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EP 2 741 001 B1 |
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EUROPEAN PATENT SPECIFICATION |
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Mention of the grant of the patent: |
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05.02.2020 Bulletin 2020/06 |
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Date of filing: 10.12.2013 |
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International Patent Classification (IPC):
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Supporting structure for gas turbine combustion chamber heat-insulating tiles, heat-insulating
module, and gas turbine combustion chamber
Stützstruktur für Hitzeschildplatten einer Gasturbinenbrennkammer, Hitzeschildeinheit
und Gasturbinenbrennkammer
Structure de support des plaques d'un bouclier thermique d'une chambre de combustion
d'une turbine à gaz, ensemble d'un bouclier thermique et chambre de combustion d'une
turbine à gaz
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Designated Contracting States: |
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AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL
NO PL PT RO RS SE SI SK SM TR |
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Priority: |
10.12.2012 IT MI20122104
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Date of publication of application: |
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11.06.2014 Bulletin 2014/24 |
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Proprietor: Ansaldo Energia S.p.A. |
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Genova (IT) |
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Inventors: |
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- Bertino, Gianluigi
16031 Bogliasco (IT)
- Galella, Rocco
16151 Genova (IT)
- Vella, Alessandro
16122 Genova (IT)
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Representative: Bernotti, Andrea et al |
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Studio Torta S.p.A.
Via Viotti, 9 10121 Torino 10121 Torino (IT) |
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References cited: :
EP-A1- 2 236 928 EP-A1- 2 341 287
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EP-A1- 2 270 395
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Note: Within nine months from the publication of the mention of the grant of the European
patent, any person may give notice to the European Patent Office of opposition to
the European patent
granted. Notice of opposition shall be filed in a written reasoned statement. It shall
not be deemed to
have been filed until the opposition fee has been paid. (Art. 99(1) European Patent
Convention).
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[0001] The present invention relates to a supporting structure for gas turbine combustion
chamber heat-insulating tiles, an insulating module and a gas turbine combustion chamber.
[0002] As known, the combustion chamber of gas turbines must be provided on the inside with
a heat-insulating lining made of refractory material, because of the high temperatures
which are developed during machine operation. The heat-insulating lining is generally
formed by a plurality of refractory tiles arranged in continuous rows on the inner
walls of the combustion chamber casing, so as to define an essentially continuous
surface. In the toroidal type combustion chambers, the refractory tiles are arranged
on circumferences about the rotor axis.
[0003] Particularly in toroidal combustion chambers, the assembly of the refractory tiles
includes inserting and sliding the connection elements along circumferential guides.
[0004] Normally, indeed, the refractory tiles have grooves on opposite sides and are fixed
to the casing by connection elements which couple to ribs defined by the grooves.
In general, the connection elements for one side of the refractory tiles are inserted
in guides on the casing and made to slide to the respective fastening positions. The
refractory tile is then arranged in seat, with a side engaging the fastening elements.
Further connection elements are inserted along the guides and made to slide to couple
with the side of the tile which is still free.
[0005] Particular measures are thus needed for the last tile of each row.
[0006] According to a known solution, a metallic tile is used in each row, which has a through
hole and is fixed to the casing for last by micro-cast screw inserted from the outside
and engaged on a pack of pre-assembled springs. In this manner, it is not necessary
to make the fastening elements slide and assembly may be used in relatively easy manner.
However, the metallic tile cannot guarantee an insulation comparable to that of the
refractory tiles and moreover requires a specific cooling system.
[0007] Another known solution uses perforated refractory tiles, fixed to the casing with
metallic through screws, using a system similar to that described above. Although
heat dispersions are partially eliminated, the problem of cooling the metallic parts,
in particular the screw, which is exposed to high temperature, remains. Furthermore,
only a few specimens of specifically perforated refractory tiles must be used, with
obvious additional costs. A supporting structure for a heat-insulating tile having
the features specified in the preamble of claim 1 is known from
EP 2 236 928 A1.
[0008] It is thus an object of the present invention to provide a supporting structure for
heat-insulating tiles of gas turbine combustion chambers, a heat-insulating module
for gas turbine combustion chambers and a gas turbine combustion chamber which allow
to overcome the limitations described.
[0009] According to the present invention, a supporting structure for heat-insulating tiles
of gas turbine combustion chambers, a heat-insulating module for gas turbine combustion
chambers and a gas turbine combustion chamber are provided, as defined in claims 1,
10 and 14, respectively.
[0010] The present invention will now be described with reference to the accompanying drawings,
which illustrate some non-limitative embodiments thereof, in which:
- figure 1 is a perspective three-quarters view from the top of a heat-insulating module
incorporating supporting structures according to an embodiment of the present invention;
- figure 2 is a plan view from the top of the heat insulating module in figure 1;
- figure 3 is a front view of the heat-insulating module in figure 1, taken along the
plotting plane III-III in figure 2;
- figure 4 is a three-quarters perspective view from the bottom of one of the supporting
structures in figure 1;
- figure 5 is a side view taken along a vertical axial plan of a gas turbine combustion
chamber incorporating specimens of the heat-insulating module in figure 1;
- figure 6 is a front view of the combustion chamber in figure 5, taken along plotting
line VI-VI in figure 5 and with parts removed for clarity;
- figure 7 shows an enlarged detail of the combustion chamber in figure 5, partially
exploded and with parts removed for clarity;
- figure 8 shows a magnified detail of figure 5; and
- figure 9 is a partially exploded perspective view of the part in figure 8.
[0011] With reference to figures 1-3, a gas turbine combustion chamber heat-insulating module,
as a whole indicated by reference numeral 1, comprises a heat-insulating tile 2, made
of refractory material, e.g. a ceramic material, and supporting structures 3 for fixing
the heat-insulating tile 2 to the walls of a gas turbine combustion chamber (not shown
here).
[0012] The heat-insulating tile 2 is rectangular and has an essentially continuous and uniform
working face 2a facing the inside of the combustion chamber in use. In particular,
the working face 2a of the heat-insulating tile 2 is free from holes, cavities and
through recesses.
[0013] In one embodiment, opposite sides of the heat-insulating tile 2 has respective groves
4, which extend for their entire length. The grooves 4 form ribs 2b, which define
fastening seats for coupling with the supporting structures 3. Alternatively, the
sides of the heat-insulating tile 2 may have separate recesses defining fastening
seats for the supporting structures 3.
[0014] In one embodiment, the heat-insulating module 1 comprises two supporting structures
3 arranged parallel to each other but it is understood that a different number thereof
could be provided.
[0015] Each supporting structure 3, one of which is shown in figure 4, comprises a first
connection element 5, a second connection element 6, a clamping device 7 and a fixing
device 8.
[0016] The first connection element 5 and the second connection element 6 are defined by
respective elastic metal laminae and extend opposite to each other from the clamping
device 7.
[0017] The first connection element 5 and the second connection element 6 have respective
first ends 5a, 6a and second ends 5b, 6b. The first ends 5a, 6a are coupled to respective
fastening seats, defined by portions of the ribs 2b on opposite sides of the heat-insulating
tile 2. In one embodiment, for example, the first ends 5a, 6a of the first connection
element and of the second connection element 6 are folded as a C toward respective
second ends 5b, 6b, on the side facing the heat-insulating tile 2, and form terminals
13, 14 adapted to receive portions of respective ribs 2b of the heat-insulating tile
2.
[0018] The second ends 5b, 6b of the first connection element 5 and of the second connection
element 6 are clamped by the clamping device 7. Furthermore, the second ends 5b, 6b
at rest are folded so that the first ends 5a, 6a extend slightly towards the heat-insulating
tile 2, once the first connection element 5 and the second connection element 6 are
coupled to the clamping device.
[0019] The clamping device 7 comprises a first plate 10 and a second plate 11, reciprocally
facing each other, and clamping screws 12 for alternatively clamping the first plate
10 and the second plate 11 against each other and to move the first plate 10 and the
second plate 11 away from each other. In one embodiment, the first plate 10 and the
second plate 11 have an essentially rectangular shape and the first connection element
5 and the second connection element 6 extend from the smaller sides, parallel to the
greater sides of the first plate 10 and of the second plate 11.
[0020] The second ends 5b, 6b of the first connection element 5 and of the second connection
element 6 are clamped between the first plate 10 and the second plate 11 of the clamping
device 7. Furthermore, the second ends 5b, 6b have holes and the screws 12 are arranged
through them preventing the connection elements 5, 6 from exiting from the respective
seats. In one embodiment, the screws 12 are of the countersunk head type and are profiled
so as to allow the thermal expansion of the connection elements 5, 6.
[0021] The fastening device 8 is arranged on one side of the supporting structure 3 opposite
to the heat-insulating tile 2 in use and in an embodiment comprises a threaded pin
15 and a nut 16. The threaded pin 15 extends from the first plate 10 of the clamping
device 7 on the side opposite to the heat-insulating tile 2 in use and, in the example
of figures 1-4, is screw/nutscrew coupled to a threaded seat 18 in the second plate
11 and in the first plate 10 with through hole. In an embodiment, the threaded pin
15 is welded in the seat 18, so as to prevent the rotation with respect to the plates
10, 11 of the clamping device 7. Alternatively, the threaded pin 15 may be made in
one piece with the second plate 11.
[0022] Figures 5 and 6 illustrate a combustion chamber 20 of a gas turbine (not shown as
a whole). The combustion chamber 20 comprises a toroidal casing 21 extending about
an axis having a first radially outer shell 22 and a second radially inner shell 23.
The combustion chamber 20 is provided with a heat-insulating lining 25 which covers
the inside of the first shell 22 and the second shell 23 and comprises a plurality
of heat-insulating tiles 26 and a plurality of heat-insulating modules 1. In one embodiment,
the heat-insulating tiles 26 are of the same type as the heat-insulating tiles 2 used
in the heat-insulating modules 1 and are arranged in adjacent groups along circumferences
about axis A of the combustion chamber 20. Each group comprises a respective heat-insulating
module 1 (except possibly groups in which an access opening to the combustion chamber
20 is provided).
[0023] The heat-insulating tiles 26 are fitted on circumferential guides 28 by connection
elements 30 on the first radially outer shell 22 (figure 7). The guides 28 are obtained
on an inner face 22a of the first shell 22 and extend about axis A. The connection
elements 30 are essentially equal to the connection elements 5, 6 of the supporting
structures 3 of the heat-insulating modules 1 and are fixed directly to the casing
21 of the combustion chamber 20.
[0024] The heat-insulating modules 1 are fixed to the first shell 22, as shown in figures
7 and 8. More specifically, the first shell 22 has through holes 31. The threaded
pins 15 of the heat-insulating modules 1 are housed in respective through holes 31
and clamped to one another by respective nuts 16. Furthermore, the guides 28 have
seats 32 for housing the clamping devices 7 (in particular, the first plates 10) of
the respective heat-insulating modules 1. Also by virtue of this measure, the heat-insulating
modules 1 are arranged so that the heat-insulating tiles 2 form an essentially continuous
surface without misalignments with the heat-insulating tiles 26 of the respective
groups.
[0025] The heat-insulating tiles 26 are fitted in conventional manner. Once the connection
elements 30 for one side of a heat-insulating tile 26 are housed in the guides 28
and fixed to the casing 21, the heat-insulating tile 26 is arranged in its seat and
the connection elements 30 for the other side of the heat-insulating tile 26 are introduced.
The procedure is repeated to complete a group of heat-insulating tiles 26 along a
circumference, except for one element. A heat-insulating module 1 is used as last
element of the group. This is pre-assembled and then fixed to the first shell 22 of
the casing 21.
[0026] During pre-assembly, the first ends 5a, 6a of the connection elements 5, 6 of the
supporting structures 3 are coupled to the ribs 2b on the sides of the heat-insulating
tile 2 and the second ends 5b, 6b are rested on the second plate 11. The first plate
10 is thus joined to the second plate 11 and clamped by screws 12. As a result of
this operation, the first connection element 5 and the second connection element 6,
which are elastic, are preloaded.
[0027] The pre-assembled heat-insulating module 1 is inserted in the single space which
is still empty of the respective group and fixed to the first shell 22 of the casing
21. The threaded pins 15 of the supporting structures 3 are introduced into respective
through holes 31 and fixed by the nuts 16.
[0028] The described supporting structure thus allows to complete the heat-insulating lining
of a toroidal gas turbine combustion chamber using heat-insulating tiles of a same
type. Multiple advantages derive from this.
[0029] Firstly, the lining is uniformly made of heat-insulating material, without tiles
or metallic inserts. The thermal conductivity of the refractory material of the heat-insulating
tiles is considerably lower than that of metals, and consequently insulation is more
effective and thermal energy losses are reduced.
[0030] Furthermore, also the fixing of the casing does not require metallic component exposed
to the high temperature of the combustion chamber. Consequently, the working conditions
being the same, the cooling system of the metallic parts (connection elements), already
present for the other heat-insulating tiles, is suitable also for the heat-insulating
modules.
[0031] The fact that no special heat-insulating tiles are needed for completing the lining
is advantageous also from the economic point of view because the need to make only
a few special specimens with high costs is avoided. Furthermore, the assembly of the
heat-insulating modules is simple and rapid.
[0032] It is finally apparent that changes and variations can be made to the described heat-insulating
module and the combustion chamber described and illustrated without departing from
the scope of protection of the accompanying claims.
1. A supporting structure for gas turbine combustion chamber heat-insulating tiles, comprising:
a first connection element (5) and second connection element (6) having respective
first ends (5a, 6a), configured to fit onto sides of a heat-insulating tile (2) of
a gas turbine combustion chamber (20), and respective second ends (5b, 6b);
a clamping device (7); and
a fixing device (8), provided with a threaded pin (15), extending from the clamping
device (7) on the side in use opposite to the heat-insulating tile (2), and with a
nut (16);
wherein the first connection element (5) and second connection element (6) have the
respective second ends (5b, 6b) clamped by the clamping device (7), and extend in
opposite directions from the clamping device (7);
characterized in that the threaded pin (15) is rigidly connected to the clamping device (7), so as to prevent
rotations of the threaded pin (15) with respect to the clamping device (7).
2. A supporting structure as claimed in claim 1, wherein the clamping device (7) comprises
a first plate (10) and a second plate (11) facing each other, and screw clamping means
(12) for alternatively tightening the first plate (10) and second plate (11) against
each other, and separating the first plate (10) and second plate (11) from each other;
and wherein the second ends (5b, 6b) of the first connection element (5) and of the
second connection element (6) are clamped between the first plate (10) and second
plate (11).
3. A supporting structure as claimed in claim 2, wherein the first plate (10) and second
plate (11) are substantially rectangular.
4. A supporting structure as claimed in claim 2 or 3, wherein the second ends (5b, 6b)
of the first connection element (5) and of the second connection element (6) have
holes, and the screw clamping means (12) comprise a first and second screw, which
fit through the second ends (5b, 6b) of the first connection element (5) and of the
second connection element (6), respectively.
5. A supporting structure as claimed in any one of the claims 2 to 4, wherein the threaded
pin (15) is screw/nut-screw coupled to a threaded seat (18) in either the first plate
(10) or the second plate (11) and welded in the threaded seat (18).
6. A supporting structure as claimed in any one of the claims 2 to 4, wherein the threaded
pin (15) is made in one piece with one between either the first plate (10) and the
second plate (11).
7. A supporting structure as claimed in any one of the foregoing claims, wherein the
first connection element (5) and second connection element (6) comprise respective
elastic metal laminae.
8. A supporting structure as claimed in any one of the foregoing claims, wherein the
first ends (5a, 6a) of the first connection element (5) and second connection element
(6) form seats (13, 14) for housing portions of respective sides of the heat-insulating
tile (2).
9. A supporting structure as claimed in any one of the foregoing claims, wherein the
first ends (5a, 6a) of the first connection element (5) and of the second connection
element (6) are bent towards the respective second ends (5b, 6b), on the side facing
the heat-insulating tile (2) in use.
10. A gas turbine combustion chamber heat-insulating module comprising a heat-insulating
tile (2) and at least one supporting structure (3) as claimed in any one of the foregoing
claims, fitted to the heat-insulating tile (2).
11. A heat-insulating module as claimed in claim 10, wherein the heat-insulating tile
(2) has fastening seats (2b) on opposite sides; and the first ends (5a, 5b) of the
first connection element (5) and of the second connection element (6) are fitted to
respective fastening seats (2b) on the heat-insulating tile (2).
12. A heat-insulating module as claimed in claim 10 or 11, comprising a plurality of supporting
structures (3) as claimed in any one of Claims 1 to 9 and fitted to the heat-insulating
tile (2) and arranged parallel to each other.
13. A heat-insulating module as claimed in any one of claims 10 to 12, wherein the heat-insulating
tile (2) has a substantially continuous and uniform work face.
14. A gas turbine combustion chamber comprising a toroidal casing (21) extending about
an axis (A) and a heat-insulating lining (25) fixed to the casing (21) having at least
one heat-insulating module (1) as claimed in any one of claims 10 to 13, and wherein
the heat-insulating module (1) is fixed to the casing (21) with the threaded pin (15)
fitted through a hole (31) in the casing (21), and the nut (16) is fitted to the threaded
pin (15) from outside the casing (21).
15. A combustion chamber as claimed in claim 14, wherein the heat-insulating lining (25)
comprises a plurality of further heat-insulating tiles (26) fitted to the first shell
(22), along a circle about the axis (A) ;
and wherein the heat-insulating module (1) forms a substantially continuous surface
with the further heat-insulating tiles (26).
16. A combustion chamber as claimed in claim 15, wherein an inner surface (22a) of the
first shell has circumferential guides (28) for housing connection elements (30) for
fastening the further heat-insulating tiles (26), and a seat (32) in which the clamping
device (7) of the heat-insulating module (1) is housed.
1. Stützstruktur für Hitzeschildplatten einer Gasturbinenbrennkammer umfassend:
ein erstes Verbindungselement (5) und ein zweites Verbindungselement (6), die jeweils
erste Enden (5a, 6a) aufweisen, welche dazu bestimmt sind, an den Seiten einer Hitzeschildplatte
(2) einer Gasturbinenbrennkammer (20) montiert zu werden, und jeweils zweite Enden
(5b, 6b);
eine Spannvorrichtung (7); und
eine Befestigungsvorrichtung (8), die mit einem Gewindestift (15) versehen ist, der
sich von der Spannvorrichtung (7) auf der Betriebsseite gegenüber der Hitzeschildplatte
(2) erstreckt, und mit einer Mutter (16) ;
wobei jeweils das zweite Ende (5b, 6b) des ersten Verbindungselements (5) und des
zweiten Verbindungselements (6) von der Spannvorrichtung (7) eingespannt wird und
sich in entgegengesetzte Richtungen von der Spannvorrichtung (7) erstreckt;
dadurch gekennzeichnet, dass das der Gewindestift (15) mit der Spannvorrichtung (7) starr verbunden ist, so dass
Drehungen des Gewindestifts (15) in Bezug auf die Spannvorrichtung (7) verhindert
werden.
2. Stützstruktur nach Anspruch 1, wobei die Spannvorrichtung (7) eine erste Platte (10)
und eine zweite Platte (11) umfasst, die einander gegenüberliegend angeordnet sind,
sowie eine Schraubklemmvorrichtungen (12), welche die erste Platte (10) und die zweite
Platte (11) abwechselnd gegeneinander festziehen und die erste Platte (10) und die
zweite Platte (11) voneinander trennen; wobei die zweiten Enden (5b, 6b) des ersten
Verbindungselements (5) und des zweiten Verbindungselements (6) zwischen der ersten
Platte (10) und der zweiten Platte (11) eingespannt sind.
3. Stützstruktur nach Anspruch 2, wobei die erste Platte (10) und die zweite Platte (11)
im Wesentlichen rechteckig sind.
4. Stützstruktur nach Anspruch 2 oder 3, wobei die zweiten Enden (5b, 6b) des ersten
Verbindungselements (5) und des zweiten Verbindungselements (6) Löcher aufweisen und
die Schraubklemmvorrichtungen (12) eine erste und eine zweite Schraube aufweisen,
welche jeweils durch die zweiten Enden (5b, 6b) des ersten Verbindungselements (5)
und des zweiten Verbindungselements (6) passen.
5. Stützstruktur nach einem der Ansprüche 2 bis 4, wobei der Gewindestift (15) entweder
an der ersten Platte (10) oder der zweiten Platte (11) mittels einer Schrauben-Mutter-Verbindung
mit einem Gewindesitz (18) verbunden und in den Gewindesitz (18) eingeschweißt ist.
6. Stützstruktur nach einem der Ansprüche 2 bis 4, wobei der Gewindestift (15) entweder
mit der ersten Platte (10) oder der zweiten Platte (11) einstückig ausgeführt ist.
7. Stützstruktur nach einem der vorstehenden Ansprüche, wobei das erste Verbindungselement
(5) und das zweite Verbindungselement (6) jeweils elastische Metalllamellen aufweisen.
8. Stützstruktur nach einem der vorstehenden Ansprüche, wobei die ersten Enden (5a, 6a)
des ersten Verbindungselements (5) und des zweiten Verbindungselements (6) Aufnahmeflächen
(13, 14) zur Aufnahme von Abschnitten der entsprechenden Seiten der Hitzeschildplatte
(2) bilden.
9. Stützstruktur nach einem der vorstehenden Ansprüche, wobei die ersten Enden (5a, 6a)
des ersten Verbindungselements (5) und des zweiten Verbindungselements (6) auf der
Seite, die der im Betrieb befindlichen Hitzeschildplatte (2) gegenüberliegt, in Richtung
der jeweiligen zweiten Enden (5b, 6b) gebogen sind.
10. Hitzeschildmodul einer Gasturbinenbrennkammer, umfassend eine Hitzeschildplatte (2)
und mindestens eine Stützstruktur (3) nach einem der vorstehenden Ansprüche, welche
an der Hitzeschildplatte (2) befestigt ist.
11. Hitzeschildmodul nach Anspruch 10, wobei die Hitzeschildplatte (2) an gegenüberliegenden
Seiten Befestigungssitze (2b) aufweist und die ersten Enden (5a, 6a) des ersten Verbindungselements
(5) und des zweiten Verbindungselements (6) an den entsprechenden Befestigungssitzen
(2b) der Hitzeschildplatte (2) befestigt sind.
12. Hitzeschildmodulnach Anspruch 10 oder 11, umfassend eine Vielzahl von Stützstrukturen
(3) nach einem der Ansprüche 1 bis 9, welche an der Hitzeschildplatte (2) befestigt
und parallel zueinander angeordnet sind.
13. Hitzeschildmodulnach einem der Ansprüche 10 bis 12, wobei die Hitzeschildplatte (2)
eine im Wesentlichen durchgehende und gleichmäßige Arbeitsfläche aufweist.
14. Gasturbinenbrennkammer, umfassend ein ringförmiges Gehäuse (21), das sich um eine
Achse (A) erstreckt, und eine an dem Gehäuse (21) befestigte Hitzeschildauskleidung
(25) mit mindestens einem Hitzeschildmodul (1) nach einem der Ansprüche 10 bis 13,
wobei das Hitzeschildmodul (1) an dem Gehäuse (21) befestigt ist und der Gewindestift
(15) durch eine in dem Gehäuse (21) vorgesehene Öffnung (31) geführt wird, wobei die
Mutter (16) von der Außenseite des Gehäuses (21) mit dem Gewindestift (15) verschraubt
ist.
15. Brennkammer nach Anspruch 14, wobei die Hitzeschildauskleidung (25) eine Vielzahl
weiterer Hitzeschildplatten (26) umfasst, die entlang einem Kreis um die Achse (A)
an dem ersten Mantel (22) befestigt sind,
wobei das Hitzeschildmodul (1) mit den weiteren Hitzeschildplatten (26) eine im Wesentlichen
durchgehenden Fläche bildet.
16. Brennkammer nach Anspruch 15, wobei eine Innenfläche (22a) des ersten Mantels Umfangsführungen
(28) zur Aufnahme von Verbindungselementen (30) aufweist, die zur Befestigung der
weiteren Hitzeschildplatten (26) dienen, und eine Aufnahmefläche (32), auf der die
Spannvorrichtung (7) des Hitzeschildmoduls (1) angeordnet ist.
1. Structure de support pour plaques thermiquement isolantes de chambre de combustion
de turbine à gaz comprenant :
un premier élément de raccordement (5) et un second élément de raccordement (6) ayant
des premières extrémités (5a, 6a) respectives, configurées pour se monter sur les
côtés d'une plaque thermiquement isolante (2) d'une chambre de combustion de turbine
à gaz (20), et des secondes extrémités (5b, 6b) respectives ;
un dispositif de serrage (7) ; et
un dispositif de fixation (8) prévu avec une broche filetée (15), s'étendant à partir
du dispositif de serrage (7) sur le côté opposé, à l'usage, à la plaque thermiquement
isolante (2), et avec un écrou (16);
dans laquelle le premier élément de raccordement (5) et le second élément de raccordement
(6) ont des secondes extrémités (5b, 6b) respectives serrées par le dispositif de
serrage (7), et s'étendent dans des directions opposées du dispositif de serrage (7)
;
caractérisée en ce que la broche filetée (15) est rigidement raccordée au dispositif de serrage (7), afin
d'empêcher les rotations de la broche filetée (15) par rapport au dispositif de serrage
(7).
2. Structure de support selon la revendication 1, dans laquelle le dispositif de serrage
(7) comprend une première plaque (10) et une seconde plaque (11) se faisant face,
et un moyen de serrage de vis (12) pour serrer, de manière alternée, la première plaque
(10) et la seconde plaque (11) l'une contre l'autre, et séparer la première plaque
(10) et la seconde plaque (11) l'une de l'autre ; et dans laquelle les secondes extrémités
(5b, 6b) du premier élément de raccordement (5) et du second élément de raccordement
(6) sont serrées entre la première plaque (10) et la seconde plaque (11).
3. Structure de support selon la revendication 2, dans laquelle la première plaque (10)
et la seconde plaque (11) sont sensiblement rectangulaires.
4. Structure de support selon la revendication 2 ou 3, dans laquelle les secondes extrémités
(5b, 6b) du premier élément de raccordement (5) et du second élément de raccordement
(6) ont des trous, et le moyen de serrage de vis (12) comprend une première et une
seconde vis, qui se montent à travers les secondes extrémités (5b, 6b) du premier
élément de raccordement (5) et du second élément de raccordement (6) respectivement.
5. Structure de support selon l'une quelconque des revendications 2 à 4, dans laquelle
la broche filetée (15) est couplée par vis / écrou - vis à un siège fileté (18) dans
la première plaque (10) ou la seconde plaque (11) et soudée dans le siège fileté (18).
6. Structure de support selon l'une quelconque des revendications 2 à 4, dans laquelle
la broche filetée (15) est réalisée d'un seul tenant avec l'une parmi la première
plaque (10) et la seconde plaque (11).
7. Structure de support selon l'une quelconque des revendications précédentes, dans laquelle
le premier élément de raccordement (5) et le second élément de raccordement (6) comprennent
des lames métalliques élastiques respectives.
8. Structure de support selon l'une quelconque des revendications précédentes, dans laquelle
les premières extrémités (5a, 6a) du premier élément de raccordement (5) et du second
élément de raccordement (6) forment des sièges (13, 14) pour loger les parties des
côtés respectifs de la plaque thermiquement isolante (2).
9. Structure de support selon l'une quelconque des revendications précédentes, dans laquelle
les premières extrémités (5a, 6a) du premier élément de raccordement (5) et du second
élément de raccordement (6) sont pliées vers les secondes extrémités (5b, 6b) respectives,
sur le côté faisant face à la plaque thermiquement isolante (2), à l'usage.
10. Module d'isolation thermique de chambre de combustion de turbine à gaz comprenant
une plaque thermiquement isolante (2) et au moins une structure de support (3) selon
l'une quelconque des revendications précédentes, montée sur la plaque thermiquement
isolante (2).
11. Module d'isolation thermique selon la revendication 10, dans lequel la plaque thermiquement
isolante (2) a des sièges de fixation (2b) sur les côtés opposés ; et les premières
extrémités (5a, 5b) du premier élément de raccordement (5) et du second élément de
raccordement (6) sont montées sur des sièges de fixation (2b) respectifs de la plaque
thermiquement isolante (2).
12. Module d'isolation thermique selon la revendication 10 ou 11, comprenant une pluralité
de structures de support (3) selon l'une quelconque des revendications 1 à 9 et montées
sur la plaque thermiquement isolante (2) et agencées parallèlement entre elles.
13. Module d'isolation thermique selon l'une quelconque des revendications 10 à 12, dans
lequel la plaque thermiquement isolante (2) a une face de travail sensiblement continue
et uniforme.
14. Chambre de combustion de turbine à gaz comprenant un carter toroïdal (21) s'étendant
autour d'un axe (A) et un revêtement thermiquement isolant (25) fixé au carter (21)
ayant au moins un module d'isolation thermique (1) selon l'une quelconque des revendications
10 à 13, dans laquelle le module d'isolation thermique (1) est fixé sur le carter
(21) avec la broche filetée (15) montée à travers un trou (31) dans le carter (21)
et l'écrou (16) est monté sur la broche filetée (15) depuis l'extérieur du carter
(21).
15. Chambre de combustion selon la revendication 14, dans laquelle le revêtement thermiquement
isolant (25) comprend une pluralité de plaques thermiquement isolantes supplémentaires
(26) montées sur la première coque (22), le long d'un cercle autour de l'axe (A) ;
et dans laquelle le module d'isolation thermique (1) forme une surface sensiblement
continue avec les plaques thermiquement isolantes supplémentaires (26).
16. Chambre de combustion selon la revendication 15, dans laquelle une surface interne
(22a) de la première coque a des guides circonférentiels (28) pour loger des éléments
de raccordement (30) afin de fixer les plaques thermiquement isolantes supplémentaires
(26) et un siège (32) dans lequel le dispositif de serrage (7) du module d'isolation
thermique (1) est logé.
REFERENCES CITED IN THE DESCRIPTION
This list of references cited by the applicant is for the reader's convenience only.
It does not form part of the European patent document. Even though great care has
been taken in compiling the references, errors or omissions cannot be excluded and
the EPO disclaims all liability in this regard.
Patent documents cited in the description