• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A combustor (14) includes an end cover (22) and a combustion chamber disposed downstream of the end cover (22). The combustor (14) further includes nozzles (32, 34) disposed radially in the end cover (22) and a jacket (36) surrounding at least one of the nozzles (34) and extending downstream into the combustion chamber , The jacket (36) has an inner wall surface and an outer wall surface. A method of operating a combustor (14) includes the steps of: directing compressed working fluid through the nozzles (32, 34) into a combustor (28) located downstream of an end cover (22) of the combustor, the plurality of nozzles (32 , 34) are arranged radially with respect to the combustion chamber in the end cover, directing fuel through each nozzle (32) in a first subset of the nozzles (32) into the combustion chamber, and igniting the of each nozzle (32) in the first subset fuel from the nozzles (32) in the combustion chamber. In addition, the method includes the step of separating fuel in the second subset of nozzles (34) to each nozzle (34) with a separate jacket (36) around each nozzle (34) in a second subset of the nozzles (34) which extends into the combustion chamber and has an inner wall surface and an outer wall surface.
    公开号:CH703865B1
    申请号:CH01544/11
    申请日:2011-09-16
    公开日:2016-01-15
    发明作者:Willy Steve Ziminsky；Christopher Edward Wolfe；Sergey Anatolievich Meshkov；Sergey Adolfovich Oskin
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Field of the invention
    The present invention relates to a combustor for a gas turbine and a method for its operation. Specifically, the present invention describes and provides a combustor having a plurality of fuel nozzles that can operate in different throttled modes to reduce fuel consumption.
    Background to the invention
    Gas turbines are often used in commercial power generation applications. A gas turbine compresses ambient air, mixes fuel with the compressed air, and ignites the mixture to produce high-energy combustion gases that flow through a turbine to do work. The turbine can drive a drive shaft which is connected to a generator to generate electricity, which is then fed into a power grid. To generate power at a desired frequency, the turbine and generator must operate at a relatively constant speed regardless of the amount of electricity produced.
    Gas turbines are usually set up to operate at substantially the constructive desired base load with the highest efficiency. However, the power demanded by the gas turbine is often lower than the basic structural load. For example, the consumption and thus the demand for energy can fluctuate over a season and even over the course of a day, with the power requirement usually being less at night. Continuing to operate the gas turbine at its basic design load during periods of low demand would waste fuel and produce excessive emissions.
    An alternative solution to the operation of the gas turbine at the base load in periods of low demand is based simply to shut down the gas turbine and start it up again when the power consumption increases. However, starting and shutting down the gas turbine along many components causes large thermal stresses, resulting in additional expense for repair and maintenance. In addition, gas turbines in a combined cycle-using system are often operated in conjunction with additional auxiliary equipment. For example, a heat recovery steam generator (HRSG) may be connected to the turbine outlet to recover heat from the exhaust gases, thereby increasing the overall efficiency of the gas turbine. Full shutdown of the gas turbine during periods of low demand therefore also requires shutdown of the associated auxiliary equipment, with the result of an additional increase in costs associated with shutting down the gas turbine.
    Another solution for operating a gas turbine in periods of low demand is based on operating the gas turbine in a throttled mode. In existing throttled modes, the gas turbine still operates at the speed required to produce power at the desired frequency, and the flow rate of fuel and air to the combustion chambers is reduced to reduce the amount of combustion gas generated in the combustion chambers. so that the power generated by the gas turbine is reduced. However, the operating range of typical compressors limits the extent to which the airflow can be reduced, with the result that the amount is limited to which the fuel flow can be reduced while maintaining the optimum ratio of fuel to air. At lower operating levels, one or more nozzles in each combustor are "idled" by blocking the flow of fuel to the idle nozzles. The fuel-supplied nozzles continue to mix fuel with the compressed working fluid for combustion, and the idled nozzles simply direct the compressed working fluid to the combustion chamber for combustion without any fuel. The throttled mode generates sufficient combustion gases to operate the turbine and generator at the required speed to produce power at the desired frequency, and the idle nozzles reduce fuel consumption. As the power demand increases, the fuel flow to all the nozzles can be resumed to allow the gas turbine to return to the design base load.
    Existing throttled modes are limited in view of the achievable degree of power reduction. For example, in a throttled mode, the compressed working fluid flowing through the idle nozzles mixes with the combustion gases from the fuel-supplied nozzles and tends to prematurely extinguish fuel combustion in the combustion chamber. The incomplete combustion of fuel causes increased CO emissions that may exceed emission limits. As a result, the minimum operating level during existing throttled modes may need to have a high value of up to 40-50% of the baseline load in order to meet emission limits for CO and NOx.
    The object underlying the present invention is to provide an improved multi-fuel nozzle combustor which can operate in different throttled modes to reduce fuel consumption.
    Brief description of the invention
    Features and advantages of the invention are set forth below in the following description, or may be obvious from the description, or may be learned by practice of the invention.
    According to the present invention, a combustor on an end cover and a combustion chamber arranged downstream of the end cover. The combustor further includes a plurality of nozzles disposed in the end cover radially with respect to the combustor and a jacket surrounding at least one of the plurality of nozzles and extending downstream of the at least one of the plurality of nozzles into the combustor. The jacket has an inner wall surface and an outer wall surface.
    According to an advantageous development of the present invention, a combustion chamber device includes an end cover and a combustion chamber arranged downstream of the end cover. The combustor further includes a plurality of nozzles disposed radially in the end cap and at least one shell surrounding each of the plurality of nozzles and extending into the combustor downstream of the at least one of the plurality of nozzles. The jacket is based on a double-walled tube.
    Further, the present invention relates to a method for operating a combustor. The method includes the steps of directing compressed working fluid across a plurality of nozzles into a combustor disposed downstream of an end cap of the combustor, the plurality of nozzles disposed radially with respect to the combustor in the end cap, and directing fuel through each nozzle in a first subset of the multiple nozzles in the combustion chamber. The method further includes the step of igniting the fuel in the combustion chamber from each nozzle in the first subset of the plurality of nozzles. In addition, the method includes the steps of extending a separate jacket around each nozzle in a second subset of the plurality of nozzles and separating fuel to each nozzle in the second subset of the plurality of nozzles, the jacket extending into the combustion chamber and an inner chamber Wall surface and has an outer wall surface.
    The skilled person will understand the features and aspects of such and further embodiments after reading the description.
    Brief description of the drawings
    A full and practical description of the present invention, which includes the best mode for the person skilled in the invention, is described in more detail in the following description in conjunction with the accompanying drawings:<Tb> FIG. 1 <SEP> shows a simplified cross section of a gas turbine;<Tb> FIG. FIG. 2 shows a perspective view of the combustor shown in FIG. 1 with the combustor wall removed for clarity; FIG.<Tb> FIG. Fig. 3 <SEP> is a perspective view of the combustor shown in Fig. 2 operating in a special throttled mode;<Tb> FIG. Fig. 4 shows a perspective view of the sheath shown in Fig. 3; and<Tb> FIG. Figures 5, 6, 7 and 8 illustrate neutral and fuel supplied nozzles in particular throttled modes.
    Detailed description of the invention
    [0014] Reference will now be made in detail to present embodiments of the invention, wherein one or more of the examples are illustrated in the accompanying drawings. The detailed description uses numerical and alphabetic designations to refer to features in the figures. In the figures and in the description, similar or similar terms have been used to refer to the same or similar elements of the invention.
    All examples serve to illustrate the invention and are not intended to limit this. One skilled in the art will readily recognize that modifications and changes may be made to the present invention without departing from the scope or subject matter of the invention. For example, features that are illustrated or described as part of one embodiment may be applied to another embodiment to yield yet another embodiment. The present invention is therefore intended to cover such modifications and variations as fall within the scope of the appended claims.
    Fig. 1 shows a simplified cross section of a gas turbine 10. The gas turbine 10 generally includes a compressor 12 at the front, one or more combustors 14 disposed about the center, and a turbine 16 at the rear. The compressor 12 and the turbine 16 usually have a common impeller 18.
    The compressor 12 imparts kinetic energy to a working fluid (air) by compressing it to bring it into a high energy state. The compressed working fluid exits the compressor 12 and flows through a compressor discharge plenum 20 to the combustors 14. Each combustor 14 generally includes an end cover 22, a plurality of nozzles 24, and a combustor wall 26 defining a combustor 28 downstream of the end cover 22. The nozzles 24 mix fuel with the compressed working fluid, and the mixture ignites in the combustion chamber 28 to produce combustion gases having a high temperature, a high pressure, and a high velocity. The combustion gases flow through a transition piece 30 to the turbine 16, where they expand to perform work.
    Fig. 2 shows a perspective view of the combustor 14 shown in Fig. 1, wherein the combustion chamber wall 26 is removed for the sake of clarity. As shown, the end cap 22 provides structural support to the nozzles 24. The nozzles 24 are generally radially disposed in the end cap 22 in a variety of geometries, such as the five nozzles shown in FIG. 2 that surround a single nozzle. Other geometries that fall within the scope of the present invention include six or seven nozzles surrounding a single nozzle, or any suitable arrangement that meets specific design requirements. The nozzles 24 may have uniform diameters or, as illustrated in FIG. 2, different diameters.
    In base load power operation, each nozzle 24 mixes fuel with the compressed working fluid. The mixture ignites downstream of the end cover 22 in the combustion chamber 28 to generate combustion gases. In periods of reduced power demand, the combustor 14 may be operated in a throttled mode in which one or more nozzles 24 are "idled" by disabling the fuel flow to the idle nozzles.
    Fig. 3 shows the combustor 14 shown in Fig. 2 operated in a special throttled mode. In this particular throttled mode, three nozzles are fuel-supplied nozzles 32, and three nozzles are idle nozzles 34. Fuel and compressed working fluid flow through the fuel-supplied nozzles 32, while through the idle nozzles 34 are only compressed working fluid flows. In addition, each idle nozzle 34 surrounds a shell 36 which extends downstream from each idle nozzle 34 into the combustion chamber. The shrouds 36 may be fixedly or movably attached to the idle nozzles 34 and / or to the end cover 22. Each shell 36 directs the compressed working fluid through a portion of the combustion chamber to prevent the compressed working fluid from the idle nozzles 34 from prematurely stifling the combustion. As the power demand increases, the combustor 14 may return to baseload power levels by resuming the fuel flow to the idle nozzles 34 and igniting the fuel mixture in the combustor.
    FIG. 4 shows a perspective view of the sheath 36 shown in FIG. 3. The sheath 36 may be made of any alloy, superalloy, coated ceramic, or other suitable material capable of withstanding combustion temperatures greater than 1500 degrees Celsius to 1600 degrees Celsius, corresponding to 2800-3000 degrees Fahrenheit, to withstand. The shell 36 may be formed on a double-walled construction having an inner wall surface 38 facing the associated idled nozzle, an outer wall surface 40 facing away from the associated idle nozzle, and an inner one between the inner and outer 38 the outer 40 wall surface arranged cavity 42 are based. In alternative embodiments, the shell 36 may be a single wall construction with the inner 38 and outer 40 wall surfaces being simply opposite sides of the single wall. Regardless of the construction, the shell 36 may be formed in the inner 38 and / or outer 40 wall surface with a plurality of openings 44 having a diameter in the range of 5.1.times.10.sup.-4.m and 1.3 × 10 <-> <3> m, corresponding to about 0.02 inches and 0.05 inches.
    A cooling fluid may be supplied through the cavity 42 and / or through the openings 44 to cool the surfaces 38, 40 of the shell 36. Suitable cooling fluids include steam, water, branched compressed working fluid, and air. Other constructions and methods known to those skilled in the art may be used to cool the shell 36. For example, US patent application 2006/0191268 describes a method and apparatus for cooling gas turbine nozzles which may also be configured to cool coats.
    Each shell 36 is sized with a slightly larger diameter than the associated, offset in the idle nozzle and may, as shown, be cylindrical or may have a convergent or divergent shape depending on the specific requirements of the embodiment and the construction. The length of the shell 36 should be sufficient to extend the shell 36 far enough into the combustion chamber to prevent the compressed working fluid from the idle nozzles from mixing with the combustion gases from the fuel supplied nozzles and preventing the combustion chamber from becoming contaminated Burning suffocated prematurely. Suitable lengths may be sized at 0.076 m, 0.13 m, 0.18 m or above, corresponding to 3 inches, 5 inches, 7 inches or more, depending on the particular combustor design and anticipated throttled mode.
    The sheath 36 shown in FIG. 4 may be retractable with respect to the end cover 22. If the jacket 36 is retractable, it is usually retracted during base load operating conditions and extended during throttling operating conditions when the fuel for the associated nozzle is disabled. As shown in FIG. 4, the shell 36 may include means for extending and retracting the shell 36. The means for extending and retracting the shell 36 may be any suitable manually, mechanically, electrically, hydraulically, pneumatically or otherwise comparable system known in the art for deploying and retracting objects. For example, as shown in FIG. 4, the shell 36 may include a threaded extension 54 that may be threaded into the end cover 22. The jacket 36 can be rotated manually or by means of an electric, hydraulic or pneumatic drive. Rotating the shell 36 in one direction could extend the shell 36 into the combustion chamber in view of throttling operating conditions, and rotating the shell 36 in the other direction may retract the shell 36 into the end cover 22 for base load operating conditions. Other prior art equivalent designs for extending and retracting objects include hydraulic pistons, pneumatic pawls, springs, pawl mechanisms, and magnetic or inductive coils.
    Figures 5, 6, 7 and 8 illustrate fuel supplied 32 and idle 34 nozzles in specific throttled modes. The hatched circular areas in each figure represent fuel supplied nozzles 32, and the non-hatched circles represent idle nozzles 34. As shown in Fig. 4, a shell 36 surrounds each idle nozzle 34 and extends from each one idle nozzle 34 downstream of the combustion chamber.
    In Fig. 5, the circumferentially disposed five nozzles are fuel-supplied nozzles 32, and the central nozzle is an idle nozzle 34. In this throttled mode, the fuel consumption can be reduced by about 16%, and the Combustion gas outlet temperature can be reduced by up to 21K, equal to 70 degrees Fahrenheit, without any exceedance of emission requirements. In Figures 6, 7 and 8, additional nozzles are placed in idle to further reduce power consumption during the throttled mode. In each throttled mode illustrated in Figs. 5, 6, 7 and 8, compressed working fluid from the compressor flows through each nozzle 32, 34. In each illustration, a first subset of the nozzles are operated as fuel supplied nozzles 32 which further supply fuel to the nozzle Incinerate in the combustion chamber. In each illustration, a second set of nozzles is operated as idle nozzles 34 by inhibiting fuel flow to the idle nozzles 34 and surrounding each idle nozzle 34 with a jacket extending from extends the idle nozzles 34 downstream in the combustion chamber.
    A combustor according to the scope of the present invention may be operated in a throttled mode as explained below. A stream of compressed working fluid may be fed into the combustion chamber through each nozzle. A fuel stream may be fed into the combustion chamber through a first subset of the nozzles (i.e., fuel supplied nozzles) and ignited in the combustion chamber. One or more shrouds may be extended around each nozzle in a second subset of the nozzles (i.e., around the idle nozzles) and the fuel to each idle nozzle may be separated. If desired, each jacket may be cooled via openings in each jacket, for example by passing steam, water, branched compressed working fluid and / or air.
    The combustor may transition to design base load operating conditions by passing fuel through each idle nozzle into the combustor, and igniting the fuel that emanates from each nozzle that was previously idled in the combustor , The shrouds may remain extended downstream of the nozzles that were previously idle into the combustion chamber. Alternatively, the coats may be withdrawn from the combustion chamber.
    The present description uses examples to describe the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, for example, make and use any devices and systems, and any methods associated therewith perform.
    A combustor 14 includes an end cap 22 and a combustor 28 disposed downstream of the end cap 22. The combustor 14 further includes nozzles 24 disposed radially in the end cap 22 and a shell 36 surrounding at least one of the nozzles 24 and which extends downstream into the combustion chamber 28. The jacket 36 has an inner wall surface 38 and an outer wall surface 40. A method of operating a combustor 14 includes the steps of directing compressed working fluid through the nozzles 32, 34 into a combustor 28 located downstream of an end cover 22 of the combustor, the plurality of nozzles disposed radially with respect to the combustor in the end cap are passing fuel through each nozzle 32 in a first subset of the nozzles 32 into the combustion chamber 28 and igniting the fuel from each nozzle 32 in the first subset of nozzles 32 in the combustion chamber 28. In addition, the method includes the step of the second subset of nozzles 34 to separate fuel to each nozzle 34, wherein a separate jacket 36 is provided around each nozzle 34 in a second subset of nozzles 34 which extends into the combustion chamber 28 and an inner wall surface 38 and an outer wall surface 40 has ,
    LIST OF REFERENCE NUMBERS
    [0031]<Tb> 10 <September> Gas Turbine<Tb> 12 <September> compressor<Tb> 14 <September> combustors<Tb> 16 <September> Turbine<Tb> 18 <September> Wheels<Tb> 20 <September> Verdichterauslasssammelraum<Tb> 22 <September> end cover<Tb> 24 <September> Nozzles<Tb> 26 <September> combustion chamber wall<Tb> 28 <September> combustion chamber<Tb> 30 <September> transition piece<tb> 32 <SEP> Fuel supplied nozzles<tb> 34 <SEP> Nozzles displaced to idle<tb> 36 <SEP> Coat - Fig. 3, 4<tb> 38 <SEP> Inner wall surface<tb> 40 <SEP> Outer wall surface<Tb> 42 <September> cavity<Tb> 44 <September> openings<Tb> 54 <September> Extension
    权利要求:
    Claims (10)
    [1]
    A combustor (14), which includes:an end cover (22);a combustion chamber (28) disposed downstream of the end cover (22);a plurality of nozzles (24) disposed radially with respect to the combustion chamber in the end cover (22); andat least one nozzle (24), a jacket (36) surrounding the respective nozzle (24) and extending from the respective nozzle (24) downstream into the combustion chamber (28), wherein the jacket (36) has an inner Wall surface (38) and an outer wall surface (40).
    [2]
    Second combustor (14) according to claim 1, wherein the jacket (36), starting from the respective nozzle (24) at least 0.13 m, corresponding to 5 inches, downstream in the combustion chamber (28).
    [3]
    3. A combustor (14) according to claim 1 or 2, wherein in the shell (36) a plurality of openings (44) are formed, which pass through at least the inner wall surface (38) and / or the outer wall surface (40).
    [4]
    4. A combustor (14) according to any one of claims 1 to 3, wherein the jacket (36) between the inner wall surface (38) and the outer wall surface (40) has a cavity (42).
    [5]
    A combustor (14) according to any one of claims 1 to 4, wherein the jacket (36) is attached to the end cover (22).
    [6]
    A combustor (14) according to any one of claims 1 to 5, further comprising means for extending and retracting the shell (36) with respect to the end cover (22) into and out of the combustion chamber (28).
    [7]
    The combustor (14) of any one of claims 1 to 6, further comprising a plurality of shrouds (36) each surrounding one of the plurality of nozzles (24), the plurality of shrouds (36) downstream of the plurality of nozzles (24) extending the combustion chamber (28).
    [8]
    8. A method of operating a combustor (14), comprising the steps of:Directing compressed working fluid through a plurality of nozzles (32, 34) into a combustion chamber (28) disposed downstream of an end cover (22) of the combustor (14), the plurality of nozzles (32, 34) radially inwardly of the combustion chamber the end cover (22) are arranged;Passing fuel through each nozzle (32) in a first subset of the plurality of nozzles (32, 34) into the combustion chamber (28);Igniting the fuel in the combustion chamber (28) from each nozzle (32) in the first subset of the plurality of nozzles (32, 34); andSeparating the fuel to each nozzle (34) in a second subset of the plurality of nozzles (32, 34) with a separate jacket (36) disposed about each nozzle (34) in the second subset of the plurality of nozzles (32, 34), which extends into the combustion chamber (28) and has an inner wall surface (38) and an outer wall surface (40).
    [9]
    The method of claim 8, further comprising, prior to separating the fuel, including the step of extending each jacket (36) disposed about the respective nozzle (34) in the second subset of the plurality of nozzles (32, 34) into the combustion chamber (28 ).
    [10]
    The method of claim 8 or 9, further comprising the step of retracting each shell (36) around the combustion chamber (28) around each nozzle (34) in the second subset of the plurality of nozzles (32, 34), and directing Fuel through each nozzle (34) in the second subset of the plurality of nozzles (32, 34) into the combustion chamber (28).
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2018-04-30| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/889,512|US8276386B2|2010-09-24|2010-09-24|Apparatus and method for a combustor|
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