WO2005095829A1 - Lamellendichtung, insbesondere für eine gasturbine, sowie verfahren zu deren herstellung - Google Patents
Lamellendichtung, insbesondere für eine gasturbine, sowie verfahren zu deren herstellung Download PDFInfo
- Publication number
- WO2005095829A1 WO2005095829A1 PCT/EP2005/051351 EP2005051351W WO2005095829A1 WO 2005095829 A1 WO2005095829 A1 WO 2005095829A1 EP 2005051351 W EP2005051351 W EP 2005051351W WO 2005095829 A1 WO2005095829 A1 WO 2005095829A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- brazing
- lamellae
- hard
- seal
- foils
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/32—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings
- F16J15/3284—Sealings between relatively-moving surfaces with elastic sealings, e.g. O-rings characterised by their structure; Selection of materials
- F16J15/3292—Lamellar structures
Definitions
- the present invention relates to the field of rotary machine sealing. It relates to a lamellar seal according to the preamble of claim 1 and a method for producing such a lamellar seal.
- a gas turbine consists of a rotor, on which various stages with compressor blades and turbine blades are attached, and a stator housing.
- the rotor is mounted in bearings at each end of the rotor shaft. Controlling the gas flow within the gas turbine is of paramount importance in terms of both functionality and effectiveness. Sealing technologies are used at various locations along the rotor shaft to reduce the axial gas flow along the shaft. This is particularly important alongside the bearings to prevent the oil used in the bearings from overheating due to the hot gases in the gas stream.
- Labyrinth seals have no metal-to-metal contact between the rotor and the stator; therefore their sealing effect is relatively small. However, they offer the advantage of low rotational friction and therefore practically unlimited service life.
- Brush seals on the other hand, have higher friction losses due to the friction between the bristle ends and the rotor shaft. This results in wear that limits the life of the seal.
- brush seals offer better inhibition of the axial gas flow, especially with higher axial pressure differences.
- the basic design involves a number of thin metal fins, which have a controlled air gap between them and are attached at a predetermined angle to the radius.
- the air gap is a critical one
- Design parameters It enables the occurrence of an air flow in order to produce the hydrodynamic effect; however, it must not be so large as to allow excessive axial leakage current.
- the lamella seal design Two variants of the lamella seal design are possible: in one variant the lamellae are blown downwards, in the other one upwards.
- the variant with the fins blown down includes that there is a distance between the lamella tips and the shaft during assembly and start-up, and that this gap is reduced to very small values by the use of an air flow between the lamellae.
- the variant with the upward blowing includes that during the start-up there is a slight mutual influence between the lamella tips and the shaft, and a distance is generated when the shaft accelerates. In both cases, the flow of the medium through the air gaps between the fins is critical, as is the control of the inner diameter of the seal created by the fin tips.
- the air flow through the fins can be altered by using a front and a rear plate that leave a narrow gap between the surfaces of the plate pack and the plates (see Figures 1 and 3 above). Careful design of these geometries makes it possible to control the upward or downward blowing effects. It may also be desirable to assist the downward blowing effect by actively applying pressure along the length of the fins or inwards from the front or from the rear directions.
- One of the other main advantages of the lamellar seal concept is a greater tolerance of the radial movement than with the labyrinth or brush seals. This requires a large distance between the inner diameter of the front and rear plates and the shaft.
- the number of lamellas can be a few thousand or tens of thousands.
- the accuracy with which these can be manufactured, assembled and connected, ensuring a reproducible air gap between each pair of fins is critical to the successful implementation of any possible seal design.
- the joining process for fixing the fins in position could be a mechanical technique such as clamping, welding or brazing or any combination thereof. It is obviously important that there is minimal disruption to the lamellas or their relative positions during the joining process.
- the object is achieved by the entirety of the features of claims 1 and 6.
- the essence of the invention is to connect the lamellae by interposed brazing foils, which are also used as spacer elements. This ensures secure connections between the slats while maintaining a precise distance.
- the distance between adjacent lamellae is preferably essentially determined by the thickness of the brazing foil lying therebetween.
- the brazing foils consist of an alloy which has a relatively large melting interval, preferably more than 50 ° C. Large melting intervals result in lower requirements for maintaining the optimal soldering temperatures. This is crucial in order to make the process robust and to ensure constant quality of the end product.
- the lamellae consist of a material that remains firm beyond the melting interval of the brazing foils.
- connection or brazing process can be carried out in a simple manner by precisely setting and keeping the soldering temperature constant.
- a preferred embodiment of the method according to the invention is characterized in that brazing foils made of an alloy are used, which have a melting interval between a solidus temperature and a liquidus temperature, and that the predetermined heating temperature is only slightly above the solidus temperature of the brazing foil.
- the distance between the lamellae can be adjusted particularly precisely if the brazing foils used as spacer elements are produced by a precision metal foil cutting or stamping method, in particular by means of a wire erosion method or photochemical processing method.
- 1 is a perspective side view of the typical structure of a lamellar seal, as used in a gas turbine: 2 shows a side view in the axial direction of the arrangement of individual lamellae inclined from the radial direction with their spacing elements in between;
- FIG. 3 shows the view of a lamella seal comparable to FIG. 1 in the circumferential direction with a front and rear end plate;
- FIG. 5 shows the detail from a conventional configuration for brazing the fins (and spacer elements) of a finned seal
- FIG. 6 shows the final state of the lamellar seal resulting from the configuration according to FIG. 5;
- FIG. 8 shows a recording, comparable to FIG. 7, of a hard soldering carried out at an optimal soldering temperature just above the solidus temperature according to the invention.
- FIG. 1 shows a perspective side view of the typical structure of a lamella seal, as used in a gas turbine.
- the Lamella seal 12 seals a rotor shaft 11 of the gas turbine 10 rotating in the direction of the arrow against a housing 14.
- a packet of thinly spaced thin fins 13 is arranged in a ring.
- the surface of the slats 13 is oriented parallel to the axis of rotation of the machine. 2, the slats are tilted from the radial direction by an angle w1 and each have a narrow gap or space 18 between them, which is preferably defined by spacer elements 17 arranged between the slats 13.
- FIGS. 7 and 8 each show the situation in which the spacer elements are made from brazing foil 22 and placed between the lamellae 13. 1 and 3, the air flow through the fins 13 can be changed by using a front and a rear end plate 15 or 16, which leave a narrow gap between the surfaces of the plate pack and the end plates 15, 16 free (distances a and b in Fig. 3). Careful design of these geometries makes it possible to control the upward or downward blowing effects mentioned at the beginning. It may also be desirable to assist the downward blowing effect by actively applying pressure along the length of the fins or inwards from the front or from the rear directions.
- One of the other main advantages of the lamella seal concept shown in FIGS. 1 and 3 is a greater tolerance of the radial movement than in the case of the labyrinth or brush seals. This requires a large distance between the inner diameter of the front and rear end plates 15, 16 and the rotor shaft 11 (distances c and d in Fig. 3). The gap between the fins 13 and the rotor shaft (distance e in Fig. 3) is only a few microns.
- the present invention relates to the connection process within the manufacture of lamellar seals. In principle, however, it could also be used in other similar connection applications where it Difficulty getting the braze to flow to the right places.
- the lamellas for lamellar seals are usually between 20 and 200 ⁇ m in thickness, and the air gaps between the lamellas are typically of the same order of magnitude.
- the connection of such a structure is achieved by the flow of liquid solder material between the fins.
- the capillary forces underlying this process are sensitive to the gap width, the flow of the solder is difficult to control.
- FIGS. 5 and 6 In the two figures, diagonally arranged lamellae 13 of a lamella seal are shown, which are spaced apart by spacer elements 17 and therefore have gaps G1 (typically 50 ⁇ m). Due to the circular shape of the lamellar seal, wedge-shaped gaps G2 (in the order of 5-10 ⁇ m) between the spacer elements 17 and lamellae 13, which reach down to the metal-metal contacts 24, result in the case of lamellae 13 and spacer elements 17 of constant thickness. If the lamellae 13 and spacer elements 17 are to be brazed to one another in the position shown, a brazing foil (or paste) 20 is placed on the outside in the conventional soldering method (FIG. 5).
- a brazing foil (or paste) 20 is placed on the outside in the conventional soldering method (FIG. 5).
- the brazing material of the brazing foil 20 starts the joining process far from the surfaces to be joined, and only reaches its final position by a capillary flow due to the surface tension in the gap G2, where it then creates the connection as a solidified brazing agent 21 (FIG. 6 ).
- the problem with the geometry of the lamellar seal is that the surfaces to be joined are too close to each other for the conventional brazing technique to allow the liquid brazing material to penetrate. Getting a good, strong braze joint in the right place can be difficult.
- the lamellas must keep an air gap (G) that extends down most of their length. This air gap is usually in the optimal range for the capillary forces around the braze implicate. Should this gap be filled with liquid solder alloy, this would be fatal for the lamellar seal.
- the procedure includes the alternating composition of the lamellae 13 and separate spacer elements 17, as well as a source of a brazing alloy (brazing foil 20) placed nearby, which is ready to flow to the corresponding points when it melts. It is clear that a similar effect can be achieved with lamella components that have a thickened section that acts as an integral spacer, although less solder alloy would be needed to achieve a connection.
- the braze alloy would have to begin the path to its desired final position by flowing through a gap (G2) with a width of 5 to 10 ⁇ m, which then decreases to zero (for the metal-metal contact 24). If it comes up to that point, namely to the metal-metal contact points of the slats 13 and spacer elements 17, it must stop before it flows down into the air gap (G1). It is essential for the functionality of the lamellar seal that the air gap is not filled with solder.
- brazing alloys assume optimal soldering gaps between 10 - 150 ⁇ m. The best one can hope for under these circumstances is that the liquid braze begins to flow into the G2 gap between the fins 13 and the spacers 17, which are usually between 5 and 10 microns. It is difficult to guarantee that the solder will flow in until the end of the gap, even under the best possible wetting conditions. On the other hand, the air gap (G1) between the fins is usually in the middle of the optimal range, so it is also difficult to ensure that the liquid solder does not flow into it. Brazing alloys are still often similar to the alloys (the fins) that they are supposed to join, except that they are alloyed with melting point suppressing elements such as boron or silicon. These additives give the alloy the desired melting properties.
- a pure metal After heating, a pure metal begins to melt at its melting temperature, and any increase in the rate of heat input will only result in an increased rate of melting, not an increase in temperature. After all, all of the metal is liquid, and only then does the temperature of the liquid metal begin to increase further. Pure metals have well-defined, isothermal melting points. Most alloys, on the other hand, melt over a temperature range (melting interval). After this
- the alloy When heated, the alloy begins to melt at a temperature known as the solidus temperature. At this point the amount of liquid metal present is infinitesimal, but it remains in equilibrium with the solid metal around it as long as there is no change in temperature (or in the composition of the alloy). After further heating, the temperature of the semi-liquid alloy increases, as does the proportion of the liquid that is in equilibrium with the solid material. This continues until the whole alloy is liquid, which happens at the liquidus temperature; then the temperature rises in the same way as for a pure metal.
- DTA differential thermal analysis
- Heat flow is a sign that either an endothermic or an exothermic reaction takes place.
- An example of a commercial Ni-based brazing alloy is shown in Figure 4.
- the ratio of solid parts to liquid parts remains the same if the alloy is kept at a constant temperature. In theory, this condition will continue indefinitely, provided that the composition of the alloy does not change due to diffusion or any volatilization mechanisms.
- a change in temperature within the limits of the solidus-liquidus range (melting interval) changes the ratio of solid to liquid. This is the basis of the present invention.
- Alternating layers of fins and spacer elements are assembled analogously to FIG. 2 into a suitable tensioning device (not shown) which can withstand the temperatures of the brazing process.
- the spacers consist of the brazing alloy itself. It is crucial that the spacer maintain its thickness in order to provide an air gap (G1 in Fig. 5) between the fins. At the same time, however, sufficient liquid metal must be generated to ensure a secure metallurgical bond between adjacent lamellae. In this regard, temperature control is obviously particularly critical.
- using a braze alloy with a wide melting range can help reduce sensitivity to temperature changes. In the case of the DTA curve shown above, the melting range is, for example, over 90 ° C. Brazing alloys with a melting interval> 50 ° C are preferred.
- Precise control of the position and the amount of the brazing alloy can be achieved by using a precision cutting process for metal foils such as wire erosion or photochemical processing to form the brazing alloy.
- Photographs are shown in Figures 7 and 8 to show the results of the brazing process of the invention applied to lamellar seals. Viewed from the side, fins 25 are shown here, which are connected to one another by brazing foils 22 and are spaced apart from one another. In Fig. 7 the soldering temperature was higher and thus closer to the conventional soldering temperature.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Sealing Material Composition (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP05717137A EP1730428B1 (de) | 2004-03-30 | 2005-03-23 | Lamellendichtung, insbesondere für eine gasturbine, sowie verfahren zu deren herstellung |
DE502005001024T DE502005001024D1 (de) | 2004-03-30 | 2005-03-23 | Lamellendichtung, insbesondere für eine gasturbine, sowie verfahren zu deren herstellung |
CA2561842A CA2561842C (en) | 2004-03-30 | 2005-03-23 | Leaf seal, in particular for a gas turbine, and method of producing it |
US11/537,211 US8220802B2 (en) | 2004-03-30 | 2006-09-29 | Leaf seal, in particular for a gas turbine, and method of producing it |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004016173A DE102004016173A1 (de) | 2004-03-30 | 2004-03-30 | Lamellendichtung, insbesondere für eine Gasturbine, sowie Verfahren zu deren Herstellung |
DE102004016173.9 | 2004-03-30 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US11/537,211 Continuation US8220802B2 (en) | 2004-03-30 | 2006-09-29 | Leaf seal, in particular for a gas turbine, and method of producing it |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005095829A1 true WO2005095829A1 (de) | 2005-10-13 |
Family
ID=34961773
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2005/051351 WO2005095829A1 (de) | 2004-03-30 | 2005-03-23 | Lamellendichtung, insbesondere für eine gasturbine, sowie verfahren zu deren herstellung |
Country Status (7)
Country | Link |
---|---|
US (1) | US8220802B2 (de) |
EP (1) | EP1730428B1 (de) |
CN (1) | CN100554738C (de) |
AT (1) | ATE366885T1 (de) |
CA (1) | CA2561842C (de) |
DE (2) | DE102004016173A1 (de) |
WO (1) | WO2005095829A1 (de) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1892381A2 (de) * | 2006-08-24 | 2008-02-27 | United Technologies Pratt & Whitney | Dichtungsanordnung |
EP2236868A1 (de) * | 2009-03-31 | 2010-10-06 | Alstom Technology Ltd | Lamellendichtung für eine Strömungsmaschine |
US20180119791A1 (en) * | 2008-07-23 | 2018-05-03 | Sew-Eurodrive Gmbh & Co. Kg | Gearing |
CN114951894A (zh) * | 2022-07-04 | 2022-08-30 | 北京航空航天大学宁波创新研究院 | 一种浸渍钎焊夹具 |
Families Citing this family (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004059858A1 (de) * | 2004-12-11 | 2006-06-29 | Alstom Technology Ltd | Lamellendichtung, insbesondere für eine Gasturbine |
US8794631B2 (en) * | 2009-01-12 | 2014-08-05 | General Electric Company | Method of manufacturing of a compliant plate seal assembly |
US8250756B2 (en) * | 2009-02-20 | 2012-08-28 | General Electric Company | Method of manufacture of compliant plate seals |
US8272644B1 (en) * | 2009-07-14 | 2012-09-25 | Florida Turbine Technologies, Inc. | Floating card seal |
GB0922074D0 (en) * | 2009-12-18 | 2010-02-03 | Rolls Royce Plc | A leaf seal assembly |
JP5473685B2 (ja) * | 2010-03-10 | 2014-04-16 | 三菱重工業株式会社 | 軸シール装置及び軸シール装置を備える回転機械 |
US9206904B2 (en) | 2010-07-08 | 2015-12-08 | Siemens Energy, Inc. | Seal including flexible seal strips |
US8690158B2 (en) * | 2010-07-08 | 2014-04-08 | Siemens Energy, Inc. | Axially angled annular seals |
GB201113590D0 (en) * | 2011-08-08 | 2011-09-21 | Rolls Royce Plc | Leaf seal |
GB201113691D0 (en) * | 2011-08-09 | 2011-09-21 | Rolls Royce Plc | Leaf seal |
GB201311607D0 (en) | 2013-06-28 | 2013-08-14 | Rolls Royce Plc | A leaf seal |
GB201311610D0 (en) * | 2013-06-28 | 2013-08-14 | Rolls Royce Plc | A Leaf Seal |
GB201311611D0 (en) | 2013-06-28 | 2013-08-14 | Rolls Royce Plc | A Brush Seal |
JP6125412B2 (ja) * | 2013-11-22 | 2017-05-10 | 三菱重工業株式会社 | 軸シール装置、回転機械、及び軸シール装置の製造方法 |
JP6358976B2 (ja) * | 2015-02-20 | 2018-07-18 | 三菱日立パワーシステムズ株式会社 | タービン用シール装置及びタービン、並びにシール装置用の薄板 |
JP6675262B2 (ja) * | 2016-05-09 | 2020-04-01 | 三菱日立パワーシステムズ株式会社 | シールセグメント及び回転機械 |
JP6631837B2 (ja) * | 2016-05-09 | 2020-01-15 | 三菱日立パワーシステムズ株式会社 | シールセグメント及び回転機械 |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
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US6343792B1 (en) | 1998-07-13 | 2002-02-05 | Mitsubishi Heavy Industries, Ltd. | Shaft seal and turbine using the same |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
USRE30206E (en) * | 1973-11-23 | 1980-02-05 | Rolls Royce (1971) Limited | Seals and method of manufacture thereof |
US4618152A (en) * | 1983-01-13 | 1986-10-21 | Thomas P. Mahoney | Honeycomb seal structure |
US5597167A (en) * | 1994-09-28 | 1997-01-28 | United Technologies Corporation | Brush seal with fool proofing and anti-rotation tab |
DE19712088C2 (de) * | 1997-03-22 | 1999-06-24 | Mtu Muenchen Gmbh | Bürstendichtung mit in Umfangsrichtung schräg gestellten Borsten |
GB9801864D0 (en) * | 1998-01-30 | 1998-03-25 | Rolls Royce Plc | A seal arrangement |
DE102004020377A1 (de) * | 2004-04-23 | 2005-11-10 | Alstom Technology Ltd | Verfahren zur Bearbeitung von Dichtungen nach Art der Lamellendichtungen |
-
2004
- 2004-03-30 DE DE102004016173A patent/DE102004016173A1/de not_active Withdrawn
-
2005
- 2005-03-23 EP EP05717137A patent/EP1730428B1/de not_active Not-in-force
- 2005-03-23 CN CNB2005800102235A patent/CN100554738C/zh not_active Expired - Fee Related
- 2005-03-23 CA CA2561842A patent/CA2561842C/en not_active Expired - Fee Related
- 2005-03-23 AT AT05717137T patent/ATE366885T1/de not_active IP Right Cessation
- 2005-03-23 WO PCT/EP2005/051351 patent/WO2005095829A1/de active IP Right Grant
- 2005-03-23 DE DE502005001024T patent/DE502005001024D1/de active Active
-
2006
- 2006-09-29 US US11/537,211 patent/US8220802B2/en not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6343792B1 (en) | 1998-07-13 | 2002-02-05 | Mitsubishi Heavy Industries, Ltd. | Shaft seal and turbine using the same |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1892381A2 (de) * | 2006-08-24 | 2008-02-27 | United Technologies Pratt & Whitney | Dichtungsanordnung |
EP1892381A3 (de) * | 2006-08-24 | 2011-03-02 | United Technologies Pratt & Whitney | Dichtungsanordnung |
US20180119791A1 (en) * | 2008-07-23 | 2018-05-03 | Sew-Eurodrive Gmbh & Co. Kg | Gearing |
US10718421B2 (en) * | 2008-07-23 | 2020-07-21 | Sew-Eurodrive Gmbh & Co. Kg | Gearing |
EP2236868A1 (de) * | 2009-03-31 | 2010-10-06 | Alstom Technology Ltd | Lamellendichtung für eine Strömungsmaschine |
DE102009015122A1 (de) | 2009-03-31 | 2010-10-14 | Alstom Technology Ltd. | Lamellendichtung für eine Strömungsmaschine |
US8517673B2 (en) | 2009-03-31 | 2013-08-27 | Alstom Technology Ltd. | Lamellar seal for a turbomachine |
CN114951894A (zh) * | 2022-07-04 | 2022-08-30 | 北京航空航天大学宁波创新研究院 | 一种浸渍钎焊夹具 |
CN114951894B (zh) * | 2022-07-04 | 2024-01-02 | 北京航空航天大学宁波创新研究院 | 一种浸渍钎焊夹具 |
Also Published As
Publication number | Publication date |
---|---|
ATE366885T1 (de) | 2007-08-15 |
EP1730428B1 (de) | 2007-07-11 |
CA2561842C (en) | 2012-03-06 |
CN1950633A (zh) | 2007-04-18 |
US8220802B2 (en) | 2012-07-17 |
US20070120326A1 (en) | 2007-05-31 |
EP1730428A1 (de) | 2006-12-13 |
CN100554738C (zh) | 2009-10-28 |
CA2561842A1 (en) | 2005-10-13 |
DE102004016173A1 (de) | 2005-10-20 |
DE502005001024D1 (de) | 2007-08-23 |
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