Gas turbine assembly with combustor assembly and method

Abstract

The invention relates to a combustion chamber arrangement (1), particularly for use in an aircraft engine, comprising: - a wall (5) that encloses a combustion chamber (101) oriented along a longitudinal axis (L), and - at least one, preferably a plurality of, fuel nozzle(s) (200) arranged on the inlet side of the combustion chamber (100) for adding liquid fuel to the combustion chamber (101). An alternative and / or combined optimized operation with fuels of different states of matter with comparatively little design effort is achieved by designing the combustion chamber arrangement (10) for operation with liquid and / or gaseous fuel, wherein at least one, preferably a plurality of, gas supply opening(s) (15, 19) arranged downstream of the fuel nozzle(s) (200) on the wall (5) are provided, by means of which gaseous fuel can be introduced into the combustion chamber (101) (Fig. 3A).

Description

[0001] The invention relates to a gas turbine arrangement comprising a turbine arrangement and a combustion chamber arrangement, as well as a method for operating the gas turbine arrangement. In known so-called "dual fuel" combustion chamber arrangements of gas turbine arrangements, different types of fuel, in particular liquid and / or gaseous fuels, can be introduced into the combustion chamber alternatively or simultaneously.

[0002] A combustion chamber arrangement and a method of this type are described in US 2017 / 307210 A1. In this known combustion chamber arrangement, a combustion chamber is bounded by a double-walled enclosure along a longitudinal axis. Primary fuel nozzles are arranged on the inlet side of the combustion chamber, and additional fuel nozzles are arranged around the perimeter of the enclosure. Gaseous or liquid fuel can be supplied via the inlet-side fuel nozzles, and gaseous fuel is supplied via the enclosure-side fuel nozzles. The enclosure-side fuel nozzles extend through the outer and inner walls of the enclosure and project radially through the inner wall into the combustion chamber. Mixing ports for the addition of air are formed in the inner wall around the fuel nozzles. This air flows through the space between the inner and outer walls.With this design, a diffuse mixing of the fuel supplied via the circumferential gas nozzles takes place with the combustion air flowing in through the mixing openings from the space between the inner and outer walls.

[0003] Document US 2016 / 123596 A1 also shows a combustion chamber arrangement with fuel nozzles located at the inlet of the combustion chamber and fuel nozzles or gas nozzles located around the perimeter of a combustion chamber wall. The gas supply openings of the perimeter gas nozzles, which are directed radially towards the combustion chamber, project into respective mixers for premixing the supplied fuel with supplied compressed air within a diffuser module housing.

[0004] Another combustion chamber arrangement with fuel nozzles located at the inlet of the combustion chamber and gas nozzles arranged circumferentially is shown in US 2021 / 199298 A1. This arrangement also addresses the use of liquid and gaseous fuels. In this arrangement, circumferentially arranged fuel nozzles within a combustion chamber wall are specially designed for premixing with high-pressure air and further mixing with lower-pressure air. High-pressure air is supplied through openings located in an outer wall of the combustion chamber wall, and fuel is introduced from outside through individual nozzle openings from a fuel mixing channel into the high-pressure airflow for premixing. The premixed fuel-air mixture is then further mixed with low-pressure air and subsequently fed through a channel in the inner wall of the combustion chamber wall into the combustion chamber in the region of a second flame zone.

[0005] Another combustion chamber arrangement, with fuel nozzles located at the inlet of the combustion chamber and fuel or gas nozzles arranged circumferentially in a wall of the combustion chamber, is described in US 2007 / 107437 A1. In this arrangement, the nozzles are also equipped with feed openings to introduce a premixed fuel-air mixture into the combustion chamber. Additionally, cooling air openings are provided around the perimeter of the combustion chamber.

[0006] A known combustion chamber arrangement for operation with liquid and / or gaseous fuel is also described in US 2016 201 897 A1. This arrangement includes a nozzle device by means of which liquid and / or gaseous fuel can be introduced into the combustion chamber.

[0007] The present invention is based on the objective of providing a gas turbine arrangement and a method of the type mentioned at the outset, wherein alternative and / or combined optimized operation with fuels of different states of matter is possible with comparatively little design effort.

[0008] The problem is solved for the gas turbine arrangement with the features of claim 1 and for the method with the features of claim 13.

[0009] Regarding the combustion chamber arrangement of the gas turbine arrangement, it is provided that the combustion chamber arrangement is designed for operation with liquid and / or gaseous fuel, wherein a plurality of gas supply opening(s) arranged downstream of the fuel nozzle(s) on the casing are provided, by means of which gaseous fuel can be introduced into the combustion chamber.

[0010] The gaseous fuel is preferably not added from the inlet end face where the fuel nozzle is located, and in particular not by means of the inlet-side fuel nozzle. For the sake of simplicity, the fuel nozzle is, for example, not designed for operation with gaseous fuel.

[0011] Preferably, the axial position of the gas supply openings is designed such that, during operation, the gaseous fuel is added to or downstream of a first combustion zone, with (at least partial) combustion of the liquid fuel.

[0012] The gaseous fuel is in particular hydrogen or a hydrogen-containing fuel gas and / or another fuel gas, for example methane or a methane-containing fuel gas.

[0013] The liquid fuel is in particular a kerosene-based or kerosene-related fuel (e.g. Jet-A1, diesel or a synthetic substitute fuel (SAF - "sustainable aviation fuel")).

[0014] The enclosure can be, for example, single-walled and / or double-walled, particularly with a gap formed between the walls. The gas supply openings are arranged, in particular, upstream of the outlet.

[0015] Introducing the gaseous fuel downstream of the fuel nozzle allows the use of an inlet-side fuel nozzle designed solely for operation with liquid fuel. This keeps the complexity of the fuel nozzle and combustion chamber arrangement comparatively low, even when designed for operation with additional gaseous fuel. Furthermore, operational advantages can arise, as combustion in the first combustion zone is optimized for liquid fuel in relevant operating ranges. A relatively reliable introduction of the gaseous fuel into the combustion chamber is achieved by incorporating a multitude of mixing ports arranged downstream of the fuel nozzle(s) in the combustion chamber's casing for adding supplemental air to the combustion chamber. If the gas supply port is present at each gas nozzle, it is located (radially) within the mixing port(s).The gas nozzles are arranged within the flow cross-section of the mixing orifice, with each gas nozzle and mixing orifice forming an air / gas supply arrangement. A gas supply orifice is located at the downstream end of each gas nozzle. The gas supply orifices can have any shape within the flow cross-section, for example, circular, elliptical, slit-shaped, or polygonal. Preferably, the shape of the flow cross-section corresponds (optionally congruently) to the shape of the flow cross-section of the mixing orifice with which the respective air / gas supply arrangement is formed. The gas nozzles can have a constant flow cross-section, particularly in a downstream section. The gas nozzles can be attached to the wall within the mixing orifice, particularly by means of one or more fastening means (e.g., struts).

[0016] The mixing openings can have any shape with respect to their respective flow cross-sections, e.g. circular, elliptical, slit-shaped and / or polygonal.

[0017] The mixing ports can each be designed as openings in the wall, their lengths corresponding to the wall thickness, and / or project beyond the wall (into the combustion chamber and / or into an air space surrounding the combustion chamber), forming air ducts. At least one outlet is arranged at the downstream end of each mixing port. In particular, the inlet and outlet areas of the mixing ports (and / or the gas supply ports) can be designed for optimal flow, e.g., rounded to minimize backflow.

[0018] The mixing openings are arranged equidistantly to each other, particularly in the direction of rotation, with the number of mixing openings corresponding, for example, to the number of inlet fuel nozzles.

[0019] This arrangement of gas supply openings or gas nozzles injects the gaseous fuel along with the mixed air, i.e., into a flow at a comparatively high velocity. Depending on the design (e.g., the size of the flow cross-section), the combustion process of the gaseous fuel can thus be shifted more or less far into the combustion chamber, with the mixed air serving, for example, as combustion air and / or jacket air, or the like.

[0020] In this way, the thermal stress on the conversion and / or the gas supply nozzle(s) can be advantageously reduced.

[0021] In this context, it is particularly advantageous if the gas nozzle(s) is / are arranged centrally within the respective mixing opening (forming the respective air / gas supply arrangement). In this way, the gaseous fuel is advantageously introduced into a region of comparatively high flow velocities, so that the reaction zone can be shifted away from the gas supply opening. The arrangement of the gas nozzle relative to the mixing opening can be, in particular, coaxial, with their central longitudinal axes coinciding. The central longitudinal axes can be oriented perpendicular to the wall (at a 90° angle) or at an angle, where the angle to the wall is less than 90°.

[0022] A more defined outflow of the gaseous fuel is advantageously achieved if, at least in sections, a (ring-shaped) circumferential air channel is arranged around the gas nozzle(s) in the respective mixing opening (of the corresponding air / gas supply arrangement) to form an airflow circulating around the gas nozzle(s). The air channel preferably has a smaller flow cross-section than the mixing opening. The air channel can, for example, terminate flush with the gas supply opening or upstream of it. For an advantageously symmetrical introduction of the gaseous fuel, the air channel is preferably arranged coaxially to the gas nozzle and / or the mixing opening and / or has a constant channel height (e.g., gap thickness).

[0023] For a uniform introduction of the mixing air and / or the gaseous fuel, several mixing openings are preferably arranged in at least one row of openings, wherein z mixing openings are present per row of openings, which are arranged at a uniform axial position and preferably equidistant from each other in the direction of rotation of the wall. If there are several rows of openings, their mixing openings can be offset from each other in the direction of rotation.

[0024] In each or every nth mixing port of each row of openings, with n = 2 to z, an air / gas supply arrangement can be formed, where n preferably represents the ordinal number of an integer quotient of z. This ensures a uniform distribution of gas nozzles per row of openings, with an equidistant arrangement of the gas nozzles in the direction of rotation, which promotes symmetrical combustion. The arrangement of the gas nozzles can vary for each row of openings.

[0025] Advantages for operation arise when several rows of openings are offset in the axial direction of the combustion chamber, with at least one air / gas supply arrangement being located in at least the most downstream row of openings.

[0026] Advantageous design options for optimized operation arise when the mixing opening(s) (with their outlets) are flush with the combustion chamber wall and / or recessed into the combustion chamber wall (the air channels protrude into the combustion chamber). Combinations with flush and recessed mixing openings are also possible.

[0027] Advantageous design options for optimized operation arise when the gas supply opening(s) are flush with the combustion chamber wall and / or are recessed into the combustion chamber relative to the wall and / or the respective mixing opening (with which they form the air / gas supply arrangement). Combinations with flush and recessed mixing openings are also possible.

[0028] Advantageous design options for optimized operation arise when at least one mixing opening is present in an air / gas supply arrangement, having a first flow cross-section A1, and when at least one mixing opening is present without an air / gas supply arrangement, having a second flow cross-section A2, where the size of the first flow cross-section A1 corresponds to the size of the second flow cross-section A2. This is achieved, for example, with circular or annular flow cross-sections, by a correspondingly larger outer diameter of the mixing opening within the air / gas supply arrangement.

[0029] Alternatively or additionally, the size of the first flow cross-section A1 can be larger than the size of the second flow cross-section A2. For example, with circular or annular flow cross-sections, this is achieved by a correspondingly much larger outer diameter of the mixing opening within the air / gas supply arrangement.

[0030] Alternatively or additionally, the outline of the first flow cross-section A1 can correspond to the outline of the second flow cross-section A2 (in size and / or shape). This results in a smaller first flow cross-section A1 compared to the second flow cross-section A2.

[0031] If several air / gas supply arrangements are available, a combination of these training variants is also possible.

[0032] Favorable flow conditions result when the gas supply opening has a diameter of approximately 1 / 2 to 1 / 6 of the diameter of the outlet of the mixing opening (or a corresponding ratio of flow cross-sections for non-circular flow cross-sections, after conversion to flow cross-sections).

[0033] The invention is advantageously applicable to a combustion chamber of the combustion chamber arrangement designed as an annular combustion chamber, wherein the combustion chamber is formed in a ring-shaped manner around a central axis, the wall having a radially inner wall and a radially outer wall. Advantageous design options for optimized operation arise when the gas supply opening(s), in particular the gas nozzle(s), is / are arranged on the radially inner wall and / or on the radially outer wall, particularly as air / gas supply arrangements.

[0034] The axial distance between the gas supply opening(s) and / or, if applicable, the mixing opening(s) and the inlet fuel nozzle(s) is between 0.65 and 0.85 times the height H of the combustion chamber. In an annular combustion chamber, the height H corresponds to the radial distance between the inner surfaces of the outer and inner walls of the casing. In a cylindrical combustion chamber, H corresponds to the diameter of the combustion chamber. The axial distance is measured from the central axis of the respective gas supply or mixing opening to the end face and / or the downstream end of the inlet fuel nozzle. If multiple rows of openings are present, the distance refers specifically to the most upstream row of openings and / or to the second, further downstream row of openings.Any existing rows of openings located further downstream can, for example, be arranged at a distance of 1 to 3 times the axial extent (with respect to the longitudinal axis) of the mixing opening(s) (e.g., a diameter) to the upstream row of openings (with respect to the upstream edges of the mixing openings).

[0035] Advantageous cooling possibilities for the combustion chamber arrangement result when the enclosure is double-walled, with an inner wall on the combustion chamber side and an outer wall on the outside.

[0036] Advantageous operational variations arise when a segmented gas manifold is used to supply gas to the gas inlet(s), with each segment having a separate fuel connection. This allows, for example, individual groups of gas nozzles to be controlled separately. Depending on the combustion chamber configuration, the manifold can be optimally designed and arranged, for example, in a ring shape, as a loop, at least substantially axially aligned with the gas nozzles, or upstream or downstream of them.

[0037] In an advantageous embodiment of the method, the combustion process is adjusted such that the combustion of the liquid fuel supplied via the fuel injectors is maintained, at least substantially, in an optimal operating condition with respect to the emission characteristics of the combustion chamber arrangement, i.e., at an air-fuel ratio that ensures minimal emissions of soot, carbon monoxide (CO), unburned hydrocarbons (UHC), nitrogen oxides (NOx), and carbon dioxide (CO2). The supply of gaseous fuel is additionally varied to achieve the overall air-fuel ratio required for the respective operating condition (from idle through takeoff to cruise flight).In this respect, the positioning of the gas supply openings downstream of the fuel nozzles is particularly advantageous, since this allows the liquid fuel to be burned in the first combustion zone at least partially without direct influences from the gaseous fuel.

[0038] Further advantageous embodiments of the method are described analogously in connection with design variants regarding the combustion chamber arrangement.

[0039] The invention will now be explained in more detail using exemplary embodiments and with reference to the drawings. The drawings show: Fig. 1A, 1 Legs Combustion chamber arrangement according to the prior art with one row of openings schematically in longitudinal section ( Fig. 1A ) and in top view ( Fig. 1B ), Fig. 2A, 2-leg combustion chamber arrangement according to the prior art with two rows of openings schematically in longitudinal section ( Fig. 2A ) and in top view ( Fig. 2B ), Fig. 3A to 3C a proposed combustion chamber arrangement with a row of openings comprising several gas nozzles in different arrangements schematically in longitudinal section ( Fig. 3A ) and in top view ( Fig. 3 B, Fig. 3 C) , Fig. 4 a sectional view of the combustion chamber arrangement along section line A according to Fig. 3A In schematic representation, Fig. 5, another embodiment of a combustion chamber arrangement with several gas nozzles in two rows of openings, schematically in longitudinal section, Figs. 6A to 6F, combustion chamber arrangements with different embodiments of gas nozzle arrangements with two rows of openings in schematic top view, Figs. 7A to 7F, different embodiments of air / gas supply arrangements, each with a mixing opening and a gas nozzle, as well as parts of the casing, schematically in longitudinal section, Figs. 8A, 8B, two different embodiments of air / gas supply arrangements and parts of the casing, each with an air channel, schematically in longitudinal section, Figs. 9A, 9, legs of air / gas supply arrangement ( Fig. 9A ) and a mixing port outside an air / gas supply arrangement ( Fig. 9B ) schematically in longitudinal section and Fig. 10 a further embodiment of a proposed combustion chamber arrangement, with the gas nozzle arranged on a radially inner wall, schematically in longitudinal section.

[0040] Fig. 1A Figure 1 shows a schematic longitudinal section representation of a combustion chamber arrangement 1 for use in an aircraft engine, as known from the prior art. Fig. 1A The figure partially schematically indicates an inner housing 4 and an outer housing 3 of an engine combustion chamber of an aircraft.

[0041] The combustion chamber arrangement 1 comprises a combustion chamber 100 designed as an annular combustion chamber with a combustion chamber 101 arranged in a circumferential ring around a central axis M, which is axially aligned along a longitudinal axis L. The combustion chamber 101 is bounded by a wall 5 of the combustion chamber arrangement 1 comprising a radially inner flame tube wall 5a and a radially outer flame tube wall 5b. The wall 5 is, by way of example, double-walled, with an inner wall 70 on the combustion chamber side and an outer wall 50 on the outside. By way of example, the wall 5 has a constant height H in its axial direction, starting from an end face 2, with the radially inner flame tube wall 5a and the radially outer flame tube wall 5b running parallel to each other. Further downstream there is a cross-sectional narrowing 23, with radially converging flame tube walls 5a, 5b, which leads into an outlet 24 of the combustion chamber arrangement 1.Downstream of outlet 24, a turbine guide wheel 6 of a turbine arrangement (not shown in full here) is connected.

[0042] On the inlet side of the combustion chamber 101, on the inlet-side end face 2 of the combustion chamber 100, several fuel nozzles 200 are arranged circumferentially, of which in the Fig. 1A The longitudinal section shown schematically depicts a fuel nozzle 200. During operation, a mixture 11 of liquid fuel and air 9 is added to the combustion chamber 101 by means of the fuel nozzle 200.

[0043] The liquid fuel is in particular a kerosene-based or kerosene-related fuel (e.g. Jet-A1, diesel or a synthetic substitute fuel (SAF - "sustainable aviation fuel")).

[0044] Downstream of the front face 2 and / or the downstream end of the fuel nozzle 200, several mixing openings 8 for adding mixing air 12 into the combustion chamber 101 during operation are arranged by way of example, which is diverted during operation from air 11 that surrounds the combustion chamber arrangement 1.

[0045] How Fig. 1B As shown in a schematic top view of the combustion chamber arrangement 1, the mixing openings 8 are arranged here by way of example in a circumferential row of openings 13. The mixing openings 8 of an opening row 13 are located at a uniform axial position and are arranged in the direction of rotation, circumferentially around the combustion chamber arrangement 10, preferably equidistant from each other.

[0046] How Fig. 1A As shown, the mixing openings 8 are arranged or formed in the radially inner flame tube wall 5a and in the radially outer flame tube wall 5b. The mixing openings 8 in the radially inner flame tube wall 5a and the radially outer flame tube wall 5b are, by way of example, arranged at the same axial position with respect to the longitudinal axis L. The mixing openings 8 each have an outlet 80 at their downstream end, which can be flush with the wall 5 with respect to the combustion chamber 101, as in the example shown in Fig. 1A The example shown illustrates the radially inner mixing openings 8. Alternatively, the mixing openings 8 can project into the combustion chamber 101 as an air duct comprising a collar, with the outlets 80 being radially offset into the combustion chamber 101.

[0047] In the double-walled design of the wall 5, the mixing opening 8 is designed as an air channel through the outer wall 50 and the inner wall 70 in order to counteract the outflow of the mixing air 12 through the air gap between the outer wall 50 and the inner wall 70.

[0048] Fig. 2A und Fig. 2B Figure 1 shows a combustion chamber arrangement 1 according to the prior art in a double-row variant, comprising two axially offset rows of openings 13. Within each row of openings 13, the mixing ports 8 are arranged equidistant from each other and at the same axial position. Relative to each other, the rows of openings 13 are arranged with an offset arrangement of the mixing ports 8 in the direction of rotation. During operation, mixing air 14 is added to the combustion chamber 101 through the row of openings 13 located further downstream. The flow cross-sections of the mixing ports 8 and / or radial positions of the outlets 80 can differ, for example, varying depending on the row of openings 13.

[0049] Fig. 3A, Fig. 3B und Fig. 3C The figures show a further development of the combustion chamber arrangement 1 according to the invention, wherein the combustion chamber arrangement 1 is designed for operation with gaseous fuel. The gaseous fuel can, in particular, be added to the combustion chamber 101 simultaneously with, or alternatively to, the liquid fuel.

[0050] For the sake of reduced complexity, the 200 fuel nozzles, for example, are not designed for operation with a gaseous fuel.

[0051] The gaseous fuel (hereinafter also referred to as Gas 16) is in particular hydrogen or a hydrogen-containing fuel gas and / or another fuel gas, for example methane or a methane-containing fuel gas.

[0052] At the in Fig. 3A, Fig. 3B und Fig. 3C In the illustrated embodiment, a plurality of gas nozzles 15 are provided, which are arranged downstream of the fuel nozzle 200 in the opening row 13 in the casing 5. In the Fig. 3A In the schematic longitudinal section of the combustion chamber arrangement 1 shown, a gas nozzle 15 is depicted.

[0053] Each of the gas nozzles 15 has a gas supply opening 150 at its downstream end.

[0054] At the in Fig. 3A, Fig. 3B und Fig. 3C In the illustrated embodiment, an opening row 13 is provided as an example.

[0055] How Fig. 3A As shown more precisely, the gas nozzles 15 are each arranged within one of the mixing openings 8, with each gas nozzle 15 and mixing opening 8 forming an air / gas supply arrangement 25. For symmetrical injection, the gas nozzles 15 are advantageously arranged centrally within their respective mixing openings 8, with the flow cross-section of the mixing opening 8 radially surrounding the gas supply opening 150. The gas nozzle 15 can be arranged perpendicular to the wall 5, or at right angles to the main flow direction within the combustion chamber 100 for the addition of the fuel gas. An arrangement with an angled orientation is also possible, such that the angle between the wall 5 and a central longitudinal axis of the gas nozzle 15 is less than 90°. The mixing openings 8 are preferably oriented at the same angle as the gas nozzle 15.

[0056] Due to the central arrangement of the gas nozzles 15 in the mixing openings 8, the gas 16 is introduced into an airflow at high velocity during operation. This advantageously allows the reaction zone of the gaseous fuel within the combustion chamber 101 to be shifted further into the combustion chamber 101, away from the gas nozzle 15 and / or the casing 5. In this way, the thermal stress on the gas nozzle 15 and / or the casing 5 is reduced.

[0057] How Fig. 3A As shown, in the illustrated embodiment, the gas nozzles 15 protrude into the combustion chamber 101. The gas supply opening 150 is, by way of example, flush with the downstream end of the mixing opening 8.

[0058] The flow cross-section of the gas nozzles 15 can be circular and / or in another shape, for example polygonal, elliptical or the like.

[0059] Fig. 3B Figure 1 shows a schematic top view of the combustion chamber arrangement 1, an embodiment in which each of the mixing openings 8 is assigned a gas nozzle 15 to form an air / gas supply arrangement 25.

[0060] Fig. 3C Figure 1 shows a schematic top view of the combustion chamber arrangement 1, illustrating an embodiment in which every second mixing opening 8 is assigned a gas nozzle 15 to form an air / gas supply arrangement 25. Mixing air 12 is supplied via the other mixing openings 8 without the addition of gas 16.

[0061] How Fig. 3A As shown, the axial distance a of the gas nozzles 15 and / or the mixing openings 8 (with respect to their respective central axis) from the inlet fuel nozzle 200 and / or the end face 2 is between 0.65 and 0.85 of the height H of the combustion chamber 101. This spacing allows a (partial) combustion reaction of the liquid fuel to occur upstream of the gas supply within the combustion chamber 101 during operation, with the fuel nozzle 200 advantageously being optimized for the combustion of liquid fuel. Simultaneously, the addition of the gaseous fuel takes place sufficiently far upstream to enable complete combustion of the gaseous fuel within the combustion chamber 101, which has a length typical for an aircraft engine.

[0062] The gas nozzles 15 are supplied with gaseous fuel, in particular by means of a manifold designed as a ring line 17, which is fed with fuel via a fuel connection 18. The ring line 17 can be, as shown in Fig. 3A, Fig. 3B und Fig. 3C The manifold is shown to be arranged axially at least near the gas nozzles 15. A different design and / or arrangement of the manifold would also be possible, for example further upstream or downstream of the gas nozzles 15.

[0063] A supply via a segmented manifold can also be advantageous, as shown for example in the cross-sectional view along section line A in Fig. 4 The diagram is shown schematically. Two fuel connections 18, 18.1 are provided, each supplying a segment 17.1, 17.2 of the ring line 17 with fuel. Each segment 17.1, 17.2 of the manifold, in particular the ring line 17, is assigned a fuel connection 18, 18.1. This allows for separate control of individual groups of gas nozzles 15 arranged on the respective segment 17.1, 17.2 of the manifold.

[0064] In Fig. 4 The ring-like design of the combustion chamber arrangement 1 is evident. This includes, by way of example, 12 air / gas supply arrangements 25, which are formed, by way of example, at the radially outer mixing openings 8. Furthermore, there are 12 fuel nozzles 200 and 12 mixing openings 8 without associated gas nozzles 15, which are arranged, by way of example, on the radial inner side of the combustion chamber 100.

[0065] Fig. 5 Figure 1 shows a variant design with two rows of openings 13. The upstream row of openings 13 is arranged with an axial distance a of approximately 0.65 to 0.85 of the height H of the combustion chamber ( Fig. 3A The first row of openings 13 is spaced 15 meters from the fuel nozzle 200. The second row of openings 13, located further downstream, is axially spaced, for example, between 1 and 3 times the diameter of the mixing opening 8 (with respect to the upstream edge). Gas 20 is added to the combustion chamber through gas nozzles 19 via the second row of openings 13, located further downstream. The gas nozzles 15 and the gas nozzles 19 are connected to the ring line 17 by way of example.

[0066] How Fig. 5 As shown, the gas nozzles 15 and 19 can project to different distances into the combustion chamber 101. For example, the air / gas supply arrangement 25 of the row of openings 13 arranged upstream of the combustion chamber 100 projects into the combustion chamber 101, while the row of openings 13 arranged downstream is flush with the wall 5. In the example shown, the downstream ends of the mixing openings 8 and the gas supply openings 150, 190 are each flush with each other.

[0067] Figuren 6A bis Fig. 6F Figure 1 shows exemplary arrangements of the gas nozzles 15, 19 with respect to the mixing openings 8 in the training variant with two rows of openings 13. Each row of openings 13 can be configured as described in Figure 1. Fig. 3B und Fig. 3C As shown, air-gas supply arrangements 25 are present in every or every nth mixing opening 8 (where n equals 2 to "number of mixing openings"), for example, in every first or second one. If several rows of openings 13 are present, air-gas supply arrangements 25 are preferably present at least in the row of openings 13 furthest downstream.

[0068] Fig. 6A shows a design variant in which the air / gas supply arrangements 25 are arranged in the further upstream row of openings 13, in every second mixing opening 8.

[0069] Fig. 6B Figure 1 shows a design variant in which the air / gas supply arrangements 25 are arranged in the further upstream row of openings 13, in each mixing opening 8.

[0070] Fig. 6C Figure 1 shows a design variant in which the air / gas supply arrangements 25 are arranged in the further downstream row of openings 13, in each mixing opening 8.

[0071] Fig. 6D Figure 1 shows a design variant in which the air / gas supply arrangements 25 are arranged in the further downstream row of openings 13, in every second mixing opening 8.

[0072] Fig. 6E Figure 1 shows a design variant in which the air / gas supply arrangements 25 are arranged in both existing rows of openings 13, in each mixing opening 8.

[0073] Fig. 6F Figure 1 shows a design variant in which the air / gas supply arrangements 25 are arranged in both existing rows of openings 13, in every second mixing opening 8.

[0074] Fig. 7A bis Fig. 7F Figure 1 shows exemplary arrangements of the mixing opening 8 and / or the gas supply opening 150, 190 in their radial positioning relative to the wall 5. In the embodiments according to Fig. 7A, Fig. 7C , Fig. 7E und Fig. 7F The enclosure 5 is exemplarily designed as a double wall, with the inner wall 70 and the outer wall 50. In the embodiments according to Fig. 7B und Fig. 7D The wall 5 is in each case exemplarily designed as a single wall.

[0075] At Fig. 7A und Fig. 7B Both the respective outlet 80 of the mixing opening 8 and the respective gas supply opening 150, 190 are flush with the wall 5 and correspondingly flush with each other.

[0076] At Fig. 7C und 7D The outlet 80 of the mixing opening 8 is flush with the wall 5, while the gas supply opening 150, 190 is offset into the combustion chamber 101, i.e. protrudes into the combustion chamber 101.

[0077] At Fig. 7E und Fig. 7F The outlets 80 are each radially offset into the combustion chamber 101, with the mixing openings 8 being designed as air channels by means of a collar. In the Fig. 7E In the illustrated embodiment, the gas supply opening 150, 190 is flush with the mixing opening 8 and thus also recessed into the combustion chamber 101. In the embodiment shown Fig. 7F In the illustrated embodiment, the gas supply opening 150, 190 is set further into the combustion chamber 101 than the outlet 80 of the mixing opening 8.

[0078] The different radial arrangements of the mixing ports 8 (with their outlets 80) and / or the gas supply ports 150, 190 allow for different mixing effects, particularly with the mixing air 12, 14 and / or the main flow within the combustion chamber 101. Depending on the combustion chamber design and / or operating conditions, one or another design variant or combination thereof may be advantageous. An advantageous design variant can be determined, for example, during test bench operation.

[0079] Fig. 8A und Fig. 8B Each figure shows a variant embodiment of an air / gas supply arrangement 25, wherein a radially circumferential air channel 21 is arranged at least partially in the mixing opening 8 around the gas nozzles 15, 19 to form an airflow 22 circulating around the gas nozzles 15, 19. The air channel 21 is arranged, in particular, coaxially to the respective gas nozzle 15, 19 and / or to the mixing opening 8. The air channel 21 contributes to more defined flow conditions of the airflow around the gas flow supplied by means of the gas nozzles 15, 19, which can, for example, serve as a kind of jacket air.

[0080] In the embodiment according to Fig. 8A The air duct 21 is flush with the outlet 80 of the mixing opening 8 and the gas supply opening 150, 190. In the case of the Fig. 8B In the illustrated embodiment, the air duct 21 is offset into the combustion chamber 101 opposite the mixing opening 8, while the gas nozzle 15, 19 is offset even further into the combustion chamber 101 opposite the air duct 21. A single-walled version of the enclosure 5 is also possible.

[0081] Fig. 9A und Fig. 9B Figure 1 shows exemplary flow cross-sectional areas of the gas nozzle 15, 19 and the gas supply opening 150, 190 and the mixing openings 8. In this example, the flow cross-sectional areas are circular, with a diameter D3 at the gas supply opening 150, 190 and at the first mixing opening 8 within the air / gas supply arrangement 25 (see Figure 1). Fig. 9 A) circular with an (outer) diameter D1 (flow cross-section with area A1 ≈ 0.25*Pi*(D1 2< -D3 2< )) and at a second mixing opening 8 outside an air / gas supply arrangement 25 circular with a diameter D2 (flow cross-section with area A2 = 0.25*Pi*D2 2< ).

[0082] Within the air / gas supply arrangement 25, the diameter D3 of the gas supply opening 150, 190 is, for example, 1 / 2 to 1 / 6 of the diameter D1 of the mixing opening 8. For example, the diameter D1 of the mixing opening 8 can be 10 mm and the diameter D3 of the gas nozzle 15, 19 can be 3 mm. The flow cross-sections are designed so that, across the entire operating range and taking into account a pressure drop across the combustion chamber selected during the design process, the velocity of the incoming fuel gas is higher than the velocity of the incoming mixing air, which is between 60 m / s and 140 m / s.

[0083] In the Figuren 9A und 9B In the illustrated embodiments, the outline of the first flow cross-section of the first mixing opening 8 corresponds to the outline of the second mixing opening 8, whereby, due to the circular (ring) shape, the diameter D1 is equal to the diameter D2. This results in a smaller area of ​​the first flow cross-section A1 compared to the second flow cross-section A2.

[0084] It is also possible to choose a correspondingly larger diameter D1, such that the size of the first flow cross-section A1 corresponds to the size of the second flow cross-section A2. Furthermore, it is possible to design the first flow cross-section to be larger than the second flow cross-section, whereby, in this example, the first diameter D1 is chosen to be much larger than the second diameter, D2.

[0085] Fig. 10 Figure 1 shows a design variant in which the gas supply opening 150, in particular the gas nozzle 15, is arranged on the radially inner flame tube wall 5a with respect to the central axis M, for example in the upstream row of openings 13. For this purpose, the gas 16 can be brought radially inwards from the outside by a suitable component, for example by struts or guide vanes in a pre-diffuser.

[0086] During operation, the liquid fuel is introduced into the combustion chamber 101 via the fuel nozzle 200. Alternatively or additionally, the gaseous fuel is introduced into the combustion chamber 101 via the gas nozzles 15 and, if applicable, the gas nozzles 19.

[0087] In an advantageous operating scenario, the fuel nozzle 200 is maintained in an emissions-optimized operating condition for at least a large portion of the operating time, meaning at an air-fuel ratio that ensures minimal emissions of soot, carbon monoxide, unburned hydrocarbons, nitrogen oxides, and / or carbon dioxide. The gaseous fuel is then varied to achieve the required overall air-fuel ratio for the respective operating condition, particularly from idle through takeoff to cruise flight.

[0088] The proposed gas turbine arrangement advantageously allows for high operational flexibility with comparatively low complexity, with operation using either liquid or gaseous fuel, or a combination of both fuels. Bezugszeichenliste

[0089] 1 Combustion chamber arrangement 100 Combustion chamber 101 Combustion chamber 2 Front side 200 Fuel nozzle 3 Outer housing 4 Inner housing 5 Enclosure 5 Inner flame tube wall 5 Outer flame tube wall 50 Outer wall 6 Turbine guide wheel 70 Inner wall 8 Mixing port 80 Outlet 9 Air 10 Air around combustion chamber 11 Mixture 12 Mixing air 13 Opening row 14 Mixing air 15 Gas nozzle 150 Gas supply port 16 Gas 17 Ring line 17.1 Segment 17.2 Segment 18 Fuel connection 18.1 Fuel connection 19 Gas nozzle 190 Gas supply port 20 Gas 21 Air duct 22 Airflow 23 Cross-sectional constriction 24 Outlet 25 Air / gas supply arrangement A1 First flow cross-section A2 Second flow cross-section D1 Diameter D2 Diameter D3 Diameter M Central axis L Longitudinal axis H Height a Distance

Claims

1. Gas turbine assembly having a turbine assembly and a combustor assembly (1), wherein the combustor assembly (1) comprises - a wall (5) that surrounds a combustion chamber (101) aligned along a longitudinal axis (L), and - at least one, preferably a plurality of, fuel nozzle(s) (200) arranged on the inlet side of the combustion chamber (101) for adding liquid fuel to the combustion chamber (101), wherein - the combustor assembly (1) is designed for operation with liquid and / or gaseous fuel, wherein a plurality of gas supply openings (15, 19) arranged downstream of the fuel nozzles (200) on the wall (5) are present, by means of which gaseous fuel can be introduced into the combustion chamber (101), - the combustor assembly (1) comprises a plurality of admixing openings (8), arranged downstream of the fuel nozzles (200) in the wall (5), for adding admixed air (12, 14) to the combustion chamber (101), - the gas supply openings (15, 19) are provided on a respective gas nozzle (150, 190) arranged within the admixing openings (8), wherein a respective gas nozzle (150, 190) forms an air / gas supply assembly (25) with an admixing opening (8), and - within the air / gas supply assembly (25), a diameter (D3) of the gas supply opening (15, 19) is 1 / 2 to 1 / 6 of a diameter (D1) of the admixing opening (8), characterized in that an axial distance (a) of the gas supply opening(s) (15, 19), and / or optionally of the admixing opening(s) (8), from the inlet-side fuel nozzle(s) (200) is between 0.65 and 0.85 times a height (H) of the combustion chamber (100) and in that the flow cross-sections of the gas supply opening (15, 19) and the admixing opening (8) of the respective air / gas supply assembly (25) are designed such that, over the entire operating range - from idling to take-off to cruising - taking into account the pressure drop across the combustion chamber selected in the design, the speed of the incoming gaseous fuel is higher than the speed of the incoming admixed air, which is between 60 m / s and 140 m / s.

2. Gas turbine assembly according to claim 1, characterized in that a circumferential air duct (21) is arranged in the respective admixing opening (8) around the respective gas nozzle (150, 190), at least in sections, to form an air flow surrounding the gas nozzle(s) (150, 190).

3. Gas turbine assembly according to claim 1 or 2, characterized in that a plurality of admixing openings (8) are arranged in at least one row of openings (13), wherein z admixing openings (8) are provided per row of openings (13), which are arranged in a uniform axial position and preferably equidistant from one another in the circumferential direction of the wall (5).

4. Gas turbine assembly according to claim 3, characterized in that an air / gas supply assembly (25) is formed per row of openings (13) in each nth admixing opening (8) with n = 2 to z, wherein n preferably forms the ordinal number of an integer quotient of z.

5. Gas turbine assembly according to claim 3 or 4, characterized in that a plurality of rows of openings (13) offset in the axial direction of the combustion chamber (101) are provided, wherein at least one air / gas supply assembly (25) is arranged in at least the row of openings (13) arranged furthest downstream.

6. Gas turbine assembly according to one of claims 1 to 5, characterized in that the admixing opening(s) (8) are designed flush with the wall (5) with respect to the combustion chamber (101) and / or are offset into the combustion chamber (101) with respect to the wall (5).

7. Gas turbine assembly according to one of the preceding claims, characterized in that the gas supply opening(s) (15, 19) are designed flush with the wall (5) with respect to the combustion chamber (101) and / or are offset into the combustion chamber (101) with respect to the wall (5), and / or optionally the respective admixing opening (8).

8. Gas turbine assembly according to one of claims 1 to 7, characterized in that the admixing openings (8) in the air / gas supply assemblies (25) have a first flow cross-section (A1), and in that the admixing openings (8) without an air / gas supply assembly (25) have a second flow cross-section (A2), wherein - the size of the first flow cross-section (A1) corresponds to the size of the second flow cross-section (A2) and / or - the size of the first flow cross-section (A1) is larger than the size of the second flow cross-section (A2) and / or - the outline of the first flow cross-section (A1) corresponds to the outline of the second flow cross-section (A2).

9. Gas turbine assembly according to one of the preceding claims, characterized in that the combustion chamber (101) is designed annularly circumferentially about a central axis (M), wherein the wall (5) has a radially inner flame tube wall (5a) and a radially outer flame tube wall (5b).

10. Gas turbine assembly according to claim 9, characterized in that the gas supply opening(s) (15, 19), in particular the gas nozzle(s) (150, 190), is / are arranged on the radially inner flame tube wall (5a) and / or on the radially outer flame tube wall (5b).

11. Gas turbine assembly according to one of the preceding claims, characterized in that the axial distance (a) of the gas supply opening (15, 19), and / or optionally of the admixing opening(s) (8), from the inlet-side fuel nozzle(s) (200) is between 0.3 and 1.0 times the height (H) of the combustion chamber (100).

12. Gas turbine assembly according to one of the preceding claims, characterized in that a segmented gas collecting line (17) for supplying gas to the gas supply opening(s) (15, 19) is provided, wherein each segment (17.1, 17.2) is assigned a separate fuel connection (18, 18.1).

13. Method for operating a gas turbine assembly designed according to one of claims 1 to 12, in which liquid fuel is added to the combustion chamber (101) via at least one, preferably a plurality of fuel nozzle(s) (200) arranged on the inlet side of a combustion chamber (101), wherein gaseous fuel is added to the combustion chamber (101) in addition to or as an alternative to the liquid fuel via a plurality of gas supply openings (15, 19) arranged downstream of the fuel nozzles (200) on the wall (5), characterized in that the gaseous fuel is added via one or a plurality of gas supply openings (15, 19), the axial distance (a) of which from the inlet-side fuel nozzle(s) is between 0.65 and 0.85 times a height H of the combustion chamber (100) and in that the flow cross-sections of the gas supply opening (15, 19) and of the admixing opening (8) of the respective air / gas supply assembly (25) are designed, taking into account the pressure drop across the combustion chamber selected in the design, such that over the entire operating range - from idling to take-off to cruising - the speed of the inflowing gaseous fuel is higher than the speed of the inflowing admixed air, which is between 60 m / s and 140 m / s.

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