EP1960636B1 - Turbomachine - Google Patents
Turbomachine Download PDFInfo
- Publication number
- EP1960636B1 EP1960636B1 EP06829956.9A EP06829956A EP1960636B1 EP 1960636 B1 EP1960636 B1 EP 1960636B1 EP 06829956 A EP06829956 A EP 06829956A EP 1960636 B1 EP1960636 B1 EP 1960636B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- insert
- seal
- gap
- turbine
- combustion chamber
- 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.)
- Not-in-force
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
- 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
- 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
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
Definitions
- the present invention relates to a turbomachine, in particular a gas turbine, having the features of the preamble of claim 1.
- a lining element for example an inner liner
- a membrane sealing groove for a membrane seal is formed on the carrier element.
- the support element is surrounded during operation of the turbomachine, for example, with a compressor end temperature and thus does not set very high demands on the oxidation resistance of the material. It is therefore usually sufficient if the support elements are made, for example, of Stg50T, Stg41T, St530TS or GGG40. In order to be able to further reduce a cooling air portion of a turbine platform in such turbomachines, this is made as short as possible, which, however, increases the static pressure before the leading edge of the turbine blade and causes a so-called bow wave effect by the aerodynamic resistance of a turbine blade.
- a turbomachine which has at least one combustion chamber and at least one turbine downstream thereto, wherein at least one support element and an associated therewith, designed as a heat protection lining element are provided. Between the at least one combustion chamber and the turbine downstream there is a gap sealed by means of a seal in which a replaceable insert is arranged on the end face on the carrier element, which protects at least the carrier element from hot gases.
- the invention is based on the general idea, in a turbomachine in a gap sealed by a seal between a combustion chamber and a turbine located downstream thereof, to arrange a replaceable insert on the end face on a carrier element of the combustion chamber, which reliably protects the carrier element from hot gases and thus oxidation.
- a replaceable insert on the end face on a carrier element of the combustion chamber, which reliably protects the carrier element from hot gases and thus oxidation.
- the exchangeable insert made of a material which is more resistant to oxidation is now designed as the carrier element itself or is coated with such a material.
- the use effectively prevents unwanted oxidation of the carrier element and, for example, must be replaced or maintained only in a maintenance interval corresponding to the lining element with the same properties as the heat-resistant lining element.
- this makes it possible to form the carrier element of a more favorable for the construction, for example, firmer, material and perform cheaper. It is therefore not necessary to produce the carrier element of a likewise oxidation-resistant material, resulting in significant savings.
- replaceable insert can be formed according to an advantageous embodiment of several circular segments or two semicircular rings, it is also possible to replace only individual insert segments as needed, which also maintenance costs and maintenance costs can be reduced,
- the replaceable insert is arranged in the gap between a first combustion chamber and a turbine located downstream thereof, and / or in the gap between a second combustion chamber and a low-pressure turbine located downstream thereof.
- the insert carries the seal and / or the seal is designed as a membrane seal.
- the seal can be easily removed by loosening the insert in the axial direction of the end face of the support element and just as easily be attached to it.
- an exchange of the entire support element is unnecessary, which on the one hand reduces the downtime of the turbomachine and on the other hand reduces costs.
- the seal is formed from a plurality of circular segments or from two semicircular rings, wherein the two semicircular rings overlap in the circumferential direction. This also allows the replacement of individual sealing segments or individual sealing semi-circular rings, whereby an individual and needs-based maintenance of the turbomachine can be achieved. At the same time, the segmentation of the gasket achieves better handling of the gasket, in particular during maintenance, which simplifies maintenance work and can thus reduce maintenance costs.
- each circle segment and / or each semicircular ring of the seal is fixed to at least one point on the insert. Due to the high temperatures, in particular caused by a hot gas break in the gap, there are significant deformations, which must be absorbed by the seal without damage.
- each of the segments or each of the half rings is, on the one hand, fixed, but, on the other hand, permits unhindered temperature expansion both in the radial and in the circumferential direction.
- Fig. 1 has a turbomachine 1 according to the invention, for example a gas turbine, at least one combustion chamber 2 and at least one turbine 3 located downstream of the combustion chamber 2.
- the flow direction is according to Fig. 1 denoted by the reference numeral 4.
- a gap 5 is formed, which via a seal 6 (see. Fig. 2 and 4 ) is sealed.
- the turbomachine 1 has at least one carrier element 7 and a lining element 8 connected thereto and designed as heat protection.
- the goal is to create a short turbine platform as possible. Due to the aerodynamic resistance of a blade 9, however, the static pressure increases in front of an inlet edge into the turbine blade 9, resulting in a so-called bow wave effect. As a result of the high static pressure in the region of a blade leading edge, hot gas penetration in the gap 5 between the combustion chamber 2 and the turbine 3 can thus occur.
- the acted upon with hot gas parts, such as the lining element 8, are preferably made of nickel-based alloys and therefore sufficiently protected even without a separate heat protection coating.
- an exchangeable insert 10 is arranged on the end side on the carrier element 7 in the gap 5 (cf. Fig. 1 to 4 ).
- the replaceable insert 10 is formed of an oxidation-resistant material, which in particular has a higher oxidation resistance than the material used for the carrier element 7.
- a welcome side effect of the short turbines 3 is also a reduced proportion of cooling air, whereby the efficiency of the turbine 3 can be increased.
- the exchangeable insert 10 is formed either from a plurality of circular segments or from two semicircular rings, wherein in particular the circular segments allow improved handling due to their low weight.
- this offers the advantage to renew individual circle segments of the insert 10 as needed, whereby a total of maintenance and thus maintenance costs can be saved.
- the end 10 arranged on the support element 7 insert 10 completely covers an end face of the carrier element 7, so that it is fully protected from entering into the gap 5 hot gases.
- An attachment of the insert 10 on the carrier element 7 takes place for example via a carrier element-side undercut 11 (see. Fig. 4 ), in which the replaceable insert 10 engages and / or via at least one fastening means 12 (see. Fig. 2 to 4 ), for example a screw. This ensures easy solubility and thus a quick replacement of the insert 10 and the seal 6 during maintenance.
- the replaceable insert 10 is preferably provided with a wear-resistant and temperature-resistant coating or formed entirely of a wear-resistant and temperature-resistant material.
- a wear-resistant and temperature-resistant coating or formed entirely of a wear-resistant and temperature-resistant material.
- An oxidation-resistant wear protection layer may, for example in the form of a Chromium carbide coating can be realized.
- Such a chromium carbide coating offers the advantage that the insert 11 per se can be formed from a material similar to the carrier element 7, whereby both the insert 10 and the carrier element 7 have a nearly identical thermal behavior, which is particularly favorable to gaps between individual Keep segments as small as possible.
- the choice of material so that in particular material pairings are used which, on the one hand, have a wear and oxidation-minimized behavior and, on the other hand, behave thermally similarly to the carrier element 7.
- Fig. 3 shows a longitudinal section in the region of a gap 5 between a first combustion chamber and a high-pressure turbine.
- the replaceable insert 10 is fastened to an outer support element 7 'by means of a fastening means 12.
- the insert 10 engages in an undercut 11 formed on the outer carrier element 7 'and rests against an outer lining element 8' on its side 16 facing away from the gap.
- the replaceable insert 10 adjoins a turbine blade carrier 18 with another side 17.
- the insert 10 closes the gap 5 according to Fig. 3 in such a way that any hot gas which may penetrate from the outside can not reach the outer carrier element 7 'and / or the turbine blade carrier 18 and thereby protect it from oxidation.
- the insert 10 is also in a gap 5 between a second combustion chamber and a low-pressure turbine located downstream thereof (see. Fig. 4 ) can be used.
- the seal 6 is arranged in an axially open stage 13 on the insert 10, wherein the seal 6 is held in the stage 13 via detachable holding elements 14 axially.
- the insert 10 thus carries the seal 6, which for example, is designed as a membrane seal.
- the seal 6 may have a plurality of circle segments or two semicircular rings which overlap in the circumferential direction.
- the holding member 14 is in each case braced by the attachment means 12 against the insert 10 and the support member 7 and thereby prevent axial displacement of the seal 6.
- each holding member 14 is arranged in each case in a recess 19 (see. Fig. 2 ), which at least reduces a thickness of the insert 10 in the flow direction 4. Through the recess 19, the position of each received therein holding member 14 is predetermined, whereby the assembly of the holding elements 14 is simplified.
- each circular segment and / or each semicircular ring of the seal 6 is fix at at least one point on the insert 10.
- these are therefore preferably fixed at 12 o'clock and at 6 o'clock at one point on the carrier element 7.
- the seal 6 is fixed in the circumferential direction via a fixing pin 15, whereas a radial clearance is possible in order to be able to absorb thermal expansions without damage.
- the solution according to the invention provides an easily exchangeable and thus cost-effective oxidation protection for a face 5 located in a gap 5 of the carrier element, resulting on the one hand lower maintenance costs and downtime of the turbomachine 1 and on the other hand, a cooling air flow, with which the gap 5 is flushed reduced can be, which has a favorable effect on the efficiency of the turbomachine 1.
- the insert 10 is optionally formed entirely of an oxidation-resistant and temperature-resistant material or has an oxidation-resistant and temperature-resistant coating, while a core of the insert 10 from the same material as the support member 7, 7 'is formed and thereby a nearly identical temperature behavior between insert 10 and support element 7, 7' can be achieved, which has a favorable effect on any expected gap widths.
- the insert 10 carries the seal 6, which may be formed for example as a membrane seal. Due to the circular segment-like or semicircular design of the insert 10 and the seal 6, a particularly favorable handling of both the seal 6 and the insert 10 is given, which can reduce the maintenance and thus the maintenance costs. In addition, this allows only those parts to be replaced, which must be replaced due to the oxidation or erosion, while other not so badly damaged sealing segments or insert segments can remain on the carrier element 7. A complete replacement of the support member 7, as he was required earlier, for example, and the associated long downtime and high maintenance or replacement costs can be effectively avoided. At the same time, the cooling air flow for cooling the gap 5 can be reduced, which increases the efficiency of the turbomachine 1.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (8)
- Turbomachine (1), en particulier turbine à gaz, comprenant au moins une chambre de combustion (2) et au moins une turbine (3) placée en aval de celle-ci,- la chambre de combustion (2) présentant au moins un élément de support (7) et un élément d'habillage (8) raccordé à celui-ci et réalisé sous forme de protection contre la chaleur,- entre l'au moins une chambre de combustion (2) et la turbine (3) placée en aval étant réalisée une fente (5) étanchéifiée au moyen d'un joint d'étanchéité (6), dans laquelle est disposé un insert remplaçable (10) du côté frontal au niveau de l'élément de support (7), lequel porte le joint d'étanchéité (6) et protège au moins l'élément de support (7) contre les gaz chauds,caractérisée en ce que
l'insert remplaçable (10) est réalisé à partir d'un matériau plus résistant à l'oxydation que l'élément de support (7) ou est revêtu d'un tel matériau. - Turbomachine selon la revendication 1, caractérisée en ce que- l'insert remplaçable (10) est formé de plusieurs segments de cercle ou de deux bagues semi-circulaires, et/ou- l'insert remplaçable (10) s'engage dans une contre-dépouille (11) du côté de l'élément de support et/ou est retenu par le biais d'au moins un moyen de fixation (12) sur le côté frontal de l'élément de support (7).
- Turbomachine selon la revendication 1 ou 2,
caractérisée en ce que
l'insert remplaçable (10) présente un revêtement résistant à l'usure et à la température. - Turbomachine selon l'une quelconque des revendications 1 à 3,
caractérisée en ce que- l'insert (10) est disposé dans la fente (5) entre une première chambre de combustion et une turbine (3) placée en aval, et/ou- l'insert est disposé dans la fente (5) entre une deuxième chambre de combustion et une turbine (3) placée en aval. - Turbomachine selon l'une quelconque des revendications 1 à 4,
caractérisée en ce que- l'insert (10) porte le joint d'étanchéité (6), et/ou- le joint d'étanchéité (6) est réalisé sous forme de joint d'étanchéité à membrane. - Turbomachine selon l'une quelconque des revendications 1 à 5,
caractérisée en ce que
le joint d'étanchéité (6) présente plusieurs segments de cercle ou deux bagues semi-circulaires, les deux bagues semi-circulaires se chevauchant dans la direction périphérique. - Turbomachine selon l'une quelconque des revendications 1 à 6,
caractérisée en ce que- le joint d'étanchéité (6) est disposé dans un étage ouvert axialement (13) sur l'insert (10) et/ou- le joint d'étanchéité (6) est retenu par le biais d'éléments de retenue amovibles (14) dans l'étage (13). - Turbomachine selon l'une quelconque des revendications 1 à 7,
caractérisée en ce que
chaque segment de cercle et/ou chaque bague semi-circulaire du joint d'étanchéité (6) est fixé au niveau d'au moins un point sur l'insert (10).
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH19772005 | 2005-12-14 | ||
PCT/EP2006/068226 WO2007068538A1 (fr) | 2005-12-14 | 2006-11-08 | Turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1960636A1 EP1960636A1 (fr) | 2008-08-27 |
EP1960636B1 true EP1960636B1 (fr) | 2016-01-27 |
Family
ID=35929927
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06829956.9A Not-in-force EP1960636B1 (fr) | 2005-12-14 | 2006-11-08 | Turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US8555655B2 (fr) |
EP (1) | EP1960636B1 (fr) |
ES (1) | ES2569521T3 (fr) |
WO (1) | WO2007068538A1 (fr) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP4626714B2 (ja) * | 2008-08-22 | 2011-02-09 | ダイキン工業株式会社 | 冷凍装置 |
CH703105A1 (de) * | 2010-05-05 | 2011-11-15 | Alstom Technology Ltd | Gasturbine mit einer sekundärbrennkammer. |
US9316119B2 (en) * | 2011-09-15 | 2016-04-19 | United Technologies Corporation | Turbomachine secondary seal assembly |
US9249678B2 (en) | 2012-06-27 | 2016-02-02 | General Electric Company | Transition duct for a gas turbine |
EP3421727B1 (fr) * | 2017-06-30 | 2020-01-29 | Ansaldo Energia Switzerland AG | Turbine à gaz équipée d'un support d'aubes de turbine |
US11959498B2 (en) * | 2021-10-20 | 2024-04-16 | Energy Recovery, Inc. | Pressure exchanger inserts |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1259142B (de) | 1962-02-14 | 1968-01-18 | Licentia Gmbh | Ringflansch des rohrfoermigen Innen- oder Aussengehaeuses einer Axialgas- oder -dampfturbine |
US3224194A (en) * | 1963-06-26 | 1965-12-21 | Curtiss Wright Corp | Gas turbine engine |
US3965066A (en) | 1974-03-15 | 1976-06-22 | General Electric Company | Combustor-turbine nozzle interconnection |
US4124737A (en) * | 1976-12-30 | 1978-11-07 | Union Carbide Corporation | High temperature wear resistant coating composition |
CH633351A5 (de) | 1978-11-09 | 1982-11-30 | Sulzer Ag | Waermedehnungen nachgebende abdichtung einer ringbrennkammer fuer eine gasturbine. |
US4379560A (en) | 1981-08-13 | 1983-04-12 | Fern Engineering | Turbine seal |
US5337583A (en) | 1992-08-24 | 1994-08-16 | United Technologies Corporation | Replaceable clip |
DE4324035C2 (de) | 1993-07-17 | 2003-02-27 | Alstom | Gasturbine |
US5749218A (en) * | 1993-12-17 | 1998-05-12 | General Electric Co. | Wear reduction kit for gas turbine combustors |
GB2373299B (en) * | 2001-03-12 | 2004-10-27 | Alstom Power Nv | Re-fired gas turbine engine |
FR2825783B1 (fr) * | 2001-06-06 | 2003-11-07 | Snecma Moteurs | Accrochage de chambre de combustion cmc de turbomachine par pattes brasees |
JP3600912B2 (ja) * | 2001-09-12 | 2004-12-15 | 川崎重工業株式会社 | 燃焼器ライナのシール構造 |
US6834507B2 (en) * | 2002-08-15 | 2004-12-28 | Power Systems Mfg., Llc | Convoluted seal with enhanced wear capability |
US7093440B2 (en) * | 2003-06-11 | 2006-08-22 | General Electric Company | Floating liner combustor |
US7527469B2 (en) * | 2004-12-10 | 2009-05-05 | Siemens Energy, Inc. | Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine |
-
2006
- 2006-11-08 WO PCT/EP2006/068226 patent/WO2007068538A1/fr active Application Filing
- 2006-11-08 EP EP06829956.9A patent/EP1960636B1/fr not_active Not-in-force
- 2006-11-08 ES ES06829956.9T patent/ES2569521T3/es active Active
-
2008
- 2008-06-16 US US12/140,094 patent/US8555655B2/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US20090071167A1 (en) | 2009-03-19 |
EP1960636A1 (fr) | 2008-08-27 |
ES2569521T3 (es) | 2016-05-11 |
WO2007068538A1 (fr) | 2007-06-21 |
US8555655B2 (en) | 2013-10-15 |
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