such as the parting joint of the housing.
- the guide vane 14 is then displaced in the direction of the free press segments 30 until the guide vane foot 27 covers the surface 36 of the press segments 30 and abuts the protruding contact area 33.
- the guide vane 14 can now be pushed over the contact area 33 with a tool and with increased effort until the guide vane foot 27 completely covers the contact area 33. Part of the excess is rubbed off by the guide vane foot 27. The prestress prevailing in the press segment 30 then presses the guide vane foot 27 from the outside against the undercut 24 of the circumferential groove 21. The guide vane 14 is thus in a safe and predetermined position.
- a construction without platform elements 32 is also conceivable if the platforms 29 of the guide vanes 14 are designed so wide in the circumferential direction U that they fill the space bridged by the platform elements 32.
- the press segments 30 remain unchanged.
- the pressing segments 30 ensure that no costly manual adaptation work is required when installing the guide vanes 14. Furthermore, the circumferential groove 21 and the guide vane feet 27 can be produced with comparatively large tolerances.
- the platform elements 32 as well as the press segments 30 can be made from the inexpensive material ST37.
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 (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04797660A EP1697618B1 (de) | 2003-12-23 | 2004-11-05 | Leitschaufelträger mit mehreren leitschaufeln und verfahren zum montieren von leitschaufeln an einen leitschaufelträger |
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03029771A EP1548232A1 (de) | 2003-12-23 | 2003-12-23 | Strömungsmaschine mit einem Leitschaufelträger und Verfahren zum Montieren von Leitschaufeln an einen Leitschaufelträger |
EP04797660A EP1697618B1 (de) | 2003-12-23 | 2004-11-05 | Leitschaufelträger mit mehreren leitschaufeln und verfahren zum montieren von leitschaufeln an einen leitschaufelträger |
PCT/EP2004/012553 WO2005066463A1 (de) | 2003-12-23 | 2004-11-05 | Strömungsmaschine mit einem leitschaufelträger und verfahren zum montieren von leitschaufeln an einen leitschaufelträger |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1697618A1 true EP1697618A1 (de) | 2006-09-06 |
EP1697618B1 EP1697618B1 (de) | 2012-12-26 |
Family
ID=34530723
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03029771A Withdrawn EP1548232A1 (de) | 2003-12-23 | 2003-12-23 | Strömungsmaschine mit einem Leitschaufelträger und Verfahren zum Montieren von Leitschaufeln an einen Leitschaufelträger |
EP04797660A Not-in-force EP1697618B1 (de) | 2003-12-23 | 2004-11-05 | Leitschaufelträger mit mehreren leitschaufeln und verfahren zum montieren von leitschaufeln an einen leitschaufelträger |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03029771A Withdrawn EP1548232A1 (de) | 2003-12-23 | 2003-12-23 | Strömungsmaschine mit einem Leitschaufelträger und Verfahren zum Montieren von Leitschaufeln an einen Leitschaufelträger |
Country Status (2)
Country | Link |
---|---|
EP (2) | EP1548232A1 (de) |
WO (1) | WO2005066463A1 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7806655B2 (en) * | 2007-02-27 | 2010-10-05 | General Electric Company | Method and apparatus for assembling blade shims |
US8047778B2 (en) * | 2009-01-06 | 2011-11-01 | General Electric Company | Method and apparatus for insuring proper installation of stators in a compressor case |
US8133019B2 (en) * | 2009-01-21 | 2012-03-13 | General Electric Company | Discrete load fins for individual stator vanes |
CH703997A1 (de) * | 2010-10-27 | 2012-04-30 | Alstom Technology Ltd | Schaufelanordnung, insbesondere Leitschaufelanordnung. |
EP2679776A1 (de) * | 2012-06-28 | 2014-01-01 | Alstom Technology Ltd | Kühlsystem und Verfahren für eine Axialturbine |
EP2851515A1 (de) * | 2013-09-24 | 2015-03-25 | Siemens Aktiengesellschaft | Anordnung zur Befestigung von Turbinenschaufeln |
US9388704B2 (en) * | 2013-11-13 | 2016-07-12 | Siemens Energy, Inc. | Vane array with one or more non-integral platforms |
EP2995775A1 (de) * | 2014-09-15 | 2016-03-16 | Siemens Aktiengesellschaft | Vorrichtung zum Eintreiben einer Leitschaufel in eine Schaufelnut |
FR3048719B1 (fr) * | 2016-03-14 | 2018-03-02 | Safran Aircraft Engines | Redresseur de flux pour turbomachine avec plateformes integrees et rapportees |
US11125092B2 (en) * | 2018-08-14 | 2021-09-21 | Raytheon Technologies Corporation | Gas turbine engine having cantilevered stators |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US998820A (en) * | 1908-05-13 | 1911-07-25 | George Westinghouse | Turbine-blading. |
GB216737A (en) * | 1923-08-02 | 1924-06-05 | Karl Baumann | Improvements relating to elastic fluid turbines |
DE518106C (de) * | 1924-02-18 | 1931-02-24 | Jan Kieswetter | Einrichtung zum Ausgleich verschiedener Waermeausdehnungen zwischen einer aeusseren Gehaeusewand und einer Zwischenwand des gleichen Gehaeuses, insbesondere bei Dampf- oder Gasturbinen |
CH482915A (de) * | 1967-11-03 | 1969-12-15 | Sulzer Ag | Leitvorrichtung für Axialturbine |
IT1062412B (it) * | 1976-06-15 | 1984-10-10 | Nuovo Pignone Spa | Sistema perfezionato di bloccaggio in posizione delle pale sulla casca statorica di un compressore assiale operante in ambiente pulverulento |
US5205708A (en) * | 1992-02-07 | 1993-04-27 | General Electric Company | High pressure turbine component interference fit up |
DE4436731A1 (de) * | 1994-10-14 | 1996-04-18 | Abb Management Ag | Verdichter |
-
2003
- 2003-12-23 EP EP03029771A patent/EP1548232A1/de not_active Withdrawn
-
2004
- 2004-11-05 EP EP04797660A patent/EP1697618B1/de not_active Not-in-force
- 2004-11-05 WO PCT/EP2004/012553 patent/WO2005066463A1/de not_active Application Discontinuation
Non-Patent Citations (1)
Title |
---|
See references of WO2005066463A1 * |
Also Published As
Publication number | Publication date |
---|---|
EP1548232A1 (de) | 2005-06-29 |
EP1697618B1 (de) | 2012-12-26 |
WO2005066463A1 (de) | 2005-07-21 |
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