This application claims priority to European Application 12175642.3 filed Jul. 10, 2012, the contents of which is hereby incorporated in its entirety.
The present invention relates to the combustion technology. It refers to a combustor arrangement, especially for a gas turbine, according to the preamble of claim 1.
In the past more than 20 years burners with short but effective premixing zones (so-called EV burners: environmental friendly V-shaped burners) have been implemented in several gas turbines of the applicant, with very low NOx levels. In addition to this, three variants of premix technologies have been successfully developed and deployed into those gas turbine engines: the sequential EV burners —a technology that allows premixing of natural gas and oil into a hot exhaust stream to reheat the exhaust gases of a first high pressure turbine; the MBtu EV burners that are used to burn syngas in a premix flame with low NOx emissions; and the advanced EV burners (AEV) that are capable to prevaporize and premix liquid fuel prior to combustion and burn it with very low NOx emissions without water injection.
Document EP 0 851 172 A2 discloses an exemplary EV burner of the double-cone type, for operating a combustion chamber with a liquid and/or gaseous fuel, whereby the combustion air required for this purpose is directed through tangential air-inlet ducts into an interior space of the burner. This directing of the flow results in a swirl flow in the interior space, which swirl flow induces a backflow zone at the outlet of the burner. In order to stabilize the flame front forming there, at least one zone is provided at each sectional body forming the burner, within which zone inlet openings are provided for the injection of supplementary air into the swirl flow. Due to this injection, a film forms at the inner wall of the sectional bodies, which film prevents the flame from being able to flashback along the inner wall of the sectional bodies into the interior space of the burner.
Document EP 2 423 597 A2 shows another exemplary EV burner in the form of a double-cone burner, which has two partial cone shells which are arranged nested one inside the other, forming air inlet ducts between them, through which combustion air from the outside flows into a conical inner space of the premix burner. Linear rows of holes of injection openings, which extend transversely to the flow direction of the combustion air, are arranged on the outer walls of the air inlet ducts and through which a gaseous fuel is injected into the combustion air which flows past transversely to them.
Document DE 195 45 310 A1 discloses a further pre-mixing burner consisting of a hollow cone with an outer and inner cone casing. At least two inlet ducts run at a tangent to the inner cone casing and are positioned along a straight cone casing line. The part cone axes of the part shells formed lie on the same cone axis. The pre-mixing burner is divided into at least two, for example four, parts containing the inlet ducts so as to swirl the combustion air. A fuel nozzle is positioned at the cone tip for injecting liquid fuel.
Document EP 0 704 657 A2 describes a combustor arrangement, which is shown in
A combustion chamber 12 adjoins the end of the mixing tube 14, there being a jump in cross-section between the two cross-sections of flow. Only here does a central backflow zone form, which has the properties of a flame retention baffle. The combustion chamber 12 has a front panel 13 with an opening for receiving the end of the mixing tube 14.
As shown in
The gas turbine burner is usually mounted to the combustion chamber such that it can move in axial direction to compensate for thermal expansion. Leakages through the seals applied between the burner and the front panel of the combustion chamber are close to the flame and cause disturbances to the oxidation process. An additional problem is caused by the approach flow to the burner which is subject to flow disturbances due to the narrow space within the combustor hood.
Thus, the current state-of-the-art distinguishes between the front panel 13 of the combustion chamber 12 and the burner 11. To minimize air leakages, a seal is applied, which however is not tight, since the burner 11 and combustion chamber 12 are subject to large temperature changes and the burner 11 must be axially movable with regard to the front panel 13. Since this seal is close to the flame at the exit of the burner the leakage air is disturbing the oxidation process of the flame by local flame quenching effects. To even out the approach flow, currently, a sieve is shrouded around the burner, however, causing a pressure drop to the air flow.
It is an object of the present invention to provide a combustor arrangement, which avoids the disadvantages of known arrangements and combines a wide range of axial variation of the burner with a minimized influence of the leakage air flow on the oxidation process within the flame.
This and other objects are obtained by a combustor arrangement according to claim 1
The combustor arrangement according to the invention comprises a combustion chamber with a front panel, and a premix burner of the multi-cone type, which is connected to said front panel though an elongated mixing zone in an axially moveable fashion by means of a sealed sliding joint.
It is characterized in that said sealed sliding joint is positioned upstream of said mixing zone.
According to an embodiment of the invention the sealed sliding joint is made up by a coaxial sliding arrangement of a cylindrical burner ring and an essentially cylindrical burner sleeve, whereby said burner ring is fixed to said burner and said burner sleeve is fixed to and part of said front panel, and a seal is provided between said burner ring and burner sleeve.
Specifically, said burner ring is surrounded by said burner sleeve.
More specifically, said burner ring extends upstream of the downstream end of the burner, and the seal is positioned at the upstream end of the burner ring.
According to another embodiment of the invention the burner sleeve has a conically widening burner outlet at the transition to said combustion chamber.
According to a further embodiment of the invention purge air holes are provided in the burner sleeve downstream of the seal to purge the gap between burner ring and burner sleeve with air.
According to just another embodiment of the invention said premix burner comprises a plurality of burner shells, which are arranged around a central burner axis and are parts of a virtual, axially extending common cone, which opens in a downstream direction, whereby said parts are displaced perpendicular to said burner axis such that a tangential slot is defined between each pair of adjacent shells, that each of the shells is equipped with a premix gas channel extending along an axially oriented edge of the respective shell such that a gas can be injected from said premix gas channel through gas injection holes into a stream of air entering the interior of the arrangement of shells through the adjacent slot, that the downstream ends of the shells and premix gas channels are bordered by intersecting planes, which are defined by intersecting said shells and premix gas channels with a virtual coaxial cylinder of a predetermined radius, and that said burner ring+has an inner radius similar to said predetermined radius.
The present invention is now to be explained more closely by means of different embodiments and with reference to the attached drawings.
As explained in the introductory part, the air leakage flow through the front panel sealing of existing EV and AEV burners bypasses the initial flame zone and is mixed later into the hot gas without premixing before with fuel. It is therefore detrimental for both NOx and CO production.
By contrast, in the combustor arrangement according to the invention, an embodiment of which is shown in
According to
The swirler configuration of
Each of the shells 25 is equipped with a premix gas channel 35 extending along an axially oriented edge of the respective shell such that a fuel gas can be injected from said premix gas channel 35 through gas injection holes (not shown) into a stream of air entering the interior of the arrangement of shells 25 through the adjacent slot 36.
The downstream ends of the shells 25 and premix gas channels 35 are bordered by intersecting planes P1 and P2, respectively, which are defined by intersecting said shells 25 and premix gas channels 35 with a virtual coaxial cylinder of a predetermined radius.
As shown in
The burner 21 with its burner ring 26 is slideably mounted in a coaxial burner sleeve 24. A seal 32 of the labyrinth type is positioned at the upstream end of the burner ring 26 between the burner ring 26 and the surrounding burner sleeve 24. The burner sleeve 24 has a conically widening burner outlet 29 at its downstream end and is fixed to a front panel 23 of the combustion chamber 22 (
Downstream of the seal 32 the burner sleeve 24 is equipped with an annular series of purge air holes 33, through which purge air can enter into an purge the gap between the burner ring 26 and the burner sleeve 24.
The use of the burner sleeve 24 mounted on the front panel 23 of the combustion chamber 22 makes the axial position of the gas turbine burner 21 axially adjustable. It improves air velocity profiles along the burner slots 36 by directing with its air inlet 31 an air approach flow in axial direction and at the same time formes a mixing tube, where air leakages are mixed with fuel sufficiently far upstream in comparison to the flame. The burner sleeve 24 takes on the function of the burner mixing tube but is introduced as part of the front panel 23, avoiding the leakage problem mentioned above. Since the burner 21 is sliding inside the sleeve 24, there will be again a leakage, which, however is not harmful, as the leakage air is added upstream of the mixing tube and will take part in the mixing process upstream of the flame.
Summarized, long cylindrical sleeves 24 shrouding the burners 21 are part of the combustor front panel 23. These sleeves 24 have a bell-shaped mouth or air inlet 31 to guide the air flow with a strong axial component to the burner slots 36. The sleeves 24 have radial air inlets or purge air holes 33 to purge the radial gap between the sleeves 24 and the burner rings 26 and to prevent flame stabilisation at the burner ring exit. Contrary to the existing AEV burner, the mixing zone is not part of the extractable burner 21 since the sleeves 24 themselves form the burner mixing zones before the outlet to the combustion chamber 22. At the outlet the sleeves have a diffuser shape (burner outlet 29) to better stabilize the flame.
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