ATBECHDEDKESFRGBGRITLILUNLSEMCPTIESILTLVFIROMKCYALTRBGCZEEHUPLSKBAHRIS..MTNORS......................
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DIM360 Ver 2.15 (14 Jul 2008) - 1100000/0
2211109
EUROPEAN PATENT APPLICATION
A1
20100728
EP
09151189.9
20090123
en
en
en
20100728
201030
20100728
201030
F23R 3/28 20060101AFI20090706BHEP
F23R 3/14 20060101ALI20090706BHEP
de
Brenner einer Gasturbine und Verfahren zum Mischen eines Kraftstoffs mit einem gasförmigen Strom
en
Burner of a gas turbine and method for mixing a fuel with a gaseous flow
fr
Brûleur de turbine à gaz et procédé pour mélanger un carburant avec un flux gazeux
1
Alstom Technology Ltd
100075247
B08/117-0 EP
Brown Boveri Strasse 7
5400 Baden
CH
Ciani, Andrea
Neugasse 31
8005, Zürich
CH
Eroglu, Adnan
Zelglistrasse 9
5417, Untersiggenthal
CH
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
SE
SI
SK
TR
AL
BA
RS
The burner (1) of a gas turbine has a duct (2) that comprises at least a vortex generator (3) and downstream of it a plurality of nozzles (5) for injecting a fuel within the duct (2). The nozzles (5) are arranged along the wall of the duct (2) and are arranged for injecting fuel toward the inner of the duct (2). The present invention also relates to a method for mixing a fuel with a gaseous flow in such a burner.

Technical Field
The present invention relates to a burner of a gas turbine and a method for mixing the fuel with a gaseous flow.
In particular the present invention refers to a burner wherein the fuel is injected in a hot gases flow and spontaneously auto ignites after a delay time from injection.

Background art
Burners wherein auto ignition of fuel occurs are typically the second burners of sequential combustion gas turbines.
In these gas turbines a compressor compresses a main air flow and feeds it to a first burner where a fuel is injected to generate a mixture. Afterwards the mixture is combusted and then expanded in a high pressure turbine. The hot gases flow coming from the high pressure turbine (that are still rich in oxygen) pass through a second burner where further fuel is injected to form a mixture. This mixture is combusted and then expanded in a low pressure turbine.
The second burner of the sequential combustion gas turbine has a duct (often square, quadrangular or trapezoidal in shape) enclosing four static vortex generators made of tetraedrical elements connected to the walls of the duct.
Downstream of the vortex generators the burner has a lance made of a straight tubular element placed perpendicularly to the direction of the hot gases flow and provided with a terminal portion that is parallel to the direction of the hot gases flow. The terminal portion has usually four nozzles that inject the fuel.
During operation the hot gases flow passes trough the vortex generators increasing its vorticity; afterwards the fuel is injected such that it mixes with the hot gases flow.
Nevertheless, this traditional burner is only able to achieve a mixing quality that is not optimal; this negatively influences the NOx emissions.
In addition traditional burners cause pressure drops in the hot gases flow passing through them that are usually very high and should be reduced to improve the engine efficiency.
Moreover, as the velocity in the vortices core is very low, traditional burners have a low flashback margin.
US2008/0148736 discloses a burner that has a duct containing a rotating hub. The rotating hub has airfoils that are provided, in a zone close to their leading edges, with nozzles for injecting the fuel.
This burner let the pressure drop be reduced and the mixing quality be improved; nevertheless a further improvement of these features is desired.
In fact the hub generates a wake that causes pressure drop, bad mixing (with high NOx emissions) and high flashback risks.
Moreover, as the fuel is injected close to the leading edges of the airfoils, there is the risk that it auto ignites before leaving the burner and entering the combustion chamber; this would severely impair the structure of the burner.

Summary of the Invention
The technical aim of the present invention is therefore to provide a burner and a method by which the said problems of the known art are eliminated.
Within the scope of this technical aim, an object of the invention is to provide a burner and a method with which mixing quality is improved and the NOx emissions are reduced.
Another object of the invention is to provide a burner and a method by which the pressure drop is reduced.
A further object of the present invention is to provide a burner and a method which let the risk of auto ignition of the fuel within the burner (flashback) be greatly reduced.
The technical aim, together with these and further objects, are attained according to the invention by providing a burner and a method in accordance with the accompanying claims.

Brief Description of the drawings
Further characteristics and advantages of the invention will be more apparent from the description of a preferred but non-exclusive embodiment of the burner and the method according to the invention, illustrated by way of nonlimiting example in the accompanying drawings, in which:
- Figure 1 is a schematic view of a burner of the invention;
- Figure 2 is a cross section along line II-II of figure 1;
- Figure 3 is an enlarged cross section along line III-III of figure 1;
- Figure 4 is a top view of the duct with an aperture for inserting the lance therein;
- Figure 5 is a schematic perspective view of an airfoil being a vortex generator of figure 1;
- Figures 6-8 are respectively two cross sections along lines VI-VI and VII-VII and a side view in direction of arrow VIII of the airfoil of figure 5;
- Figure 9 is a front view in direction of arrow IX of the airfoil of figure 5; and
- Figure 10 is a different embodiment of the vortex generator comprising two airfoils.

Detailed Description of the Invention
With reference to the figures, these show a burner of a gas turbine overall indicated by the reference number 1.
The burner 1 is the second burner of a sequential gas turbine and has a duct 2 that has a circular cross section and comprises a vortex generator 3 and, downstream of it, a plurality of nozzles 5 for injecting a fuel within the duct 2.
The nozzles 5 are of hybrid type and in this respect they are arranged to inject oil (from a central aperture), gas (from an intermediate annular aperture encircling the central aperture) and shielding air (from an outer annular aperture encircling the central and the intermediate annular aperture).
The nozzles 5 are arranged along the wall of the duct 2 and, in addition, are arranged for injecting fuel toward the inner of the duct 2.
As shown in figure 1-3, the nozzles 5 have their axes 6 toward a longitudinal axis 7 the duct 2.
Preferably, the nozzles 5 are located on a lance 9 that is annular (i.e. toroidal) in shape and is housed in the duct 2 with a portion lying on the wall of the same duct 2, and with its central aperture facing the vortex generator 3 such that the hot gases flow may pass through it.
In a first embodiment, the duct 2 is provided with a longitudinal aperture 11 such that the lance 9 can be introduced within the duct 2 via this longitudinal aperture 11 and subsequently (once it is inside the duct 2) rotated to be transversal housed within the duct 2 (i.e. to be placed in its operating conditions as shown in figure 3).
In a different embodiment (not shown in the figures) the duct is provided with a transversal aperture for letting the lance 9 be inserted within the duct 2.
The vortex generator 3 comprises an airfoil 13 rotating about the longitudinal axis 7 of the duct 2.
The airfoil 13 has a leading edge 15 (with 0 angle of attack) and a trailing edge 16 that are tilted with each other.
In particular the leading edge 15 of the airfoil 13 lay radially within the duct 2 and the trailing edge 16 of the airfoil 13 is straight but not radial within the duct 2.
Figure 6 shows a central cross section of the airfoil 13; this central cross section is symmetrical with respect to the rotation axis of the airfoil that overlaps the longitudinal axis 7 of the duct 2; moreover also the cord 18 of the airfoil (i.e. the line between the leading edge 15 and the trailing edge 16) overlaps the longitudinal axis 7 of the duct 2.
The other sections are not symmetric but, as the leading edge 15 and the trailing edge 16 are both straight but tilted with each other, they have the cord 18 that is tilted with respect to the rotation axis of the airfoil (this axis overlaps the axis 7).
In particular, the cross sections in each longitudinal section of the airfoil (i.e. the cross section similar to that of figures 6-7) has the angle between the rotational axis of the airfoil (overlapping the axis 7) and the cord 18 that increases with the distance from the rotation axis.
Advantageously, the duct 2 has an inlet portion 19 that is convergent; the inlet portion is preferably made of a trapezoidal cross section at its larger end (this is due to the fact that the flow comes from the high pressure turbine) and a circular cross section at its smaller end.
The outlet portion 20 has a diffuser.
The operation of the burner of the invention is apparent from that described and illustrated and is substantially the following.
The hot gases flow coming from the high pressure turbine enters the duct 2 through the convergent inlet portion 19; in this zone of the duct the hot gases flow is straightened and stabilised.
Thus the hot gases flow passes around the rotating airfoil that makes it increase its vorticity by generating a vortex that rotates about the longitudinal axis 7 of the duct 2 (see arrows F).
Advantageously there are no wakes in the duct 2 where the hot gases flow may have a very low velocity.
Afterwards the hot gases flow (rotating about the axis 7) passes through the lance 9, and the nozzles 5 inject the gaseous or liquid fuel (i.e. the gas or the oil eventually with the shielding air) according to the operating stage.
Advantageously the fuel (both liquid and gaseous fuel) is injected from a plurality of nozzles (in the embodiment shown the nozzles 5 are eight in number, but in different embodiments the nozzles can also be much more than eight, for example sixteen or even more); the great number of nozzles and the fact that they are placed along all the perimeter of the duct and also the fact that the fuel is injected toward the inner of the duct lets the fuel be distributed in the whole cross section of the duct 2.
In addition, the rotating velocity of the hot gases flow and the velocity of the fuel injected toward the centre of the duct 2 are such that while the hot gases flow rotate of an angle A between two next nozzles 5, the fuel goes from the nozzle 5 to the axis 7 of the duct 2; this further increases fuel distribution over the whole cross section of the duct 2.
Moreover, thanks to the structure with rotating airfoil as a vortex generator and annular lance, when passing through the duct 2 the hot gases flow generates no wakes or zones where the velocity is low, but it generates a single vortex rotating about the axis 7 of the duct.
Advantageously, the zone of the hot gases flow having the lowest velocity (i.e. the zone along the axis 7 of the duct) is the last to be reached by the fuel; this improves flashback margin.
Afterwards, the hot gases flow flows within the duct 2 up to the exit 2 and the entrance of the combustion chamber where the fuel is combusted; in the zone between the lance and the combustion chamber (mixing zone) the hot gases flow further mixes with the fuel to achieve an optimal mixing quality.
The present invention also relates to method for mixing a fuel with a gaseous flow passing through the duct of the burner of the gas turbine.
The method comprises generating at least a vortex within the gaseous flow and radially injecting a fuel toward the inner of the duct.
Advantageously the vortices are generated making the gaseous flow rotate around the axis 7 of the duct 2 and, during rotation, while the gas flow sweep an angle A between two next nozzles 5, the fuel sweeps the distance B between the nozzle 5 from which it was injected and the axis 7 of the duct 2.
Modifications and variants in addition to those already stated are possible, for example figure 10 shows a different vortex generator that could be used in the burner 1 of the invention.
In particular the vortex generator of figure 10 is made of two airfoils 13 each having the features of the airfoil already described.
These airfoils 13 have the leading edges at right angle with each other and the trailing edges tilted in the same direction with respect to the leading edges.
The burner provided with this vortex generator having two airfoils has the same operation already described for the burner with vortex generator with one single airfoil.
In practice the materials used and the dimensions can be chosen at will according to requirements and to the state of the art.

Reference numbers
- 1 burner
- 2 duct
- 3 vortex generator
- 5 nozzles
- 6 axes of the nozzles
- 7 longitudinal axis of the duct
- 9 lance
- 11 longitudinal aperture of the duct
- 13 airfoil
- 15 leading edge of the airfoil
- 16 trailing edge of the airfoil
- 18 cord of the airfoil
- 19 inlet portion of the duct
- 20 outlet portion of the duct
- A angle between two adjacent nozzles
- B distance between a nozzle and the axis of the duct
- F vortex
1. Burner (1) of a gas turbine having a duct (2) that comprises at least a vortex generator (3) and downstream of it a plurality of nozzles (5) for injecting a fuel within the duct (2), characterised in that said nozzles (5) are arranged along the wall of the duct (2) and are arranged for injecting fuel toward the inner of the duct (2).
2. Burner (1) as claimed in claim 1, characterised in that said nozzles (5) have their axes toward the longitudinal axis (7) of the duct (2).
3. Burner (1) as claimed in claim 1, characterised in that said nozzles (5) are located on a lance (9) that is annular in shape.
4. Burner (1) as claimed in claim 3, characterised in that said duct (2) is provided with a longitudinal aperture (11) such that the lance (9) can be introduced within the duct (2) via said longitudinal aperture (11) and subsequently rotated to be transversal housed within the duct (2).
5. Burner (1) as claimed in claim 1, characterised in that said vortex generator (3) comprises at least an airfoil (13) rotating about a longitudinal axis (7) of the duct (2).
6. Burner (1) as claimed in claim 5, characterised in that said airfoil (13) has a leading edge (15) and a trailing edge (16) that are tilted with each other.
7. Burner (1) as claimed in claim 6, characterised in that said leading edge (15) of said airfoil extends radially within said duct (2) and said trailing edge (16) of the airfoil is straight.
8. Burner (1) as claimed in claim 6, characterised in that said airfoil (13) has a symmetrical central cross section.
9. Burner (1) as claimed in claim 1, characterised in that said duct (2) has a circular cross section.
10. Burner (1) as claimed in claim 1, characterised by comprising an inlet convergent portion (19).
11. Burner (1) as claimed in claim 1, characterised by being the second burner of a sequential combustion gas turbine.
12. Method for mixing a fuel with a gaseous flow passing through the duct (2) of a burner (1) of a gas turbine, characterised by generating at least a vortex within the gaseous flow and radially injecting a fuel toward the inner of the duct.
13. A method as claimed in claim 12, characterised in that the vortices are generated making the gaseous flow rotate around the axis (7) of the duct (2).
14. A method as claimed in claim 13, characterised in that, while during rotation the gas flow sweep an angle (A) between two next nozzles (5), the fuel sweeps the distance (B) between the nozzle (5) from which it was injected and the axis (7) of the duct (2).

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
- US
20080148736
A
[0011]