BURNER ASSEMBLY FOR A COMBUSTOR OF A GAS TURBINE POWER PLANT AND COMBUSTOR COMPRISING SAID BURNER ASSEMBLY

Abstract

A burner assembly for a combustor is provided with a pilot burner extending along a longitudinal axis and a premix burner surrounding the pilot burner; the pilot burner being integral with the premix burner.

Claims

1. Burner assembly for a combustor, the burner comprising: a pilot burner extending along a longitudinal axis (A); and a premix burner surrounding the pilot burner; the pilot burner being integral with the premix burner.

2. Burner assembly according to claim 1, wherein the premix burner and the pilot burner are a monolithic body.

3. Burner assembly according to claim 1, wherein the premix burner and the pilot burner are two separated pieces fixed together.

4. Burner assembly according to claim 1, wherein the pilot burner is fixed to an inner surface of the premix burner.

5. Burner assembly according to claim 3, wherein the premix burner comprises: an inlet portion coupled to a fuel supply assembly; and an injection portion extending, when in use, about the longitudinal axis (A) and coupled to the inlet portion.

6. Burner assembly according to claim 5, wherein the injection portion is provided with a first end and a second end, the second end having a second section diameter lower than a first section diameter of the first end and the inlet portion being coupled to the second end.

7. Burner assembly according to claim 5, wherein the pilot burner is fixed to the inlet portion of the premix burner.

8. Burner assembly according to claim 7, wherein the pilot burner is fixed to the inlet portion of the premix burner along at least two contact zones axially displaced.

9. Burner assembly according to claim 4, wherein the pilot burner and the premix burner are fixed together so as to define a sliding interface between the pilot burner and the premix burner.

10. Burner assembly according to claim 9, wherein the sliding interface is defined by an air gap between the pilot burner and an inlet portion of the premix burner.

11. Burner assembly according to claim 1, wherein the pilot burner comprises: at least two concentric conduits, at least one of the two concentric conduits being provided with an extendible portion.

12. Burner assembly according to claim 1, wherein the premix burner comprises: at least one fuel supply conduit provided with a further extendible portion.

13. Combustor for a gas turbine power plant the combustor comprising: the burner assembly claimed in claim 1.

Description

[0028] The present invention will now be described with reference to the accompanying drawings, which illustrate some non-limitative embodiment, in which:

[0029] FIG. 1 is a schematic section view, with parts removed for sake of clarity, of the burner assembly according to the present invention;

[0030] FIG. 2 is a schematic section view, with parts removed for sake of clarity, of the burner assembly according to a second embodiment of the present invention.

[0031] Reference number 1 in FIG. 1 indicate a burner assembly for a combustor 9 of a gas turbine power plant (here only partially illustrated).

[0032] Burner assembly 1 comprises a pilot burner 2 extending along a longitudinal axis A and a premix burner 3 extending about the pilot burner 2.

[0033] Pilot burner 2 and premix burner 3 are coupled to a fuel supply assembly 4 (schematically represented in the attached figures) which is connected to a respective fuel supply circuit (not illustrated). In the non-limiting here disclosed and illustrated, the fuel supply assembly 4 is arranged along the longitudinal axis A. However, variants of the fuel supply assembly 4 can be provided in order to supply the fuel from other sides of the burner assembly 1. For example, fuel supply assembly 4 can comprise metal rigid hoses or/and flexible hoses connected to the pilot burner 2 and to the premix burner 3.

[0034] The pilot burner 2 comprises a lance 5 which is provided with a first conduit 6 supplied, in use, with a first fuel, with a second conduit 7 supplied, in use, with air and with a third conduit 8 supplied, in use, with a second fuel.

[0035] Preferably the first fuel is gas and the second fuel is fuel oil.

[0036] Preferably the first conduit 6, the second conduit 7 and the third conduit 8 are concentric and extends about the longitudinal axis A.

[0037] In the non-limiting example here disclosed, the third conduit 8 extends along the longitudinal axis A, the first conduit 6 extends about the third conduit 8 and the second conduit 7 extends about the first conduit 6.

[0038] The first conduit 6 and the third conduit 8 are supplied with the respective first fuel and second fuel by the fuel supply assembly 4. In particular the fuel is supplied along a flow direction D (indicated by an arrow in FIGS. 1 and 2) towards the inside of the combustor 9.

[0039] The second conduit 7 has an axial length lower than the axial length of the first conduit 6 and the third conduit 8.

[0040] The lance 5 has an end tip 10 which faces inside the combustor 9.

[0041] The lance 5 is schematically represented in the attached drawings. Preferably the lance 5 is provided with a plurality of first nozzles (not illustrated) connected to the first conduit 6, with a plurality of second nozzles (not illustrated) connected to the second conduit 7 and with a plurality of third nozzles (not illustrated) connected to the third conduit 8.

[0042] The lance end tip 10 has preferably a circular section and is provided with a circular edge 15. The end tip 10 comprises an end surface 16 which is defined by a respective end wall 17 and is preferably planar.

[0043] The premix burner 3 extends about the pilot burner 2 and substantially comprises an inlet portion 20 coupled to the supply assembly 4, an injection portion 21 coupled to the inlet portion 20 and an outlet portion 22 coupled to the injection portion 21 and to the combustor 9.

[0044] The inlet portion 20 comprises a fuel supply conduit 23 which is preferably annular and extends about a respective inlet portion of the pilot burner 2.

[0045] The dimensions of the fuel supply conduit 23 are designed so as to allow an easy insertion of the pilot burner 2 into the substantially cylindrical seat defined by the fuel supply conduit 23.

[0046] The fuel supply conduit 23 is supplied with fuel by the fuel supply assembly 4 along a flow direction D (indicated by an arrow in FIGS. 1 and 2) towards the inside of the combustor 9. The fuel supplied to the fuel supply conduit 23 is gas.

[0047] In the fuel supply conduit 23 are arranged a plurality of air inlet channels 24 (represented in dotted lines) which are configured to supply air to the second conduit 7 of the pilot burner 2. The air supplied through the air inlet channels 24 is air collected in a plenum 25 (only partially visible in the drawings) in communication with the outlet of the compressor of the plant.

[0048] The injection portion 21 is preferably defined by a truncated-cone shaped swirler 26 provided with air slots 27 (the air slots are not well visible in the attached drawingsdotted arrows indicate the air flowing through said air slots) and fuel nozzles 28.

[0049] The air slots 27 are supplied with the air collected in the plenum 25 in communication with the outlet of the compressor of the plant.

[0050] Fuel nozzles 28 are supplied with fuel by the fuel supply conduit 23.

[0051] The injection portion 21 is provided with a first end 29a and a second end 29b; the second end 29b having a section diameter lower than the section diameter of the first end 29a.

[0052] The inlet portion 20 is coupled to the second end 29b, while the outlet portion 22 is coupled to the first end 29a.

[0053] Preferably, the injection portion 21 is made by two shells assembled together.

[0054] The outlet portion 22 has preferably a cylindrical shape and is generally defined as CBO (cylindrical burner outlet). The outlet portion 22 is coupled to a wall 31 of the combustor 9.

[0055] The pilot burner 2 and the premix burner 3 are integral.

[0056] In other words, the pilot burner 2 and the premix burner 3 are rigidly fixed together.

[0057] Preferably, the pilot burner 2 is fixed to at least a portion of an inner surface of the premix burner 3. The inner surface of the premix burner 3 is the surface of the premix burner 3 facing, in use, the pilot burner 2.

[0058] In the non-limiting example here disclosed and illustrated, the premix burner 3 and the pilot burner 2 are two separated pieces fixed together. Preferably, the premix burner 3 and the pilot burner 2 are directly fixed together.

[0059] According to an embodiment not illustrated, the premix burner 3 and the pilot burner 2 can be made as a monolithic body. For example, the monolithic body can be obtained by additive manufacturing or by casting processes.

[0060] In detail, the pilot burner 2 is fixed to the inlet portion 20 of the premix burner 3. In particular, the outer surface of the pilot burner 2 is fixed to the inner surface of the inlet portion 20 of the premix burner 3.

[0061] In the non-limiting example illustrated in FIG. 1, the outer surface of the second conduit 7 is fixed to the inner surface of the inlet portion 20.

[0062] Preferably, the outer surface of the second conduit 7 is fixed to the inner surface of the inlet portion 20 at the boundary with the injection portion 21.

[0063] Preferably, the fixing of the pilot burner 2 is made along at least one contact zone 30 (schematically represented in the attached figure by a black dot) of the inner surface of the inlet portion 20.

[0064] The fixing of the pilot burner 2 to the inner surface of the inlet portion 20 can be made, for example, by welding, by bolts or by clamping means, by casting of by additive manufacturing.

[0065] According to a variant illustrated in FIG. 2, the pilot burner 2 and the premix burner 3 are fixed together so as to define a sliding interface 35 between the pilot burner 2 and the inlet portion 20 of the premix burner 3.

[0066] Said sliding interface 35 allows relative axial movements between the pilot burner 2 and the premix burner 3 due to thermal expansions.

[0067] In the non-limiting example here disclosed and illustrated, the sliding interface 35 is defined by an air gap 36 between the pilot burner 2 and the inlet portion 20 of the premix burner 3.

[0068] Preferably, the sliding interface 35 is defined by an air gap 36 between the outer surface of the second conduit 7 and the inner surface of the inlet portion 20 of the premix burner 3.

[0069] The air gap 36 is preferably arranged along the inlet portion 20 near the injection portion 21.

[0070] The outer surface of the pilot burner 2 is fixed to the inner surface of the inlet portion 20 of the premix burner 3.

[0071] In the non-limiting example illustrated in FIG. 2, the outer surface of the first conduit 6 is fixed to the inner surface of the inlet portion 20.

[0072] Preferably, the inner surface of the inlet portion 20 is fixed to the outer surface of the first conduit 6 near the beginning of the second conduit 7.

[0073] Analogously to the embodiment of FIG. 1, the fixing of the pilot burner 2 is made along at least one contact zone 30 (schematically represented in the attached figure by a black dot) of the inner surface of the inlet portion 20.

[0074] The fixing of the pilot burner 2 to the inner surface of the inlet portion 20 can be made, for example, by welding, by bolts or by clamping means, by casting of by additive manufacturing.

[0075] According to one variant not illustrated, the fixing of the pilot burner 2 to the premix burner 3 can be made along at least two contact zones axially displaced in order to ensure a more stable coupling. For example, the pilot burner 2 and the premix burner 3 can be coupled according to a combination of the coupling illustrated in FIG. 1 and FIG. 2.

[0076] With reference to both the embodiments of FIG. 1 and FIG. 2 the first conduit 6, the second conduit 7 and the third conduit 8 of the pilot burner 2 and the fuel supply conduit 23 of the premix burner 3 are provided with at least one extendible portion 37.

[0077] These extendible portions 37 can be provided in order to compensate the axial displacement due to thermal expansions of the first conduit 6, the second conduit 7 and the third conduit 8 of the pilot burner 2 and of the fuel supply conduit 23 of the premix burner 3.

[0078] In the embodiment shown in FIG. 2, wherein a sliding interface 35 is provided between the pilot burner 2 and the inlet portion 20 of the premix burner 3, the second conduit 7 does not require the extendible portion as the thermal expansions are compensated by the sliding between the pilot burner 2 and the inlet portion 20 of the premix burner 3.

[0079] In the non-limiting example here disclosed and illustrated, the extendible portions 37 are defined by a corrugated portions of the conduit.

[0080] According to a variant not illustrated, the extendible portions can be defined by a helical wrapped portion of the conduit.

[0081] Finally, it is clear that modifications and variants can be made to the burner assembly and to the combustor described herein without departing from the scope of the present invention, as defined in the appended claims.