Abstract:
The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber with a low pressure drop. The disclosure further refers to a method for operating a gas turbine with such a combustor arrangement.

Description:
CROSS-REFERENCE TO RELATED APPLICATIONS 
       [0001]    This application claims priority to PCT/EP2013/058650 filed Apr. 25, 2013, which claims priority to European application 12189685.6 filed Oct. 24, 2012, both of which are hereby incorporated in their entireties. 
     
    
     TECHNICAL FIELD 
       [0002]    The invention refers to a sequential combustor arrangement for a gas turbine with admixing dilution gas into the combustor arrangement. The invention additionally refers to a method for operating a gas turbine with admixing dilution gas into a combustor arrangement. 
       BACKGROUND 
       [0003]    Due to increased power generation by unsteady renewable sources like wind or solar existing gas turbine based power plants are increasingly used to balance power demand and to stabilize the grid. Thus improved operational flexibility is required. This implies that gas turbines are often operated at lower load than the base load design point, i.e. at lower combustor inlet and firing temperatures. 
         [0004]    At the same time, emission limit values and overall emission permits are becoming more stringent, so that it is required to operate at lower emission values, keep low emissions also at part load operation and during transients, as these also count for cumulative emission limits. 
         [0005]    State-of-the-art combustion systems are designed to cope with a certain variability in operating conditions, e.g. by adjusting the compressor inlet mass flow or controlling the fuel split among different burners, fuel stages or combustors. However, this is not sufficient to meet the new requirements. 
         [0006]    To further reduce emissions and operational flexibility sequential combustion has been suggested in DE 10312971 A1. Depending on the operating conditions, in particular on the hot gas temperature of a first combustion chamber it can be necessary to cool the hot gases before they are admitted to a second burner (also called sequential burner). This cooling can be advantageous to allow fuel injection and premixing of the injected fuel with the hot flue gases of the first combustor in the second burner. 
         [0007]    Conventional cooling methods either require heat exchanger structures which lead to high pressure drops in the main hog gas flow or suggest injection of a cooling medium from the side walls. For injection of a cooling medium from the side walls a high pressure drop is required which is detrimental to the efficiency of a gas turbine operated with such a combustor arrangement and a controlled cooling of the whole flow is difficult. 
       SUMMARY 
       [0008]    The object of the present disclosure is to propose a sequential combustor arrangement with a mixing section for dilution gas admixing between the first combustion chamber and the second burner. The dilution gas is admixed in the mixing section to provide proper inlet flow conditions for the second burner. In particular the hot gases are cooled. 
         [0009]    High inlet temperatures may result in high emissions (in particular NOx, CO, and unburned hydrocarbons) and/or flashback in the second burner. Flashback and NOx are induced by the reduced self-ignition time for the injected fuel due to a high inlet gas temperature or high oxygen concentration, which causes earlier ignition (leading to flashback) or reduced time for fuel air mixing resulting in local hot spots during combustion and consequently increases NOx emission. Low temperature regions can cause CO emissions, due to the increased self-ignition time. This can reduce the time for CO to CO2 burnout, and a reduced local flame temperature, which is can further slowdown the CO to CO2 burnout. Finally local hot spots may lead to overheating of certain parts downstream of the mixer. 
         [0010]    A sequential combustor arrangement according to the disclosure comprises a first burner, a first combustion chamber, a mixing device for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection, wherein the mixer is adapted to guide combustion gases in a hot gas flow path extending between the first combustion chamber and the second burner comprising a duct having an inlet at an upstream end adapted for connection to the first combustion chamber and an outlet at a downstream end adapted for connection to the second burner. 
         [0011]    A local high oxygen concentration can have a similar effect as a local high temperature, e.g. fast reaction reducing the time for mixing, high combustion temperatures, increased NOx emissions and possibly flash back. A local low oxygen concentration can have a similar effect as a local low temperature, e.g. slow reaction leading to increased CO and UHC (unburned hydrocarbon) emissions. 
         [0012]    A high or low local inlet velocity can lead to increased or reduced residence time in the second burner and subsequent second combustion chamber, which has similar negative effects as inhomogeneous self-ignition times, e.g. a reduced residence time in the second burner can lead to incomplete mixing and high NOx. A reduced residence time in the second combustor can lead to incomplete combustion resulting in increased CO emissions. A reduced flow velocity in the second burner can lead to early ignition and flash back. 
         [0013]    Further important requirements from the aerodynamic point of view are minimised pressure loss in the hot gas path and the dilution gas supply. Both can impact the performance of a gas turbine operating with such a combustor arrangement. 
         [0014]    According to a first embodiment the mixer comprises a plurality of injection pipes, which are pointing inwards from the walls of the duct for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber to provide appropriate inlet conditions to the second burner. 
         [0015]    The diameter, length and number of these pipes are designed to admix dilution gas into the hot gas flow such that the required local mass flow and temperature drop are achieved with a low pressure drop. Typically the injection pipes allow admixing of dilution gas with a pressure drop of 0.4% to 2% of the total pressure of the dilution gas pressure before admixing. With a low pressure drop at the inlet of the injector pipes, a pressure drop of 0.2% to 1% of the total pressure of the dilution gas pressure before admixing can be sufficient. To reduce the inlet pressure drop rounded pipe inlets can be used. 
         [0016]    According to an embodiment the combustor arrangement comprises first injection pipes having a first intrusion depth into the hot gas flow normal to the side wall, and second injection pipes having a second intrusion depth normal to the side wall. The intrusion depth of the second injection pipes can be smaller than the intrusion depth of the first injection pipes. 
         [0017]    For pipes arranged normal to the side wall the length of the pipes extending into the hot gas path is equal to the intrusion depth. 
         [0018]    According to a further embodiment the ratio of the intrusion depth of the first injection pipe to the intrusion depth of the second injection pipe is greater than 2. In yet another embodiment the ratio of the intrusion depth of the first injection pipe to the intrusion depth of the second injection pipe is greater than 3. 
         [0019]    According to yet another embodiment at least a third injection pipe with a length between the length of the first and second injection pipe is arranged in the mixer. The third injection pipes can for example be arranged upstream or downstream of the first injection pipes and have a length of 60% to 80% of the first injection pipe. 
         [0020]    According to one embodiment the ratio of equivalent diameter of the cross section of the flow path at the location of the first injection pipes in the mixer to the intrusion depth of the first injection pipes is in the range of 2.5 to 8. In yet another embodiment the ratio of equivalent diameter of the cross section of the flow path at the location of the first injection pipes in the mixer to the intrusion depth of the first injection pipes is in a range of 3 to 6. For mixers in a can architecture the equivalent diameter is the diameter of a circular duct or pipe that gives the same cross sectional area as the area of the flow duct. For mixers in an annular architecture the equivalent diameter is the height of the annular duct (i.e. the outer radium minus the inner radius). 
         [0021]    According to one embodiment the ratio of the length of the second injection pipe to the diameter of the second injection pipe is smaller than ¼. With this embodiment dilution gas can be admixed close to the side walls with minimum pressure loss. This short pipe allows penetration of the admixed dilution gas beyond the boundary layer of the side walls and admixing into the main flow. 
         [0022]    According to a further embodiment the mixer comprises first injection pipes and injection holes arranged along the side wall. The first injection pipes are arranged to admix dilution gas towards the central region of the hot gas flow path and the injection holes are arranged to admix dilution gas into the wall regions of the hot gas flow path. 
         [0023]    To minimize the pressure drop in the hot gas flow path it can be advantageous to arrange the second injection pipes or injection holes close to the first injection pipes. The dilution gas injected from the second injection pipes or injection holes close to the first injection pipe can reduce the pressure drop. In particular the second injection pipes or injection holes can be arranged downstream of first injection pipes or vice versa, i.e. the first injection pipes or holes can be arranged downstream of the second injection pipes or injection holes. If the second injection pipe is arranged downstream of the first injection pipe it can compensate for the wake of the first injection pipes thus reducing the pressure loss due to the first injection pipes. If the second injection pipe is arranged upstream of the first injection pipe the flow velocity in the vicinity of the first injection pipe is reduced due to the wake of the second injection pipe and the injected dilution air of the second injection pipe thus also reducing the pressure drop. 
         [0024]    According to a further embodiment the distance in flow direction of the hot gases between first injection pipe and second injection pipe, respectively injection holes, is less than three times the diameter of the first injection pipe preferably less than two and a half times the diameter of the first injection pipes. The short distance reduces the overall length of the mixer and allows effective injection into the wake. 
         [0025]    According to one embodiment the pipes of one length, e.g. the first injection pipes, are arranged circumferentially distributed along the wall of the mixer in one plane normal to the main flow direction of the hot gases flowing through the mixer. 
         [0026]    According to a further embodiment the pipes are arranged circumferentially distributed along the wall of the mixer and staggered relative to a plane normal to the main flow direction of the hot gases flowing through the mixer. The stagger reduces the blockage of the pipes extending into the hot gas flow path. To keep the mixer length short the stagger can be smaller than half the pipe diameter. To effectively reduce the blockage the stagger should preferably be more than 10% of the pipe diameter, and more preferably more than 25% of the pipe diameter. 
         [0027]    The pipes of the mixer are exposed to the hot gases leaving the first combustion chamber. The pipes are inherently cooled by the dilution gas which is flowing through them. However, to increase life time of the pipes additional measures to reduce the temperature of the pipes can be applied. 
         [0028]    In one embodiment the heat transfer coefficient on the inside of the pipe is increased. For increased heat transfer cooling ribs and/or a pin field can be arranged on the inner surface of the injection pipes. 
         [0029]    In another embodiment the outer surface of the pipe is coated with thermal barrier coating (TBC). In a further embodiment thermal barrier coating is applied on the leading edge region of the pipe. This can for example be a region of +/−45° from the leading edge. In combination with TBC or as an alternative to TBC diffusion cooling holes can be applied on the pipe such that part of the dilution gas discharges through the cooling holes and thereby reduces the thermal load of the pipe walls. Preferably the diffusion cooling holes are arranged on the downstream side of the pipe. The dilution gas can be injected with a low pressure difference relative to the total pressure of the hot gases. Therefore an injection at the leading edge might not be possible. Additionally, by diffusion cooling of the downstream side the negative effect of the pipes wake on the mixer pressure drop can be at least partly mitigated. 
         [0030]    One of the objects of the present disclosure is to provide a mixer which allows admixing of dilution gas with a low pressure drop in the hot gas flow path. To reduce the pressure drop a low flow velocity is expedient. According to one embodiment the mixer of the combustor arrangement comprises a diffusor section upstream of the dilution gas admixing to reduce the flow velocity of the hot gases. Alternatively or in addition the mixer comprises a diffusor section in the region of the dilution gas admixing to increase the flow area as the volume flow increases due to the admixing of dilution gas. The increase in flow area can have the same ratio as the volume flow increase to keep the axial flow velocity constant. In a further embodiment the increase in flow area is chosen such that the increase in the average axial velocity stays within 20% of the axial velocity upstream of the admixing location. 
         [0031]    In a further embodiment the injection pipes are inclined at an angle of less than 90° relative to the flow direction of the hot gases such that the dilution gas leaving the pipes have a flow component in the direction of the hot gas flow at the location of injection. 
         [0032]    Preferably the injection pipes are inclined at an angle such that the axial component of the dilution gas leaving the pipes is equal to or within +/−50% of the axial flow velocity of the hot gas flow at the location of injection. 
         [0033]    Besides the combustor arrangement a gas turbine comprising such a combustor arrangement is subject of the present disclosure. Such a gas turbine comprises at least a compressor, a combustor arrangement with a first burner, a first combustion chamber, a mixing device for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in fluid flow connection, wherein the mixer is adapted to guide combustion gases in a hot gas flow path extending between the first combustion chamber and the second burner comprising a duct having an inlet at an upstream end adapted for connection to the first combustion chamber and an outlet at a downstream end adapted for connection to the second burner, and a turbine. The mixer comprises a plurality of injection pipes pointing inwards from the side walls of the duct for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber during operation. The mixer is arranged such that the dilution gas is admixed during operation to cool the hot gases. 
         [0034]    Besides the gas turbine a method for operating such a gas turbine is subject of the present disclosure. Dilution gas can be admixed to the hot gases in the mixer such that the hot gases are cooled. According to one embodiment dilution gas is injected through holes and/or injection pipes with different lengths in order to introduce dilution gas in different regions of the cross section of the mixer. In one embodiment the first injection pipes are arranged to admix dilution gas towards the central region of the hot gas flow path and the second injection pipes or injection holes are arranged to admix dilution gas into the wall regions of the hot gas flow path. 
         [0035]    Effusion cooling might be used to cool the combustor walls and/or side walls of the mixing section. 
         [0036]    Downstream of the dilution air injection mixing between dilution air and hot gas can be enhanced by a contraction of the flow path. 
         [0037]    Referring to a sequential combustion the combination of combustors can be disposed as follows:
       Both, the first and second combustors are configured as sequential can-can architecture.   The first combustor is configured as an annular combustion chamber and the second combustor is configured as a can configuration.   The first combustor is configured as a can-architecture and the secondary combustor is configured as an annular combustion chamber.   Both, the first and second combustor are configured as annular combustion chambers.       
 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0042]    The disclosure, its nature as well as its advantages, shall be described in more detail below with the aid of the accompanying drawings. Referring to the drawings: 
           [0043]      FIGS. 1   a, b, c  and  d  show a generic gas turbine using sequential combustion with a mixer for admixing dilution gas; 
           [0044]      FIG. 2   a  shows a mixer with first and second injection pipes; 
           [0045]      FIG. 2   b  shows a mixer with first injection pipes and injection holes; 
           [0046]      FIG. 2   c  shows a mixer with first injection pipes and injection holes and diverging mixer side walls; 
           [0047]      FIG. 2   d  shows a mixer with first and second injection pipes and direct dilution gas supply from the compressor plenum; 
           [0048]      FIG. 3  shows a wall section of a mixer with first and second injection pipes inclined in the direction of the hot gas flow; 
           [0049]      FIG. 4  shows a section of mixer side wall with staggered first and second injection pipes; 
           [0050]      FIG. 5  shows a section of mixer in an annular architecture with first and second injection pipes arranged on inner and outer side walls; 
           [0051]      FIG. 6  shows a section of mixer in a can architecture with first and second injection pipes arranged on a cylindrical wall. 
       
    
    
     DETAILED DESCRIPTION 
       [0052]      FIG. 1   a, b, c , and  d  show a gas turbine  100  with a sequential combustor arrangement  104  according to the disclosure. It comprises a compressor  103 , a combustor arrangement  104 , and a turbine  105 . The combustor arrangement  104  comprises a first burner  112 , a first combustion chamber  101 , and a mixer  117  for admixing a dilution gas to the hot gases leaving the first combustion chamber  101  during operation. Downstream of the mixer  117  the combustor arrangement  104  further comprises a second burner  113 , and a second combustion chamber  102 . The first burner  112 , first combustion chamber  101 , mixer  117 , second burner  113  and second combustion chamber  102  are arranged sequentially in a fluid flow connection. Fuel can be introduced into the first burner  112  via a first fuel injection  123 , mixed with compressed air which is compressed in the compressor  103 , and combusted in the first combustion chamber  101 . Dilution gas is admixed in the subsequent mixer  117 . Additional fuel can be introduced into the second burner via a second, fuel injection  124 , mixed with hot gases leaving the mixer  117 , and combusted in the second combustion chamber  102 . The hot gases leaving the second combustion chamber  102  are expanded in the subsequent turbine  105 , performing work. The turbine  105  and compressor  103  are arranged on a shaft  106 . 
         [0053]    The remaining heat of the exhaust gas  107  leaving the turbine  105  can be further used in a heat recovery steam generator or boiler (not shown) for steam generation. 
         [0054]    In the example shown here compressor exit gas is admixed as dilution gas. 
         [0055]    Typically compressor exit gas is compressed ambient air. For gas turbines with flue gas recirculation (not shown) the compressor exit gas is a mixture of ambient air and recirculated flue gas. 
         [0056]    Typically, the gas turbine system includes a generator (not shown) which is coupled to a shaft  106  of the gas turbine  100 . 
         [0057]    Different exemplary embodiments of the mixer  117  are shown in  FIGS. 2   a  to  2   d  as an enlarged section of the  FIGS. 1   a  to  1   d .  FIG. 2   a  shows a first example with a mixer comprising first injection pipes  114  with a length L and second injection pipes  115  with a length l arranged downstream of the first injection pipes  114 . In this example compressed gas from the compressor plenum is guided along combustor liner in a connection duct  111  as dilution gas  110 . From the connection duct  111  the dilution gas  110  is injected into the mixer via the first injection pipes  114  and second injection pipes  115 . The mixer  117  has a cross section with a height H. 
         [0058]    The mixer can be arranged with an annular cross section. For an annular mixer the height H is the difference between the diameter of an outer wall of the annular flow section and the inner wall of the annular flow section. For a mixer with a cylindrical cross section (can-like mixer arrangement) the height H is the diameter of the cross section. The height L of the first injection pipes  114  and the height l of the second injection pipes  115  are chosen such that good mixing of injected dilution gas  110  with the hot gas leaving the first combustion chamber  101  is assured. 
         [0059]      FIG. 2   b  shows an example with a mixer  117  comprising first injection pipes  114  with a length L and injection holes  118 . The second injection pipes  115  of  FIG. 2   a  are replaced by injection holes  118 . The use of injection holes can reduce the pressure drop of the hot gas flow in the mixer  117 . It can for example be used if the height H is small enough to allow good mixing with admixing of dilution gas through the first injection pipes  114  with a length L and injection holes  118 . 
         [0060]      FIG. 2   c  shows another example with a mixer comprising first injection pipes  114  with a length L and second injection pipes  115  with a length l arranged downstream of the first injection pipes  114 . To reduce the pressure loss in the hot gas flow the mixer is arranged with diverging side walls  116  in the region of the mixer where dilution gas is admixed. Due to the diverging side walls  116  the cross section of the mixer is increasing like in a diffusor. This increase in cross section leads to a reduction in the flow velocity and a reduction of the pressure drop caused by the first injection pipes  114  and second injection pipes  115 . Further it reduces the pressure drop induced by injection dilution gas into the hot gas flow. 
         [0061]      FIG. 2   d  shows example which is based on the example of  FIG. 2   a . In this example the dilution gas  110  is directly supplied to the first injection pipes  114  and second injection pipes  115  from the compressor plenum (downstream of the compressor  103 ). The first injection pipes  114  and second injection pipes  115  are extending into the compressor plenum and therefore dilution gas  110  with a higher pressure and lower temperature (no temperature pick-up due to the cooling of the combustor before use as dilution gas) is available. 
         [0062]      FIG. 3  shows a wall section of a mixer  117  with inclined first and second injection pipes  114 ,  115 . The first and second injection pipes  114 ,  115  are inclined in the direction of the hot gas flow to reduce the pressure drop of the first and second injection pipes  114 ,  115 . Preferably the inclination has an angle such that the dilution gas leaving the pipes have an axial flow component v d.ax  in the direction of the hot gas flow at the location of injection, which is equal to the flow velocity v hot  of the hot gas. The dilution gas leaves the injection pipe  114 ,  115  with a velocity of dilution gas v d . This has the component in direction of the hot gas flow with an axial velocity of dilution gas v d,ax  and a flow component normal to the hot gas flow which has a velocity of dilution gas normal to the hot gas flow v d,n . The velocity of dilution gas normal to the hot gas flow v d,n  facilitates penetration of the dilution gas into the hot gas flow and mixing with the hot gas flow. 
         [0063]    In the example of  FIG. 3  a thermal barrier coating (TBC)  119  is applied to the upstream side of the injection pipes  114 ,  115  to reduce their temperature. The TBC can be applied for example on a section of the upstream half or around the whole injection pipe  114 ,  115 . In addition cooling holes  120  are applied on the downstream side. Besides cooling the pipe wall the cooling air ejected from these cooling holes  120  is injected into the wake of the injection pipes  114 ,  115  and thereby reduces the pressured drop in the hot gas flow. 
         [0064]      FIG. 4  shows a top view of cut-out section the side wall  116  of a mixer  117  with staggered first and second injection pipes  114 ,  115  having a diameter D. The first injection pipes are arranged in a plane A respectively a plane A′ which is normal to the flow direction of the hot gases. The first injection pipes are staggered by a stagger s, i.e. the plane A is arranged at a distance s in flow direction relative to the plane A′. Due to the stagger the free distance f′ between two adjacent first injection pipes  114  is increased compared to the free distance f between two adjacent injection pipes which are not staggered. 
         [0065]    The second injection pipes  115  are arranged with the same stagger s downstream of the first injection pipes  114  with a distance a between first and a second injection pipes  114 ,  115 . In the example shown the diameter d of the second injection pipes  115  is equal to the diameter D of the first injection pipes  114 . 
         [0066]      FIG. 5  shows an example of a section of mixer  117  in an annular architecture. First and second injection pipes  114 ,  115  are arranged on inner and outer side walls  116 , which are arranged concentrically with an annular hot gas flow path in-between. Hot gases are flowing into the mixer  117  with a velocity of the hot gas v hot . The resulting mixed gas is leaving the mixer  117  with a velocity of the mixed gas v mix . 
         [0067]    Admixing via injection pipes from only one annular side wall  116  is also feasible, e.g. from the outer side wall (not shown). This can facilitate supply of dilution gas to the injection pipes. 
         [0068]      FIG. 6  shows an example of a section of mixer in a can architecture.  FIG. 6  shows a cut-out of a cylindrical side wall  116 . First and second injection pipes  114 ,  115  are arranged on the cylindrical wall  116 . The second injection pipes  115  are arranged downstream of the first injection pipes  114  in the direction of the hot gas flow velocity v hot . The inlet to the first and second injection pipe  114 ,  115  is rounded to reduce the pressure loss of the dilution gas entering the injection pipe  114 ,  115 . The second injection pipe  115  has a length, which is only in the order of two times the radius of the inlet rounding. 
         [0069]    The first combustion chamber  101  and the second combustion chamber  102  can be arranged in a combustor can-can-architecture, i.e. the first combustion chamber  101  and second combustion chamber  102  are can combustion chamber. 
         [0070]    The first combustion chamber  101  and the second combustion chamber  102  can be arranged in a combustor can-annular-architecture, i.e. the first combustion chamber  101  is arranged as an annular combustion chamber and second combustion chamber  102  is arranged as can combustion chamber. 
         [0071]    The first combustion chamber  101  and the second combustion chamber  102  can be arranged in a combustor annular-can-architecture, i.e. the first combustion chamber  101  is arranged as can combustion chamber and second combustion chamber  102  is arranged as an annular combustion chamber. 
         [0072]    The first combustion chamber  101  and the second combustion chamber  102  can be arranged in a combustor annular-annular-architecture, i.e. the first combustion chamber  101  and second combustion chamber  102  are annular combustion chambers. 
         [0073]    The mixing quality of the mixer  117  is crucial since the burner system of the second combustion chamber  102  requires a prescribed inlet temperature and inlet velocity profile. 
         [0074]    All the explained advantages are not limited just to the specified combinations but can also be used in other combinations or alone without departing from the scope of the disclosure. Other possibilities are optionally conceivable, for example, for deactivating individual burners or groups of burners. Further, the dilution gas can be re-cooled in a cooling air cooler before admixing in the mixer  117 . Further the arrangement of the injection pipes or injection holes can be reversed, i.e. the short second injection pipes or holes can be arranged upstream of the long first injection pipes. Further, there can be additional pipe types with further pipe length and pipe diameter combinations.