EP1295014B1 - Transition piece for non-annular gas turbine combustion chambers - Google Patents
Transition piece for non-annular gas turbine combustion chambers Download PDFInfo
- Publication number
- EP1295014B1 EP1295014B1 EP01956465A EP01956465A EP1295014B1 EP 1295014 B1 EP1295014 B1 EP 1295014B1 EP 01956465 A EP01956465 A EP 01956465A EP 01956465 A EP01956465 A EP 01956465A EP 1295014 B1 EP1295014 B1 EP 1295014B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- transition piece
- gas turbine
- combustion chambers
- stage
- axis
- 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.)
- Expired - Lifetime
Links
- 230000007704 transition Effects 0.000 title claims description 52
- 238000002485 combustion reaction Methods 0.000 title claims description 33
- 239000000463 material Substances 0.000 claims description 6
- 229910001347 Stellite Inorganic materials 0.000 claims description 4
- AHICWQREWHDHHF-UHFFFAOYSA-N chromium;cobalt;iron;manganese;methane;molybdenum;nickel;silicon;tungsten Chemical compound C.[Si].[Cr].[Mn].[Fe].[Co].[Ni].[Mo].[W] AHICWQREWHDHHF-UHFFFAOYSA-N 0.000 claims description 4
- 229910001235 nimonic Inorganic materials 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 45
- 239000003344 environmental pollutant Substances 0.000 description 4
- 231100000719 pollutant Toxicity 0.000 description 4
- 239000002184 metal Substances 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 238000003490 calendering Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 230000004936 stimulating effect Effects 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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
- 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 transition piece for non-annular gas turbine combustion chambers.
- gas turbines comprise a compressor, to which air from the external environment is supplied in order to pressurise the compressor.
- the compressed air passes into a series of combustion chambers which end in a nozzle, into each of which an injector supplies fuel, which is mixed with the air in order to form a mixture of combustible air to be burnt.
- the burnt gases are conveyed towards the turbine, which transforms the enthalpy of the burnt gases in the said combustion chamber into mechanical energy which is available to a user.
- transition pieces in a gas turbine are substantially tubular elements, each of which is used to connect a combustion chamber, which belongs to the combustion system of the gas turbine, to the first stage of the said gas turbine.
- combustion chambers comprise a plurality of elements with a generally cylindrical shape, which are provided with nozzles disposed around an annular development.
- transition pieces are disposed with an annular development, in order to direct the flow of hot burnt gases from the combustion chambers to the first stage of the gas turbine.
- the transition pieces have an upstream aperture for the flow of gas, which is generally cylindrical, and is used to receive the flow of gas directly from the corresponding combustion chamber, and are configured in a longitudinal direction such that their downstream ends comprise arcuate segments which open towards the first stage of the gas turbine.
- transition pieces can direct the flow of gas with a high level of enthalpy obtained from spaced, generally cylindrical flow configurations, towards arcuate segments which form a ring-type configuration relative to the first stage of the gas turbine.
- the document EP-A-753 704 discloses a transition piece having a mount connector device and a body with a lead in axis parallel to the gas turbine axes.
- these components comprise the combustion chamber, the nozzles and the transition pieces, and are the ones which are subjected to the highest temperatures.
- the combustion system since the combustion system has an energising function in relation to the thermal carrier fluid, it is the true heart of the turbine engine, and thus defines its level of emission, and, according to the service life of its own components, also defines the intervals of functioning between machine stoppages, which are necessary in order to carry out inspections of the combustion chambers.
- a major technical problem therefore consists substantially of determining solutions which permit achievement of maximum satisfaction of the client for the three aforementioned aspects, all by means of innovative creations which are economically acceptable.
- stellite 6 deposited onto elements which may become worn by relative vibratory motion, and of super-alloys with a nickel/cobalt base, with high levels of mechanical characteristics and of resistance to corrosion at high temperatures.
- the original system having six combustion chambers, arranged in two rows of three parallel chambers stacked on both sides of the machine, in an arrangement at right-angles to the machine axis, with interposition of 90° connection elbows between the liners and transition pieces, has thus been replaced by an arrangement characterised by chambers inclined by only a few degrees in relation to the machine axis, and insertion of the liners directly in the transition piece, and therefore without the need for further connection elements.
- the object of the present invention is therefore to provide a transition piece for non-annular gas turbine combustion chambers, which permits optimisation of the performance in operation.
- a further object of the invention is to provide a transition piece for non-annular gas turbine combustion chambers, which permits improved efficiency in operation.
- Another object of the invention is to provide a transition piece for non-annular gas turbine combustion chambers, which permits a longer service life of the machine.
- a further object of the invention is to provide a transition piece for a non-annular gas turbine combustion chamber system, which generates fewer pollutant emissions.
- a transition piece for non-annular gas turbine combustion chambers comprising a body which has a cylindrical section, relative to a first terminal end, which ends with an aperture for connection to a combustion chamber, and a second terminal end, which is connected to the first stage of a gas turbine, having a projecting connection arm, for support on the turbine stator, wherein the said projecting connection arm makes it possible to obtain a lead-in axis with an angle of between 5° and 7° relative to an axis, which is parallel to the axis of the machine, and is perpendicular to the plane on which there lies the frame for interfacing of the transition piece with the ring of nozzles which belong to the first stage of the said gas turbine.
- the transition piece has a support arm, with a circular or elliptical base, which is present at the said second terminal end, and surrounds the flow aperture of the said transition piece, wherein the said support arm with a circular or elliptical base has an upper side and a lower side, for its own connection to the first stage of the said gas turbine.
- the cylindrical section relative to the first terminal end, has an anti-wear deposit made of Stellite 6 or another, similar material.
- a deposit of the TBC type is provided on the entire inner surface of the said transition piece, in order to reduce the temperature of the metal.
- the distance between the centre of the lead-in of the said transition piece and the support plane of the flange for anchorage to the stator of the said gas turbine is between 350 mm and 380 mm.
- the body of the transition piece can be made of Nimonic 263 or of Hastelloy-X.
- transition piece according to the present invention for non-annular gas turbine combustion chambers, is indicated globally by the reference number 10.
- the transition piece 10 consists of a body 11, which receives upstream the flow of burnt gases, directly from the corresponding combustion chamber 25, and is configured longitudinally such as to have a downstream end which opens towards the first stage 17 of the gas turbine 18.
- the body 11 of the transition piece 10 has a cylindrical section 13, relative to a first terminal end, which ends with an aperture 14 for connection to a combustion chamber 25.
- the body 11 of the transition piece 10 also has a second terminal end 16, which is connected to the first stage 17 of a gas turbine 18, and thus has a flow aperture 15.
- the transition piece 10 thus consists of a body 11, which is provided with a support arm, with a circular or elliptical base, which is present at the second terminal end 16, and surrounds the flow aperture 15.
- the support arm with a circular or elliptical base has an upper side 20 and a lower side 21.
- the body 11 is provided with characteristics of resilience, such as to minimise the stresses associated with its anchorage onto the stator of the said gas turbine 18.
- the body 11 is preferably made of Nimonic 263, or, alternatively, of Hastelloy-X, and is produced in a single component part, indicated by the reference number 11, which reduces the parts necessary and the assembly time, and thus permits considerable savings.
- the cylindrical section 13, relative to the first terminal end, has an anti-wear deposit made of Stellite 6, or of another material homologous with that used on the Hula Seals of the liners.
- a deposit of the TBC type is provided on the entire inner surface of the body 11 of the transition piece 10, in order to reduce the temperature of the metal.
- the transition piece 11 also has a projecting connection arm, indicated as a whole by the reference number 22, for support on the turbine stator.
- the projecting connection arm 22 also has a hole 30, for its own connection to the first stage of the gas turbine 18, and a centring pin 31.
- the geometry of the transition piece 11 is thus completely re-shaped, compared with the known art.
- the distance between the centre of the lead-in of the transition piece 10 and the support plane of the flange for anchorage to the stator of the gas turbine is between 350 mm and 380 mm.
- the most significant functioning parameters are: Tmax of the gas ⁇ 1300°C, and Pmax of the gas ⁇ 10 Ata.
- the transition piece 11 thus formed has an optimal geometric profile, which, inter alia, makes it possible to keep the thermal stresses within acceptable limits.
- transition piece 11 makes it possible to obtain increased structural stability, with consequent reduction of the vibratory motion.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gas Burners (AREA)
Description
The present invention relates to a transition
piece for non-annular gas turbine combustion chambers.
As is known, gas turbines comprise a compressor,
to which air from the external environment is supplied
in order to pressurise the compressor.
The compressed air passes into a series of
combustion chambers which end in a nozzle, into each of
which an injector supplies fuel, which is mixed with
the air in order to form a mixture of combustible air
to be burnt.
Subsequently, the burnt gases are conveyed towards
the turbine, which transforms the enthalpy of the burnt
gases in the said combustion chamber into mechanical
energy which is available to a user.
It is also known that the transition pieces in a
gas turbine are substantially tubular elements, each of
which is used to connect a combustion chamber, which
belongs to the combustion system of the gas turbine, to
the first stage of the said gas turbine.
More particularly, the combustion chambers
comprise a plurality of elements with a generally
cylindrical shape, which are provided with nozzles
disposed around an annular development.
Similarly, the transition pieces are disposed with
an annular development, in order to direct the flow of
hot burnt gases from the combustion chambers to the
first stage of the gas turbine.
The transition pieces have an upstream aperture
for the flow of gas, which is generally cylindrical,
and is used to receive the flow of gas directly from
the corresponding combustion chamber, and are
configured in a longitudinal direction such that their
downstream ends comprise arcuate segments which open
towards the first stage of the gas turbine.
This means that the transition pieces can direct
the flow of gas with a high level of enthalpy obtained
from spaced, generally cylindrical flow configurations,
towards arcuate segments which form a ring-type
configuration relative to the first stage of the gas
turbine.
The document EP-A-753 704 discloses a transition piece having a mount
connector device and a body with a lead in axis parallel to the gas turbine axes.
In order to introduce the technical problems which
are faced and solved by means of the present invention,
it should be noted that the continual quest which is in
progress at present, for increases in the performance
of gas turbines, and increases in the intervals between
the various stoppages for maintenance, as well as the
pressing need to reduce to a minimum the pollutant
emissions produced by the gas turbine, necessitates
optimisation of all the components inserted in the so-called
hot gas path.
In particular, these components comprise the
combustion chamber, the nozzles and the transition
pieces, and are the ones which are subjected to the
highest temperatures.
It should be emphasised at this point that, since
the combustion system has an energising function in
relation to the thermal carrier fluid, it is the true
heart of the turbine engine, and thus defines its level
of emission, and, according to the service life of its
own components, also defines the intervals of
functioning between machine stoppages, which are
necessary in order to carry out inspections of the
combustion chambers.
In addition, the requirement to develop the
machines in operation, with increases in the
compression ratios and fire temperatures, are a further
reason for emphasising the criticality of the hot
components.
Reduction of the emissions, with an increase in
the service life of the components, and optionally also
in the efficiency of the system, also constitutes a
general target which undoubtedly has an impact on the
clientele of heavy duty machines, and is a stimulating
technological challenge for the designers.
In particular, in the case of machines which have
had a certain length of service, it is possible to
gather sufficient statistical data to determine the
parameters and details which are critical in achieving
overall improvements, such as to justify the cost of
the design and subsequent marketing, optionally in
uprate packages for the aftermarket.
A major technical problem therefore consists
substantially of determining solutions which permit
achievement of maximum satisfaction of the client for
the three aforementioned aspects, all by means of
innovative creations which are economically acceptable.
In order better to understand the technical
problems which are involved in the present invention,
at this point reference is made to the following state
of the art.
The solutions which are currently used in order to
achieve the three above-described objectives (greater
efficiency, longer service life of the machine, and
fewer pollutant emissions), are not in general combined
in a single product, but are on the other hand
implemented in ranges of alternative components.
In order to increase the service life, and thus
the intervals of inspection of the combustion chambers,
use is generally made of materials, such as stellite 6,
deposited onto elements which may become worn by
relative vibratory motion, and of super-alloys with a
nickel/cobalt base, with high levels of mechanical
characteristics and of resistance to corrosion at high
temperatures.
Use is also made of additions of a ceramic type,
to reduce the temperatures of the metal (for the same
cooling flows), and the design of the components is
being optimised, on the basis of experience acquired.
In the case of known turbine engines, the original
combustion system has been completely redesigned, both
in terms of the overall arrangement and component
elements.
The original system, having six combustion
chambers, arranged in two rows of three parallel
chambers stacked on both sides of the machine, in an
arrangement at right-angles to the machine axis, with
interposition of 90° connection elbows between the
liners and transition pieces, has thus been replaced by
an arrangement characterised by chambers inclined by
only a few degrees in relation to the machine axis, and
insertion of the liners directly in the transition
piece, and therefore without the need for further
connection elements.
In this embodiment, there is thus implementation
of all the solutions known in the present state of the
art, for the three above-described objectives
(efficiency, service life of the machine, and fewer
pollutant emissions), such as to obtain a unit device
which combines the advantages thus accumulated.
The object of the present invention is therefore
to provide a transition piece for non-annular gas
turbine combustion chambers, which permits optimisation
of the performance in operation.
A further object of the invention is to provide a
transition piece for non-annular gas turbine combustion
chambers, which permits improved efficiency in
operation.
Another object of the invention is to provide a
transition piece for non-annular gas turbine combustion
chambers, which permits a longer service life of the
machine.
A further object of the invention is to provide a
transition piece for a non-annular gas turbine
combustion chamber system, which generates fewer
pollutant emissions.
These objects and others are obtained by a
transition piece for non-annular gas turbine combustion
chambers, comprising a body which has a cylindrical
section, relative to a first terminal end, which ends
with an aperture for connection to a combustion
chamber, and a second terminal end, which is connected
to the first stage of a gas turbine,
having a projecting connection arm, for support on
the turbine stator, wherein the said projecting
connection arm makes it possible to obtain a lead-in
axis with an angle of between 5° and 7° relative to an
axis, which is parallel to the axis of the machine, and
is perpendicular to the plane on which there lies the
frame for interfacing of the transition piece with the
ring of nozzles which belong to the first stage of the
said gas turbine.
According to a preferred embodiment of the present
invention, the transition piece has a support arm, with
a circular or elliptical base, which is present at the
said second terminal end, and surrounds the flow
aperture of the said transition piece, wherein the said
support arm with a circular or elliptical base has an
upper side and a lower side, for its own connection to
the first stage of the said gas turbine.
According to a preferred embodiment of the present
invention, the cylindrical section, relative to the
first terminal end, has an anti-wear deposit made of
Stellite 6 or another, similar material.
In addition, a deposit of the TBC type is provided
on the entire inner surface of the said transition
piece, in order to reduce the temperature of the metal.
According to a further preferred embodiment of the
present invention, the distance between the centre of
the lead-in of the said transition piece and the
support plane of the flange for anchorage to the stator
of the said gas turbine is between 350 mm and 380 mm.
According to a further preferred embodiment of the
present invention, the body of the transition piece can
be made of Nimonic 263 or of Hastelloy-X.
Further characteristics of the invention are
defined in the claims attached to the present patent
application.
Further objects and advantages of the present
invention, as well as its structural and functional
characteristics, will become apparent from the
following description and the attached drawings, which
are provided purely by way of explanatory, non-limiting
example, and in which:
- figure 1 represents a view, partially in cross-section, of a gas turbine to which there is fitted the transition piece according to the present invention, for non-annular gas turbine combustion chambers;
- figure 2 represents a plan view of a transition piece according to the present invention, for non-annular gas turbine combustion chambers;
- figure 3 represents a view in cross-section according to the plane III-III, of the transition piece in figure 2;
- figure 4 represents a front view of the transition piece in figures 2-3; and
- figure 5 represents a view in cross-section of a detail belonging to the transition piece in figures 2-4.
With particular reference to the aforementioned
figures, the transition piece according to the present
invention, for non-annular gas turbine combustion
chambers, is indicated globally by the reference number
10.
The transition piece 10 consists of a body 11,
which receives upstream the flow of burnt gases,
directly from the corresponding combustion chamber 25,
and is configured longitudinally such as to have a
downstream end which opens towards the first stage 17
of the gas turbine 18.
More particularly, the body 11 of the transition
piece 10 has a cylindrical section 13, relative to a
first terminal end, which ends with an aperture 14 for
connection to a combustion chamber 25.
The body 11 of the transition piece 10 also has a
second terminal end 16, which is connected to the first
stage 17 of a gas turbine 18, and thus has a flow
aperture 15.
The transition piece 10 thus consists of a body
11, which is provided with a support arm, with a
circular or elliptical base, which is present at the
second terminal end 16, and surrounds the flow aperture
15.
In particular, the support arm with a circular or
elliptical base has an upper side 20 and a lower side
21.
The body 11 is provided with characteristics of
resilience, such as to minimise the stresses associated
with its anchorage onto the stator of the said gas
turbine 18.
In addition, the body 11 is preferably made of
Nimonic 263, or, alternatively, of Hastelloy-X, and is
produced in a single component part, indicated by the
reference number 11, which reduces the parts necessary
and the assembly time, and thus permits considerable
savings.
The cylindrical section 13, relative to the first
terminal end, has an anti-wear deposit made of Stellite
6, or of another material homologous with that used on
the Hula Seals of the liners.
In addition, a deposit of the TBC type is provided
on the entire inner surface of the body 11 of the
transition piece 10, in order to reduce the temperature
of the metal.
The transition piece 11 also has a projecting
connection arm, indicated as a whole by the reference
number 22, for support on the turbine stator.
At its own terminal end, the projecting connection
arm 22 also has a hole 30, for its own connection to
the first stage of the gas turbine 18, and a centring
pin 31.
The geometry of the transition piece 11 is thus
completely re-shaped, compared with the known art.
In fact, it has a lead-in axis with an angle of
between 5° and 7°, relative to an axis which is
parallel to the axis of the machine, and is
perpendicular to the plane on which there lies the
frame for interfacing of the transition piece 10 with
the ring of nozzles which belong to the first stage 17
of the gas turbine 18.
In addition, it can be noted that the distance
between the centre of the lead-in of the transition
piece 10 and the support plane of the flange for
anchorage to the stator of the gas turbine, is between
350 mm and 380 mm.
In particular, according to the invention
described, the most significant functioning parameters
are: Tmax of the gas < 1300°C, and Pmax of the gas < 10
Ata.
The description provided makes apparent the
characteristics and advantages of the transition piece
which is the subject of the present invention, for non-annular
gas turbine combustion chambers.
The following concluding considerations and
comments are now provided, in order to define the said
advantages more clearly and accurately.
In particular, the elimination of the intermediate
elbows, with the arrangement of the combustion chambers
in the gap between the flanging on the stator of the
turbine and the compressor suction air feed pipe (which
is further limited in the lower area by the presence of
the front support fork of the machine), in association
with the provision of new liners with low LHE emission,
with dilution air feed holes in the head, and
calendered Hula seals with anti-wear material
deposited, have led to the re-design of the transition
piece, with materials used and a configuration which
reflect the best which can be obtained for industrial
gas turbines.
Since this application is designed for the
aftermarket, and thus has pre-defined constraints of
geometries and functional parameters, the design of the
component elements, and their integration in the
system, has led to the development of details which are
innovative in terms of design and functionality.
In view of the operative conditions of the machine
for which this application is planned, there has been
definition of the specific geometry parameters
necessary in order to obtain the functional
characteristics required for integration of the
combustion system as a whole.
The transition piece 11 thus formed has an optimal
geometric profile, which, inter alia, makes it possible
to keep the thermal stresses within acceptable limits.
The particular design of the transition piece 11
described makes it possible to obtain increased
structural stability, with consequent reduction of the
vibratory motion.
To summarise, a transition piece for non-annular
gas turbine combustion chambers has been produced,
which makes it possible also to obtain the significant
advantages of ease of fitting and removal, as well as
of improved overall mechanical reliability and
efficiency of the machine to which it is fitted.
The theoretical and experimental results have been
so satisfactory, that they show that the system can be
used on widely distributed gas turbines.
It is apparent that many variations can be made to
the transition piece which is the subject of the
present invention, for non-annular gas turbine
combustion chambers, without departing from the
principles of novelty which are inherent in the
inventive concept illustrated.
Finally, it is apparent that, in the practical
embodiment of the invention, any forms and dimensions
can be used for the details illustrated, according to
requirements, and can be replaced by others which are
equivalent from a technical point of view.
The scope of the invention is defined by the
attached claims.
Claims (5)
- Transition piece (10) for connecting non-annular gas turbine combustion chambers to first stages of a gas turbine, comprising a tubular body (11) which has a cylindrical section (13), relative to a first terminal end, which ends with a first aperture (14) for connection to a combustion chamber (25), and a second terminal end (16), for connection to the first stage (17) of a gas turbine (18), comprising a mount connector device (22) provided on the transition piece (10) and comprising a tubular projection protruding away from the body and curved for securing the transition piece (10) to said first stage (17) of the gas turbine (18), the body (11) having a lead-in axis with an angle of between 5° and 7° relative to an axis which is parallel to the intended axis of the machine, and is perpendicular to the plane on which there lies a frame for interfacing of the said transition piece (10) with the ring of nozzles belonging to the first stage of the said gas turbine (18).
- A transition piece (10) according to claim 1, characterised in that said cylindrical section (13) has an anti-wear deposit, made of Stellite 6 or another similar material at the first aperture (14)
- A transition piece according to claim 1, characterised in that a deposit of the TBC type is provided on the entire inner surface of the said transition piece (10),
- A transition piece according to clam 1, characterised in that said tubular body (11) is made of Nimonic 263 or Hastelloy-X
- A transition piece according to claim 1, characterised in that the distance between the centre of the lead-in of the said transition piece (10) and the support plane of the flange for anchorage to the stator of the said gas turbine (18), is between 350 mm and 380 mm.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| ITMI001362 | 2000-06-16 | ||
| IT2000MI001362A IT1317978B1 (en) | 2000-06-16 | 2000-06-16 | TRANSITION PIECE FOR COMBUSTION CHAMBERS OF NONANULAR GAS TURBINES. |
| PCT/EP2001/006484 WO2001096712A1 (en) | 2000-06-16 | 2001-06-08 | Transition piece for non-annular gas turbine combustion chambers |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1295014A1 EP1295014A1 (en) | 2003-03-26 |
| EP1295014B1 true EP1295014B1 (en) | 2005-11-23 |
Family
ID=11445283
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01956465A Expired - Lifetime EP1295014B1 (en) | 2000-06-16 | 2001-06-08 | Transition piece for non-annular gas turbine combustion chambers |
Country Status (12)
| Country | Link |
|---|---|
| US (1) | US20030167776A1 (en) |
| EP (1) | EP1295014B1 (en) |
| AR (1) | AR028133A1 (en) |
| AT (1) | ATE310896T1 (en) |
| AU (1) | AU7844301A (en) |
| BR (1) | BR0111577A (en) |
| DE (1) | DE60115236T2 (en) |
| IT (1) | IT1317978B1 (en) |
| MX (1) | MXPA02012451A (en) |
| NO (1) | NO330416B1 (en) |
| RU (1) | RU2275554C2 (en) |
| WO (1) | WO2001096712A1 (en) |
Families Citing this family (32)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7178341B2 (en) * | 2004-06-17 | 2007-02-20 | Siemens Power Generation, Inc. | Multi-zone tubing assembly for a transition piece of a gas turbine |
| US7278254B2 (en) * | 2005-01-27 | 2007-10-09 | Siemens Power Generation, Inc. | Cooling system for a transition bracket of a transition in a turbine engine |
| US8015818B2 (en) * | 2005-02-22 | 2011-09-13 | Siemens Energy, Inc. | Cooled transition duct for a gas turbine engine |
| US7827801B2 (en) * | 2006-02-09 | 2010-11-09 | Siemens Energy, Inc. | Gas turbine engine transitions comprising closed cooled transition cooling channels |
| US8151570B2 (en) * | 2007-12-06 | 2012-04-10 | Alstom Technology Ltd | Transition duct cooling feed tubes |
| US8113003B2 (en) * | 2008-08-12 | 2012-02-14 | Siemens Energy, Inc. | Transition with a linear flow path for use in a gas turbine engine |
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| RU2141078C1 (en) * | 1998-02-02 | 1999-11-10 | Открытое акционерное общество "Авиадвигатель" | Gas turbine cannular-type combustion chamber |
-
2000
- 2000-06-16 IT IT2000MI001362A patent/IT1317978B1/en active
-
2001
- 2001-06-08 US US10/311,251 patent/US20030167776A1/en not_active Abandoned
- 2001-06-08 AU AU78443/01A patent/AU7844301A/en not_active Abandoned
- 2001-06-08 EP EP01956465A patent/EP1295014B1/en not_active Expired - Lifetime
- 2001-06-08 WO PCT/EP2001/006484 patent/WO2001096712A1/en not_active Ceased
- 2001-06-08 RU RU2003101058/06A patent/RU2275554C2/en not_active IP Right Cessation
- 2001-06-08 MX MXPA02012451A patent/MXPA02012451A/en unknown
- 2001-06-08 DE DE60115236T patent/DE60115236T2/en not_active Expired - Lifetime
- 2001-06-08 BR BR0111577-4A patent/BR0111577A/en not_active Application Discontinuation
- 2001-06-08 AT AT01956465T patent/ATE310896T1/en active
- 2001-06-15 AR ARP010102872A patent/AR028133A1/en unknown
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2002
- 2002-12-13 NO NO20025995A patent/NO330416B1/en not_active IP Right Cessation
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| NO330416B1 (en) | 2011-04-11 |
| IT1317978B1 (en) | 2003-07-21 |
| MXPA02012451A (en) | 2003-04-25 |
| NO20025995D0 (en) | 2002-12-13 |
| ITMI20001362A0 (en) | 2000-06-16 |
| DE60115236D1 (en) | 2005-12-29 |
| NO20025995L (en) | 2003-02-13 |
| ATE310896T1 (en) | 2005-12-15 |
| EP1295014A1 (en) | 2003-03-26 |
| BR0111577A (en) | 2003-03-18 |
| DE60115236T2 (en) | 2006-07-27 |
| WO2001096712A1 (en) | 2001-12-20 |
| US20030167776A1 (en) | 2003-09-11 |
| ITMI20001362A1 (en) | 2001-12-16 |
| AU7844301A (en) | 2001-12-24 |
| RU2275554C2 (en) | 2006-04-27 |
| AR028133A1 (en) | 2003-04-23 |
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