Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/26—Controlling the air flow
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
  • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
  • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
  • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

• the invention relates to a method for operating a combustion chamber arrangement.
• a portion of the airflow provided by a compressor is often not fed into the combustion process, but is instead routed as a secondary flow outside the combustion chamber between a pressure casing of the gas turbine and the combustion chamber wall, and downstream of the combustion zone is mixed with the combustion exhaust gases as secondary air or mixed air through secondary openings (mixing air openings).
• the split i.e., the ratio between the primary flow participating in combustion and the secondary flow forming the mixed air, depends primarily on the geometry of the combustion chamber arrangement within the pressure casing of the gas turbine. This geometry is generally at least approximately constant across various load points, resulting in a nearly constant split across the entire load range.
• the air and fuel mass flow rates vary considerably with the load point or the required electrical power.
• the ratio between air and fuel mass flow rates is generally not constant across the load range, but shifts towards a greater excess of air (higher air-fuel ratio ⁇ ) at partial load.
• a constant split therefore leads to problems due to the varying ratio across the load range.
• the difference between the total air flow and the fuel mass flow leads to a shift in the air-fuel ratio in the combustion chamber, and thus in the air-fuel ratio ⁇ . This influence on the air-fuel ratio ⁇ directly affects the emission values of the gas turbine.
• a combustion chamber arrangement of the type mentioned above, as well as a method for operating a combustion chamber arrangement, are derived from the DE 10 2017 120 370 A1
• the known combustion chamber arrangement comprises a burner head for supplying fuel and oxidizer for jet-stabilized combustion into a combustion chamber, with a fixed section comprising supply nozzles and a movable section with branch lines and fuel nozzles for adjusting the proportion of mixed air and oxidizer (split).
• the adjustment possibilities are limited.
• axial adjustment of the fuel nozzles to influence the split also changes the length of the premixing section between fuel and oxidizer within the supply nozzles.
• the DE 10 2020 132 494 A1 Figure 1 shows a gas turbine combustion chamber system where the split is controlled by a control device that varies the flow cross-sections of the mixing air openings.
• a control device that varies the flow cross-sections of the mixing air openings.
• an orifice plate is arranged in the area of the mixing air openings.
• very high temperatures prevail in this area, just behind the combustion zone, accompanied by high potential thermal expansion. Therefore, the high tolerances that must be taken into account can negatively affect the effectiveness of the orifice plate and/or its movement.
• the DE 38 19 898 A1 Disclosing a combustion chamber for a gas turbine engine for operation with liquid fuel, with an inlet-side flow guide vane and connecting bores arranged circumferentially around a combustion chamber for the addition of a secondary airflow.
• the ratio between the primary and secondary airflow is adjustable with regard to minimizing oxygen emissions.
• the flow is controlled by means of adjustable guide vanes of the flow guide grid.
• the invention is based on the objective of providing a combustion chamber arrangement of the type mentioned above and a method for operating a combustion chamber arrangement, wherein the emissions are reliably optimized over a wide operating range.
• the combustion chamber arrangement provides that the adjusting device has an adjusting element separate from the fuel line and associated with at least one supply nozzle, which in a first position opens the flow cross-section to the maximum extent, i.e., the area of the flow cross-section with respect to the adjustable flow cross-sections within the combustion chamber arrangement is maximally large, and/or in a second position closes the flow cross-section to the maximum extent. i.e., the area of the flow cross-section is minimized with respect to the adjustable flow cross-sections.
• the adjusting element acts as a kind of aperture for the respective feed nozzle. Between the first and second positions, the adjusting element occupies an intermediate position.
• the adjusting element and/or the adjusting device constitute an additional component of the burner system, separate from the fuel line (and/or the component comprising the fuel line), which is integrated into the combustion chamber system.
• the adjusting device with the adjusting element can also be used for retrofitting existing burner systems with a suitable or easily adaptable burner geometry, e.g., by means of an adjusting component.
• At least one primary channel serves to add a primary flow of oxidizer, which is supplied to the combustion zone, particularly as combustion air.
• the at least one secondary opening is arranged, in particular, in the downstream half of the combustion chamber, at least so far downstream that, during operation, the oxidizer flowing through it, especially air, does not participate in the combustion in the combustion chamber, at least for the most part.
• several secondary openings are provided, which are arranged, in particular, equidistant from each other in a ring arrangement circumferentially in the combustion chamber wall.
• the split By adjusting the flow cross-section, i.e., changing the cross-sectional area of the primary channel, the split is modified when the total oxidizer flow is divided. Reducing the cross-sectional area decreases the proportion of the primary flow and increases the proportion of the secondary flow. In this way, the split can be adjusted relatively precisely over a wide load range and/or depending on (other) changing boundary conditions, e.g., due to system changes such as changes in fuel, in particular the fuel gas composition, and/or changes to the combustion chamber inlet temperature, are optimized to minimize emissions.
• the presence of the adjustment element allows for optimized design with regard to advantageous adjustment options and/or characteristics, while simultaneously offering favorable implementation possibilities, particularly in conjunction with other components of the combustion chamber assembly as a single structural unit.
• the adjustment element enables a large cross-sectional change within the primary channel, thereby influencing the split, advantageously without affecting the length of a premix section (the distance between a fuel outlet opening and an oxidizer outlet opening).
• the adjusting device in particular the adjusting element, can be designed such that in the second position the flow cross-section for the flow of oxidizer is minimally open.
• This provides a safety feature that ensures that even in the event of a malfunction of the adjusting device, the primary channel is never completely closed and a minimum flow of oxidizer always reaches the combustion zone.
• the minimum flow cross-section can be dimensioned, for example, with respect to a design operating point, such that a minimum desired oxidizer-to-fuel ratio is achieved. In this way, flame extinguishment due to a malfunction of the control and/or regulation of the adjusting device is advantageously prevented.
• the adjusting element can be arranged to be axially displaceable within the combustion chamber assembly, wherein in the first position the adjusting element is arranged upstream and outside the primary channel and/or in the second position it is arranged at least partially inside the primary channel.
• the displacement is preferably automated, e.g., by means of an actuator located externally to the pressure housing.
• the adjusting body and the fuel line are arranged coaxially with respect to the nozzle axis (and symmetrically to the at least one supply nozzle), wherein in particular the fuel line runs centrally on the nozzle axis at least in a section arranged within the supply nozzle, and/or the adjusting body is arranged (ring-shaped) around the fuel line.
• the adjusting element is designed and arranged such that, at least in an intermediate position between the first and second positions, the oxidizer flowing through the primary channel is divided into two primary flow paths.
• a first primary flow path is located radially inside the adjusting element, between the fuel line and the adjusting element, and a second primary flow path is located radially outside the adjusting element, in particular between the adjusting element and the nozzle wall.
• the adjustment characteristic can be optimized continuously and/or stepwise when the adjusting element is moved, e.g., by closing one of the flow paths in the second position.
• the adjusting body can be provided with a cone-shaped upstream section, wherein the radial thickness increases in the axial direction up to a radial outer edge, and/or a cone-shaped downstream section, wherein the radial thickness decreases in the axial direction.
• the cones are, for example, truncated at the axial ends of the adjusting body. "In the axial direction" here corresponds to "with respect to operation in the flow direction".
• the adjusting body has a stop, in particular a circumferential one, for axial contact with the feed nozzle, in particular the upstream end of the nozzle wall, in the second position, wherein in particular The second primary flow path is completely closable or closed.
• the stop preferably makes contact with the upstream end of the feed nozzle in its second position.
• the stop is formed by means of the radial outer surface, wherein the radial outer surface is arranged further away from the nozzle axis than the nozzle wall and subsequently has a recess, preferably a right-angled, circumferential one, axially (downstream).
• the circumferential recess forms the stop in the manner of a "shoulder", which preferably transitions directly into the downstream section.
• the fuel line is provided with a radial thickening on its outer surface, particularly a circumferential one, which preferably extends axially from or across the area of the upstream end of the feed nozzle along the section of the fuel line projecting into the feed nozzle.
• the wall of the fuel line is, for example, up to 1.2 to 4 times thicker than the upstream wall of the fuel line.
• the radial thickening serves, in particular, to adjust the flow cross-section within the inner, first primary flow path in conjunction with the radial inner surface of the adjustment element.
• the radial thickening starting from its upstream end, is continuously radially thickened, e.g., conically shaped. In this way, a flow-optimized guidance of the oxidizer flow directed through the first primary flow path is achieved.
• the fuel line upstream of the supply nozzle has a displacement section aligned coaxially with the supply nozzle.
• the length is such that the adjusting element is displaceable into the displacement section even in the position furthest upstream (the first position).
• the displacement section corresponds at least to the axial length of the adjusting element.
• the multiple feed nozzles are arranged on a nozzle ring around the longitudinal axis on the end wall, and an adjusting body is provided for each feed nozzle, wherein the adjusting bodies are arranged in a ring arrangement coaxially (with respect to the longitudinal axis) to the nozzle ring.
• the adjustment device has a radially outer ring, which is arranged radially around the outside of the ring assembly, coaxially to the adjustment elements, and to which the adjustment elements are each attached, e.g., by means of an outer strut.
• the adjustment device has a radially inner ring, which is arranged radially inside the ring assembly, coaxially to it, and to which the adjustment elements are each attached, e.g., by means of an inner strut.
• the inner ring and/or the outer ring is/are preferably cylindrical.
• the outer ring has a larger axial dimension, for example more than twice, preferably more than four times, the dimension of the adjusting elements and/or extends axially further upstream.
• the outer ring can serve for mechanical stabilization and/or guidance and/or as a flow-guiding element.
• One suitable design variant consists of a (e.g., tubular) nozzle extending centrally along the longitudinal axis in an upstream direction from the side of the end wall facing away from the combustion chamber, which preferably The nozzle extends axially further upstream than the displacement section of at least one fuel line.
• the nozzle can serve as a guide and stabilizing element, for example, in conjunction with internal struts of another component, such as a gas guidance component or an adjustment component, when assembled.
• At least one fuel line is each attached by means of an inner strut to a radially inner ring, which is axially displaceable, e.g., essentially positively, arranged circumferentially around the nozzle.
• the diameters of the inner ring and the outer diameter of the nozzle are matched to each other such that the inner ring can be slid onto or off the nozzle during assembly and/or disassembly.
• the combustion chamber assembly is preferably modular in design, comprising a gas guide component with the oxidizer plenum and preferably with the annular channel, an adjustment component with the adjustment device, and a combustion chamber component with the combustion chamber and at least one feed nozzle.
• the components are designed for installation in a pressure casing of the gas turbine to form (together with the pressure casing) a combustion chamber system, interacting with one another and being appropriately coordinated.
• the combustion chamber assembly consisting of the individual components forms a unit of the gas turbine.
• the at least one fuel line is attached to the gas guiding component, wherein in particular a radially outer strut is arranged between the outer ring and the fuel line for each fuel line, and wherein preferably the inner struts and the radially inner ring are assigned to the gas guiding component.
• the invention further relates to an adjusting component in design according to one of the design variants described in connection with the combustion chamber arrangement, with an adjusting device designed for use in a combustion chamber arrangement according to one of the aforementioned design variants.
• a position of the adjusting device is automatically adjusted by means of a control device depending on at least one boundary condition, wherein, for example, an adjustment characteristic determined by means of calibration and stored in the control device is included and/or a defined controlled variable is regulated by means of, in particular, the position of the adjusting device as the manipulated variable.
• FIG. 1 shows a schematic view of part of a combustion chamber arrangement 1 with a jet-stabilized burner according to the prior art, as used in gas turbines, in particular in micro gas turbines with power outputs of 1 MW and below.
• the combustion chamber arrangement 1 comprises a combustion chamber 2 extending symmetrically along a longitudinal axis L, with a combustion chamber 4 enclosed by a combustion chamber wall 10, which is preferably cylindrical.
• the combustion chamber 4 is bounded on the inlet side by an end wall 12, which is shown here as an example of a conical shape.
• the combustion chamber 2 transitions into an exhaust gas tract, preferably by means of a conical constriction.
• водородн ⁇ openings 36 are preferably provided in the combustion chamber wall 10, which are arranged in a ring arrangement around the circumference, particularly equidistant from each other (in Fig. 1 (not shown).
• the secondary openings 36 are designed for the addition of secondary air, also referred to as mixing air, and are arranged so far downstream that, during operation, the oxidizer flowing through them, in particular air, does not participate, at least for the most part, in the combustion in the combustion chamber 4.
• the secondary air is mixed with the exhaust gas flow exiting the combustion chamber 2.
• An inlet nozzle 16 is attached to the end wall 12 in the radially outer half of the combustion chamber 2, preferably with several inlet nozzles 16 arranged in a ring around the longitudinal axis L on a nozzle ring 18 (as e.g. in Fig. 6
• the feed nozzle 16 comprises a primary channel 22, which is enclosed by a nozzle wall 20 (in particular cylindrical) and aligned along a nozzle axis M, with an oxidizer outlet opening 24 on the downstream side for the swirl-free, in particular exclusively axial, supply of oxidizer from an oxidizer plenum 6 via the inlet-side end wall 12 into the combustion chamber 4.
• the oxidizer plenum 6 forms an oxidizer supply chamber for flow through with a total flow of oxidizer.
• the primary channel 22 preferably has a cross-sectional narrowing in its course, wherein the nozzle wall 20 is preferably conical.
• the feed nozzle 16 is attached to the end wall 12 in such a way that it extends into the combustion chamber 4 with an end encompassing the oxidizer outlet opening 24 on the downstream side.
• the combustion chamber arrangement 1 further comprises, for each supply nozzle 16, a fuel line 26 with a fuel channel 28 and a downstream component, preferably arranged at or upstream of the cross-sectional constriction within the primary channel 22.
• Fuel outlet opening 30 can also be arranged at the level of the oxidizer outlet opening 24 (not shown here).
• the fuel line 26 runs, at least with its downstream section arranged within the supply nozzle 16, in particular coaxially to the supply nozzle 16 on the nozzle axis M.
• a secondary channel 34 is formed between the combustion chamber wall 10 and an outer wall 7 surrounding the combustion chamber wall 10, which is in particular associated with a pressure housing of the gas turbine, through which secondary air flows to the secondary openings 36 during operation.
• the combustion chamber arrangement 1 Upstream of the supply nozzles 16, the combustion chamber arrangement 1 has the oxidizer plenum 6 for supplying a total flow of oxidizer, which in particular includes air provided by a compressor of the gas turbine, to the combustion chamber 2.
• the total flow of oxidizer passes through the oxidizer plenum 6 to the combustion chamber 2.
• the total flow is divided into a primary flow and a secondary flow by means of the geometry of the combustion chamber arrangement 1 installed in the pressure housing and/or the pressure housing itself.
• the primary flow enters the combustion chamber 4 directly through the supply nozzles 16, mixing with fuel, in particular fuel gas, supplied through the fuel lines 26, and participates directly in the combustion reaction.
• the fuel-oxidizer mixture is introduced into the combustion chamber 2 as jets with such a high axial momentum that a large-scale recirculation zone 5 is formed.
• Typical flow velocities at the oxidizer outlet 24 are between 60 m/s and 200 m/s.
• the recirculation brings the combusted, hot exhaust gas back to the jet root near the feed nozzles 16 and mixes it with the incoming fresh gases, i.e., fuel and oxidizer.
• the recirculation zone 5 is generally formed essentially radially within the nozzle ring 18.
• the secondary flow is directed past a large part of the combustion chamber 2 as the remaining oxidizer flow via the secondary channel 34, cools it and preferably enters the combustion chamber 4 at least substantially downstream of the combustion zone via the secondary openings 36.
• the split i.e., the ratio of the primary flow to the secondary flow when distributing the total flow to the oxidizer, depends predominantly on the geometry of the combustion chamber arrangement 1 in its installed state within the pressure housing, for example, the flow cross-sections of the primary channels 22 and the secondary channel 34.
• the geometry of the combustion chamber arrangement 1 is at least approximately constant over different load points, which is why an approximately constant distribution between the primary flow and the secondary flow results over the entire load range.
• the oxidizer and fuel mass flow rates vary considerably with the load point or the required electrical power.
• the ratio between oxidizer and fuel mass flow rates is generally not constant across the load range, but shifts towards a greater excess air ratio (higher air-fuel ratio ⁇ ) at partial load.
• a constant split therefore leads to inefficiencies due to the varying mass flow rates across the load range.
• the ratio between the total oxidizer flow and the fuel mass flow leads to a shift in the oxidizer-fuel ratio (air-fuel ratio) in combustion chamber 4 of combustion chamber 2, and thus in the air-fuel ratio ⁇ . This influence on the air-fuel ratio ⁇ directly affects the emission values of the gas turbine.
• Fig. 2 The relationship is shown in diagram 80, where emissions 82 are plotted against the air-fuel ratio 84.
• Combustion chamber arrangements 1 which are optimized, for example, at their full-load operating point with respect to nitrogen oxide ( NOx ) emissions 822 (optimal air-fuel ratio 86), experience significantly lower oxygen (leaner) conditions in the part-load range. As a result, carbon monoxide (CO) emissions 824 increase sharply at part load.
• NOx nitrogen oxide
• CO carbon monoxide
• FIG. 3A and Fig. 3B Figure 1 shows a schematic view of a part of a combustion chamber arrangement 1 designed according to the invention for emission-optimized control of the split over a large load range and/or depending on other variable boundary conditions, such as different fuels and/or different combustion chamber inlet temperatures.
• the combustion chamber arrangement 1 has an adjustment device 40 with, in particular, an adjustment element 42 for each supply nozzle 16, by means of which a flow cross-section 224 of the primary channel 22 (see Figure 1) is adjusted.
• Fig. 4A is adjustable during the operation of the gas turbine.
• FIG. 3A shows the adjusting device 40 in a first position, in which the adjusting body 42 maximally opens the flow cross-section 224 of the feed nozzle 16, i.e., with maximum area of the flow cross-section 224. In the first position, the adjusting body 42 can also be arranged further upstream of the feed nozzle 16 (see Figure 1). Fig. 4A ).
• Fig. 3B The adjusting device 40 is shown in a second position, wherein the adjusting body 42 maximally closes the flow cross-section 224 of the supply nozzle 16, i.e. with minimum area of the flow cross-section 224.
• the adjustment of the adjusting element 42 is effected by axial displacement of the adjusting element 42, which for this purpose is arranged to be axially displaceable within the combustion chamber assembly 1.
• the adjusting element 42 In the first axial position, the adjusting element 42 is preferably arranged completely outside the primary channel 22, upstream of it. In the second axial position, the adjusting element 42 is preferably arranged partially (not completely) inside the primary channel 22.
• the displacement can preferably be effected by means of an actuator located outside the pressure housing (i.e., external) (not shown here) and corresponding force transmission means 55 to the adjusting element 42 (see Figure 1).
• Fig. 7A take place.
• the adjusting body 42 is arranged coaxially around the fuel line 26 (with respect to the nozzle axis M) and is designed to be rotationally symmetrical at least in its essentials (e.g., apart from retaining elements such as struts) (cf. e.g. Fig. 7B
• the adjusting body 42 has a cone-shaped upstream section 44 (where "upstream” and “downstream” refer to the flow direction with respect to the oxidizer flow during operation), within which the radial thickness of the adjusting body 42 increases in the axial direction up to a radial outer surface 48 with maximum radial extent.
• the adjusting body 42 Downstream of the radial outer surface 48, the adjusting body 42 has a cone-shaped downstream section 46 for precise adjustment of the primary flow, within which the radial thickness of the adjusting body 42 decreases in the axial direction.
• the radial outer surface 48 is, in particular, radially further away from the nozzle axis M than the nozzle wall 20 at the upstream end of the feed nozzle 16. Downstream of the radial outer surface 48, a right-angled recess 52 is arranged downstream of the radial outer surface 48.
• the recess 52 together with the dimensions of the radial outer surface 48, forms, for example, a circumferential axial stop 50 in the form of a shoulder, which in the second position abuts the upstream end of the nozzle wall 20 comes into contact and thus completely closes off a second primary flow path 222 (cf. Fig. 3B ).
• the adjusting body 42 is designed and arranged such that, at least in an intermediate position axially located between the first and second positions, at least two primary flow paths are formed, a first primary flow path 220 and a second primary flow path 222.
• the first primary flow path 220 is located radially inside the adjusting body 42, between the fuel line 26 and the adjusting body 42.
• the second primary flow path 222 is located radially outside the adjusting body 42. When the adjusting body 42 is positioned sectionally inside the feed nozzle 16, the second primary flow path 222 is formed between the adjusting body 42 and the nozzle wall 20.
• the fuel line 26 with the radial thickening 32 and the adjusting body 42 are coordinated such that in the second position, with the minimum area of the flow cross-section 224, the inner, first primary flow path 220 remains open.
• the radial inner surface of the adjusting body is The 42 radially spaced elements are arranged radially around the radial thickening 32. In this way, a minimum primary flow of oxidizer can always enter the combustion zone.
• the minimum area of the flow cross-section 224 is preferably dimensioned, taking into account the operating range of the gas turbine, such that, e.g., at a design operating point, a minimum desired oxidizer-fuel ratio is established.
• the fuel line 26, extending upstream from the section projecting into the supply nozzle 16 has a displacement section 260 aligned coaxially with the supply nozzle 16.
• the displacement section 260 has at least such an axial length that the adjusting element 42 can be displaced upstream into the displacement section 260 up to the first position, i.e., the axial length preferably corresponds at least to the axial length of the adjusting element 42.
• Fig. 4A and Fig. 4B show more precisely the flow cross-section 224 in the first position ( Fig. 4A ) and in an intermediate position ( Fig. 4B
• the decisive factor for the split is the smallest flow cross-section 224 (i.e., the smallest cross-sectional area in the axial direction) in or on the primary channel 22 within the effective range of the adjusting body 42.
• adjusting body 42 is located in the first position upstream of the supply nozzle 16 in the displacement section 260 upstream of the supply nozzle 16.
• the relevant flow cross-section 224 is formed annularly around the fuel line 26 within the supply nozzle 16 at the position of the maximum radial thickening 32.
• Fig. 4B The adjusting body 42 is located in the intermediate position, partially inside the supply nozzle 16, forming the two primary flow paths 220, 222.
• the relevant flow cross-section 224 is composed of the annular circumferential flow cross-sections of the inner, first primary flow path 220 and the outer, second primary flow path 222.
• the adjusting body 42 In the case of the Fig. 4B In the intermediate position shown, the adjusting body 42 is axially close to the second position, in which the outer, second primary flow path 222 is completely closed by means of the stop 50.
• the flow cross-section 224 gradually decreases due to the conical design of the downstream section 46 of the adjusting body 42 and/or the radial thickening 32, thereby reducing the flow cross-sections of the first primary flow path 220 and the second primary flow path 222. This shifts the split towards the secondary flow.
• the primary flow rate can be adjusted to the fuel quantity, and a design air-fuel ratio can be achieved in the combustion chamber arrangement 1 for optimized combustion with low emissions over a significantly extended load range.
• operation can also be optimized for altered boundary conditions resulting from other system changes, such as changes to the fuel mixture, particularly the fuel gas mixture, and/or changes to the combustion chamber inlet temperature.
• the adjusting element 42 is, for example, actuated by the in Fig. 4A
• the first position shown is inserted axially into the feed nozzle 16 and fixed at an axial position with the desired flow cross-section, e.g., at an intermediate position or the second position.
• a control system can be provided, for example, wherein the axial position of the adjusting device 40, in particular the adjusting element 42, constitutes the manipulated variable, which is set to a suitable controlled variable, e.g., exhaust emissions, by means of a control device.
• a suitable controlled variable e.g., exhaust emissions
• a calibration procedure can be applied, whereby an optimal position of the adjustment device 40 is determined in a calibration operation across the entire load and/or operating range of the gas turbine during plant operation.
• the determined values are stored, for example, as a map-based calibration characteristic in the control unit and used for automated position tracking, controlled by the control unit and, for example, the external actuator, particularly depending on a load point.
• other possible changes in boundary conditions such as the aforementioned system changes, can be included in the calibration.
• FIG. 5 and Fig. 6 Figure 1 shows a preferred embodiment of the combustion chamber arrangement 1 in longitudinal section, in which the combustion chamber arrangement 1 is modular in design.
• Fig. 5 shows the combustion chamber arrangement 1 in a longitudinal section through the feed nozzles 16 and Fig. 6 in a longitudinal section in a position rotated by 30° around the longitudinal axis L, whereby the feed nozzles 16 are not cut.
• the combustion chamber assembly 1 comprises a gas guidance component 70 with the oxidizer plenum 6, an adjustment component 72 with the adjustment device 40, and a combustion chamber component 74 with the combustion chamber 2 and the feed nozzles 16.
• the components are designed for installation in a pressure housing of the gas turbine to form a combustion chamber system.
• the components for the combustion chamber arrangement 1 according to the invention are designed and/or adapted accordingly.
• the gas guide component 70 has, in addition to the extended fuel lines 26, comprising the adjusting section 260, inner struts 68 and/or outer struts 66 for stabilizing the fuel lines. 26 as well as an outer ring 64 and/or an inner ring 65 for stabilization and/or support relative to the other components.
• the combustion chamber component 74 has, in particular, an upstream extending nozzle 62.
• FIG. 5 and Fig. 6 The figures show, taking into account the rotational symmetry with respect to the longitudinal axis L, the arrangement of the, in this case exemplary, six feed nozzles 16 on the nozzle ring 18 on the end wall 12. Accordingly, the adjusting elements 42 are arranged in a ring arrangement 420 coaxially to the nozzle ring 18.
• Fig. 7A shows the adjustment component 72 in a perspective view from the front, Fig. 7B front view and Fig. 7C in a sectional view along a Fig. 7B
• the section line AA is designated.
• the adjusting component 72 which in this case comprises the adjusting device 40, has a cylindrical radially outer ring 54 for stabilizing and guiding the adjusting elements 42.
• This ring 54 is arranged radially around the outside of the adjusting elements 42, coaxially (with respect to the longitudinal axis L) to the ring arrangement 420.
• the adjusting elements 42 are each attached to the outer ring 54 by means of a radially outer strut 58.
• At least one of the force transmission means 55 for coupling to the, in particular, external actuator is arranged on the outer ring 54.
• the force transmission acts from the radial direction, but can also occur, for example, from the axial direction (not shown here).
• the adjusting component 72 has, for example, a cylindrical radial inner ring 56, which is arranged radially within the ring arrangement 420 coaxially to it.
• the adjusting elements 42 are each attached to the inner ring by means of a radially inner strut 60.
• the outer ring 54 has a larger axial extent than the adjusting bodies 42, in this example more than four times the axial extent of the adjusting bodies. 42, and extends axially further upstream than the adjusting elements 42.
• the outer ring 54 is preferably matched with its diameter to an outer annular surface 640 of the outer ring 64 of the gas guiding component 70 such that the outer ring 54 of the adjusting component 72 is axially displaceable on the outer annular surface 640 and thus cooperates with the annular surface 640 to guide the adjusting component.
• the outer ring 54 Downstream of the adjusting body 42, the outer ring 54 forms a section of the outer wall 7 for guiding the oxidizer.
• the nozzle 62 extends axially further upstream than the sliding sections 260 of the six fuel lines 26.
• the fuel lines 26, in turn, are each attached upstream of the sliding sections 260 to the radially inner, in particular cylindrical, ring 65 by means of the inner struts 68.
• the radially inner ring 65 is matched to the diameter of the nozzle 62 such that, when the components are assembled in the pressure housing, the radially inner ring 65 can be positively slid onto the nozzle 62. In this way, the nozzle 62 serves to stabilize the fuel lines 26 and/or to position the gas guide component 70 relative to the combustion chamber component 74.
• a recess 762 is arranged for each projection 706, its circumferential position and size adapted to the respective projection 706 in the plate 760.
• a rod element 764 is preferably centrally attached to the plate 760 as a handle.
• the gas guidance component 70 with the projections 706 can also be provided on another gas guidance component of a gas turbine arrangement, independently of the design of the gas guidance component 70 relating to the adjusting device 40.
• the combustion chamber arrangement 1 can be used particularly advantageously in gas turbine plants that are not designed and operated to operate under a constant load profile, but rather, for example, to handle peak loads.
• the combustion chamber arrangement 1 also offers advantages in hybrid systems, for example, with a coupling of a gas turbine and another energy conversion and/or storage arrangement, where the input boundary conditions (e.g., the oxidizer inlet temperature) of the gas turbine can change over the operating range, due to its optimized adaptability. This ensures that optimized emission values of the gas turbine can be maintained over a wide operating range, even with changing load and/or boundary conditions.

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