Injector assembly for a gas turbine and aircraft

Abstract

The invention relates to an injector arrangement (100) for a gas turbine, in particular an aircraft engine, for introducing a gaseous fuel (31) and a liquid fuel (32) as well as air (30) into a combustion chamber (BK), having an injector shaft (1) and an injector main body (22) aligned along an injector longitudinal axis (L), wherein the injector main body (22) comprises: - a first gas channel (40) arranged centrally on the injector longitudinal axis (L) for introducing a gas flow into the combustion chamber (BK), - at least one air channel (5, 133, 134) arranged radially outwardly around the first gas channel (40) and - a liquid fuel injection (6) arranged radially around the first gas channel (40) for introducing the liquid fuel (32) into the combustion chamber (BK), wherein the injector arrangement (100) additionally for introducing the gaseous fuel (31).An advantageous emission characteristic is obtainable in that the injector arrangement (100) is designed to assume, in particular, two alternative configurations, between which the injector arrangement (100) can be switched during operation, wherein the first gas channel (40) can be flowed through in a first configuration with air, functioning as air injection, and in a second configuration with the gaseous fuel (31), functioning as gaseous fuel injection (Fig. 3).

Description

[0001] The invention relates to an injector arrangement for a gas turbine, in particular an aircraft engine, for introducing a gaseous fuel and a liquid fuel as well as air into a combustion chamber, with an injector shaft and an injector main body aligned along an injector longitudinal axis, wherein the injector main body comprises: a first gas channel arranged centrally on the injector's longitudinal axis for introducing a gas flow into the combustion chamber, at least one air channel arranged radially outwardly around the first gas channel and a liquid fuel injection arranged radially around the first gas channel for introducing the liquid fuel into the combustion chamber, The injector assembly is also configured to introduce the gaseous fuel. The invention further relates to an aircraft having an injector assembly.

[0002] An injector arrangement of the type mentioned above is described, for example, in DE 10 2022 201 182 A1. A fuel injector for the gaseous fuel is arranged radially outward around a central air channel arranged on a nozzle's longitudinal axis, and a liquid fuel injector is arranged.

[0003] The invention is based on the object of providing an injector arrangement of the type mentioned above and an aircraft with optimized emission characteristics.

[0004] The problem is solved for the injector arrangement with the features of claim 1 and for the aircraft with the features of claim 15.

[0005] With regard to the injector arrangement, it is provided that it is designed to assume (optionally or depending on the operation), in particular two alternative configurations, between which the injector arrangement can be switched during operation, wherein the first gas channel can be flowed through in a first configuration with air, functioning as air injection, and in a second configuration with the gaseous fuel, functioning as gaseous fuel injection.

[0006] The injector arrangement preferably has only the first gas channel as a gas fuel injection in the second configuration, no further gas fuel injection.

[0007] In the first configuration, the injector arrangement can be operated in a separate mode exclusively with the liquid fuel and cannot be flowed through by the gaseous fuel into the combustion chamber.

[0008] In the second configuration, the injector assembly can be operated both exclusively with gaseous fuel (without liquid fuel) and simultaneously in a combined operation with flow through both the gaseous fuel and the liquid fuel, and not exclusively with the liquid fuel.

[0009] The gaseous fuel is formed, in particular, from hydrogen or contains hydrogen. The liquid fuel is formed, in particular, from kerosene and / or a sustainable alternative fuel (SAF).

[0010] The changeover is preferably carried out by switching on and / or off the flow of gaseous fuel (by applying or reducing an excess pressure compared to the air pressure prevailing in the combustion chamber), in particular by opening and / or closing a fuel valve for the gaseous fuel within the fuel periphery of the aircraft, outside the injector arrangement.

[0011] In a preferred embodiment, the first gas channel comprises an air inflow opening in an upstream end section, which is arranged in particular centrally on the injector's longitudinal axis (i.e., coaxial with the section of the first gas channel extending downstream thereof). At least one, preferably two, gas-fuel transfer line(s) is / are arranged within (in particular exclusively) the injector main body, which gas-fuel transfer line(s) runs / run in particular radially (or radially axially) between a gas-fuel supply line, in particular between a gas-fuel ring reservoir arranged downstream of the gas-fuel supply line, and the first gas channel. In the first configuration, the gas-fuel transfer line(s) is / are closed (i.e., gaseous fuel cannot flow through it) and the air inflow is open (i.e., air can flow through it). In the second configuration, the air inflow opening is closed (i.e.,not through which air can flow) and the gaseous fuel transfer lines are open (i.e., through which gaseous fuel can flow). In particular, the upstream end section is exclusively through which air can flow (in the first configuration). The gaseous fuel ring reservoir is arranged, in particular, in the injector main body in a ring around the first gas channel (with the second gas channel interposed).

[0012] Preferably, at least one, preferably two, closing bodies are provided for switching between the configurations, which in the first configuration are adjusted (in particular pushed in) radially into the gas fuel transfer line(s) while releasing the air inflow opening (outside the first gas channel) to close the gas fuel transfer line(s) and release the air inflow opening, and in the second configuration are positioned radially centrally in or downstream of the air inflow opening in the first gas channel to close the air inflow opening and release the gas fuel transfer line(s).

[0013] It can expediently be provided that a closing body channel for the gaseous fuel to flow through is arranged in the at least one closing body, which channel is arranged such that it cannot be flowed through in the first configuration, in particular due to the positioning of the closing body(s), and such that it can be flowed through in the second configuration. The closing body channel can in particular be aligned with an upstream section parallel to the corresponding gaseous fuel transfer line and with a downstream section parallel to the first gas channel. In the second configuration, the closing body channel thus forms a flow connection between the (optionally respective) gaseous fuel transfer line and the first gas channel. In the first configuration, for example, the downstream section of the closing body channel is closed at its downstream end by an inner wall of the gaseous fuel transfer line.

[0014] For automated control of the changeover between the configurations using mechanical forces, in particular without the influence of electrical control signals within the injector arrangement, at least one spring-elastic actuating element is preferably provided for switching between the configurations. This actuating element effects the changeover between the first configuration and the second configuration by means of spring force in interaction with a pressure force applied by the gaseous fuel. The actuating element is designed in particular as a helical compression spring. The changeover can thus be effected by switching the flow of the gaseous fuel on and off outside the injector arrangement and automatically effect an adjustment of the corresponding configuration of the injector arrangement.

[0015] For example, the first configuration represents a resting state in which the actuator is in its resting position without any counteracting pressure force. In the second configuration, the actuator is adjusted while counteracting the pressure force.

[0016] The adjusting element is preferably arranged, in particular fastened, to the at least one closing body. Advantageously, the adjusting element can be securely mounted and / or guided on or in the closing body by means of a recess (optionally present in each case) in the closing body. In particular, the adjusting element is fully inserted into the recess(es) when pushed together. If two closing bodies are present, the recesses are preferably located in the same axial position, whereby, when the closing bodies are pushed together, they jointly form a cavity for receiving the adjusting element.

[0017] In a particularly advantageous embodiment, two closing bodies and two gaseous fuel transfer lines are arranged opposite one another in the direction of rotation with respect to the injector's longitudinal axis (i.e. in each case one gaseous fuel transfer line with an associated closing body opposite the other pairing), wherein the adjusting element is fastened at one end to one of the closing bodies. In the first configuration, the closing bodies are pushed radially apart by means of the adjusting element, thereby releasing the air inlet opening, and are adjusted into the gaseous fuel transfer lines, i.e. are pushed in (at least largely, in particular completely), and / or in the second configuration, the closing bodies are compressed radially against the spring force of the adjusting element by means of the pressure force of the gaseous fuel.-pushed, wherein the closing bodies are positioned centrally within the first gas channel, touching one another (with the air inlet opening closed). The respective closing bodies are preferably mounted and guided in the respective gas fuel transfer lines so as to be radially displaceable, wherein at least one radially outward-facing section of the respective closing body permanently projects into the respective gas fuel transfer line. The gas fuel transfer lines with the respective associated closing bodies can, for example, be arranged at a position of 90° and 270° in the circumferential direction relative to the position of the injector shaft. In the first configuration, the closing body channel is closed, in particular in cooperation with the inner wall of the (respective) gas fuel transfer line, so that the respective closing body acts as a closure for the gas fuel transfer lines.

[0018] Advantageous installation options arise when the first gas channel has the smallest flow cross-section, in particular the smallest diameter, at the axial position of the closing body(s). In this context, the presence of two closing bodies is particularly advantageous. This allows the closing bodies to be inserted through the air inlet opening into the first gas channel or onto the gas-fuel transfer lines during installation.

[0019] An advantageous flow characteristic can be obtained by means of the injector arrangement if the air channel is designed as a second gas channel which runs radially directly (i.e. without the interposition of a further fluid channel) around the first gas channel (in other words, a second gas channel is designed as an air channel radially directly around the first gas channel), wherein, for example, its upstream end is positioned at least substantially at the axial position of the upstream end of the air inlet opening.

[0020] Advantages, particularly with regard to assembly, arise when the first gas channel is arranged in a central body extending coaxially to the injector's longitudinal axis within the second gas channel, wherein the gas fuel transfer line(s) extend radially through the second gas channel and wherein, in particular, further support elements and / or second swirl elements for holding the central body are arranged radially extending within the second gas channel. The gas fuel transfer line(s) and / or further support elements and / or second swirl elements are distributed equidistant from one another in the second gas channel, in particular in the circumferential direction. The support elements and / or further second swirl elements preferably have a smaller inflow cross-section than the gas fuel transfer line(s).The gas fuel ring reservoir and / or the liquid fuel ring reservoir is / are arranged in particular radially outwardly around the second gas channel in the injector arrangement.

[0021] A low pressure loss within the injector arrangement is beneficial if the gas fuel transfer line(s) in the second gas channel are shaped in a flow-optimized manner and / or covered (e.g. by means of a wall), wherein the gas fuel transfer line, if necessary (i.e. if there are several gas fuel transfer lines), can each be designed to act, in particular, as a second swirl element.

[0022] A uniform introduction of the liquid fuel into the combustion chamber, without interruption during the changeover between configurations, can be ensured if the liquid fuel injection is arranged radially outwardly around the second gas channel and is designed to introduce the liquid fuel at the downstream end of the second gas channel into an air flow flowing through and / or exiting the second gas channel, in particular by means of at least one liquid fuel outlet opening opening at the downstream end of the second gas channel. The liquid fuel outlet opening can in particular be annular at least in sections and designed as a single outlet opening and / or comprise a plurality of discrete outlet openings.

[0023] For a favorable flow characteristic, at least one third gas channel and preferably also a fourth gas channel is / are arranged radially outwardly around the liquid fuel injection, wherein the third gas channel is designed as a radially outer air channel and optionally the fourth gas channel is designed as a radially outermost air channel.

[0024] In the aircraft it is provided that the aircraft comprises at least one engine comprising an injector arrangement according to one of the preceding claims, as well as a fuel periphery comprising at least one tank device each for gaseous fuel and for liquid fuel and line means for conducting the gaseous fuel and the liquid fuel from the respective tank device to the injector arrangement, wherein in the line means at least one fuel valve is arranged in each case for controlling and / or regulating the gaseous fuel and the liquid fuel, wherein upon closing of the fuel valve for gaseous fuel, with interruption of the flow of gaseous fuel, the injector arrangement assumes a first configuration and upon opening of the fuel valve for gaseous fuel the injector arrangement assumes a second configuration.

[0025] The invention will be explained in more detail below using exemplary embodiments with reference to the drawings. They show: Fig. 1 shows an injector arrangement according to the invention for introducing a gaseous fuel and a liquid fuel into a combustion chamber of an engine, in a first configuration, in a schematic representation in a longitudinal section along an injector longitudinal axis, Fig. 2 shows the injector arrangement in a second configuration in a schematic representation in a longitudinal section along an injector longitudinal axis, Fig. 3 shows the injector arrangement in the second configuration in a Fig. 2 longitudinal section rotated by 90° around the injector longitudinal axis, Fig. 4 the injector arrangement in the first configuration in the view according to Fig. 3 , Fig. 5 the injector arrangement in a plan view looking towards the combustion chamber and Fig. 6 a further embodiment of the injector arrangement, with a non-adjustable closure element, in the view according to Fig. 3 .

[0026] Fig. 1 shows, in a schematic representation in longitudinal section, an injector arrangement 100 for introducing fuel and air 30 into a combustion chamber BK of an engine, in particular of an aircraft. The injector arrangement 100 has an injector shaft 1 and an injector main body 22 arranged on the injector shaft 1. The injector main body 22 is aligned along an injector longitudinal axis L extending at an angle, in this case essentially at a right angle, to the injector shaft 1.

[0027] The injector assembly 100 is designed to operate with two types of fuel, a gaseous fuel 31 and a liquid fuel 32. The fuels can be supplied to the injector assembly 100 both simultaneously (in parallel) in a combined operation and individually, in a separate operation of liquid and / or gaseous fuel. For the fuel supply, both a gaseous fuel supply line 2 and a liquid fuel supply line 3 are arranged in the injector shaft 1. Fig. 1 The two fuel supply lines 2, 3 are, for example, routed parallel to each other.

[0028] The gaseous fuel 31 is formed, in particular, from hydrogen and / or contains hydrogen. The liquid fuel 32 is formed, in particular, from kerosene and / or a sustainable alternative fuel (SAF).

[0029] The aircraft has a correspondingly equipped fuel periphery, which comprises at least one tank device for gaseous fuel 31 and liquid fuel 32 (in Fig. 1 not shown). In addition, there are conduits for conveying the gaseous fuel 31 and the liquid fuel 32 to the injector arrangement 100. A fuel valve 16, 16' (cf. Fig. 2 ) for controlling and / or regulating the gaseous fuel 31 and the liquid fuel 32.

[0030] To supply the liquid fuel 32, the injector assembly 100 preferably has a liquid fuel annular reservoir 8 at the downstream end of the liquid fuel supply line 3. Starting from the liquid fuel annular reservoir 8, a liquid fuel injector 6 is guided within the injector main body 22 to a downstream end section of the injector main body 22. The liquid fuel injector 6 has, for example, discrete fuel channels and / or, at least in sections, a radially circumferential, connected fuel annular channel (not shown in detail here). In addition, the liquid fuel injector 6 can be designed, in particular, by means of swirl elements for swirling the liquid fuel 32 (not shown here). Heat shields 14 can preferably be provided to shield the fuel channels of the liquid fuel injector 6 against high heat input, for example from surrounding air channels.At the downstream end section, the liquid fuel injector 6 has at least one liquid fuel outlet opening 60, wherein several discrete openings or a circumferential ring opening may be present.

[0031] The injector assembly 100 comprises a first gas channel 40 arranged centrally on the injector's longitudinal axis L, which is designed and arranged to introduce a central gas flow into the combustion chamber BK. A flow body 12 with swirl elements can be arranged centrally on the injector's longitudinal axis L in the first gas channel 40 to impart a circumferential swirl to the central gas flow.

[0032] In particular, a second gas channel 5 is arranged as an air channel 50, radially encircling the first gas channel 40 directly (i.e., without the interposition of another fluid channel). The upstream end of the air channel 50 is positioned, for example, at least substantially at the level of the upstream end of the air inlet opening 10. At the downstream end of the air channel 50, the at least one liquid fuel outlet opening 60 is arranged for injecting the liquid fuel 32 into the air stream flowing through the second air channel 50.

[0033] The first gas channel 40 is preferably arranged in a central body 4 extending coaxially to the injector's longitudinal axis L within the second gas channel 5. The central body 4 is held and / or secured in the second gas channel 5, for example, by means of radially extending support elements 7 (for example, four to eight in number). The support elements 7 can, in particular, at least partially be designed as second swirl elements 70 and / or as gas fuel transfer lines 15, 15' (cf. Fig. 3 ) must be trained.

[0034] Arranged radially around the second gas channel 5 in the injector main body 22 is, in particular, an annular gas fuel reservoir 9, into which the gas fuel supply line 2 opens. The gas fuel reservoir 9 is positioned, in particular, at a greater axial distance from the combustion chamber BK than the liquid fuel reservoir 8.

[0035] Outer gas channels, for example two gas channels, are preferably arranged radially outwardly around the liquid fuel injection 6 in the downstream end section of the injector main body 22: a third gas channel 131 and a fourth gas channel 132 radially outwardly around the third gas channel 131. The outer gas channels 131, 132 form an outer air channel 133 and an outermost air channel 134.

[0036] According to the invention, the injector assembly 100 is designed such that it can be switched between two configurations during operation: a first configuration, in which the central, first gas channel 40 functions as an air injection port, with air 30 flowing through the first gas channel 40 during operation, and a second configuration, in which the central, first gas channel 40 functions as a gaseous fuel injection port, with gaseous fuel 31 (and not air 30) flowing through the first gas channel 40 during operation. In this way, the injector assembly 100 can advantageously be operated both in combined operation and in separate operation with the central, first gas channel 40 flowing through, thereby avoiding "running dry" of the first gas channel 40 and associated disadvantages (e.g., overheating, soot formation, etc.).The central flow contributes to extremely advantageous emission characteristics, with low nitrogen oxide (NO x ) emissions.

[0037] A further gaseous fuel injection, in addition to the first gas channel 40 in the second configuration, is preferably not present on the injector assembly 100.

[0038] In the first configuration, in particular, the injector assembly 100 is not flowed through by the gaseous fuel 31, and thus no gaseous fuel 31 is supplied to the combustion chamber BK. The first configuration is thus intended for separate operation with liquid fuel 32.

[0039] In the second configuration, in particular, the injector assembly 100 is flowed through by the gaseous fuel 31, and additionally by air at least through the second gas channel 5. Optionally, the liquid fuel injector 6 is flowed through with liquid fuel 32. The second configuration is thus intended for combined operation or separate operation with the gaseous fuel 31.

[0040] Fig. 1 shows the injector arrangement 100 in the first configuration, wherein the first gas channel 40 functions as an air injection device. For this purpose, the first gas channel 40 comprises an air inlet opening 10 in an upstream end section. The air inlet opening 10, like the remaining gas channel 40, is arranged centrally on the injector longitudinal axis L. In particular, the air inlet opening 10 terminates axially upstream with the upstream end of the injector main body 22 facing away from the combustion chamber BK. The upstream end section with the air inlet opening 10 can be flowed through exclusively by air.

[0041] In the first configuration, as in Fig. 1 As shown, the air inlet opening 10 is open, with the air inlet opening 10 being in flow communication with a section of the first gas channel 40 adjacent to the combustion chamber BK. Thus, in the first configuration, air 30 flows into the first gas channel 40 via the air inlet opening 10 and through the same into the combustion chamber BK. Gaseous fuel 31 is not supplied to the combustion chamber BK.

[0042] Fig. 2 shows the injector arrangement 100 in the second configuration, wherein the first gas channel 40 functions as a gaseous fuel injection. The air inlet opening 10 is closed by means of at least one closing body 11 arranged within the first gas channel 40, in particular directly downstream of the air inlet opening 10. Fig. 2 In the example shown, two closing bodies 11, 11' in the form of pistons 110, 110' are present, as described below in connection with Fig. 3 and Fig. 4 described in more detail. "Closed" here means that the flow connection to the section of the first gas channel 40 adjacent to the combustion chamber BK is interrupted, wherein the two closing bodies 11, 11', for example, are positioned at least substantially flow-tight in the air inlet opening 10 and / or (in particular immediately) downstream thereof, extending radially centrally in the gas channel 40.

[0043] The first gas channel 40 can advantageously have a minimum flow cross-section, in particular a minimum diameter, at the axial position of the closing bodies 11, 11'. In this way, the radial expansion of the closing bodies 11, 11' can be kept as small as possible, and the inlet opening 11, 11' can be used for the insertion of the closing body(s) 11, 11' during assembly.

[0044] For supplying the gaseous fuel 32 from the gas fuel ring reservoir 9 into the first gas channel 40, two gas fuel transfer lines 15, 15' are provided within the injector main body 22 (cf. Fig. 3 ). The gas fuel transfer lines 15, 15' extend radially between the gas fuel ring reservoir 9 and the first gas channel 40 through the second gas channel 5. The gas fuel transfer lines 15, 15' can preferably each have a flow-optimized (aerodynamically) shaped wall 18, 18' and / or be flow-optimized in order to reduce the flow resistance within the second gas channel 5. As Fig. 3 shows, the gas fuel transfer lines 15, 15' are arranged opposite one another in particular in the direction of rotation, for example at a position of 90° and 270° with respect to the injector shaft 1. The gas fuel transfer lines 15, 15' can additionally serve as a holder for the central body 4 in particular in the function of the support elements 7, wherein they are arranged equidistant from one another in the direction of rotation together with the (other) support elements 7 and / or swirl elements 70 (cf. also Fig. 5 ).

[0045] Fig. 3 shows in more detail the design and arrangement of the closing bodies 11, 11' in a Fig. 2 A representation of the injector arrangement 100 in longitudinal section, rotated by 90° around the injector longitudinal axis L. As Fig. 3 As shown, in the second configuration, the closing bodies 11, 11' each extend from the gas-fuel transfer lines 15, 15' into the center of the first gas channel 40 and are in sealing contact with each other at the injector's longitudinal axis L with respect to the air flowing toward the injector main body 22. Thus, the air inlet opening 10 is closed.

[0046] Closing body channels 17, 17' are formed within the closing bodies 11, 11', which, in the second configuration, form a flow connection from the gaseous fuel transfer lines 15, 15' into the first gas channel 40. The closing body channels 17, 17' are aligned, in particular, with an upstream first section parallel to the gaseous fuel transfer lines 15, 15' and with a downstream second section parallel to the injector longitudinal axis L. To seal the closing bodies 11, 11' from the gaseous fuel transfer lines 15, 15', circumferential sealing means 19, 19' are preferably provided. The closing bodies 11, 11' are mounted radially displaceably opposite one another in the gaseous fuel transfer lines 15, 15'. The flow cross-section of the closing body channels 17, 17' is in total sufficiently large to ensure a flow of the gaseous fuel 31 into the gas channel 40 with as little pressure loss as possible.By means of the arrangement and design of the two closing bodies 11, 11' shown here as examples, the gas fuel transfer lines 15, 15' and the closing body channels 17, 17' are open to flow in the second configuration.

[0047] To switch between the first and second configuration, Fig. 3 At least one spring-elastic adjusting element 20, e.g. in the form of a compression spring, is visible, which is fastened with one end to one of the closing bodies 11, 11'. Fig. 3 In the second configuration shown, the actuating element 20 is pushed together against the radially outward-acting spring force, wherein an opposite, radially inward-pointing pressure force is applied by the gaseous fuel, which overcomes the spring force and causes the closing bodies 11, 11' to be compressed until they come into contact on the injector longitudinal axis L.

[0048] The adjusting element 20 is fastened and guided in elongated recesses 111, 111' provided within the closing bodies 11, 11' in such a way that the closing bodies 11, 11' can be in contact with one another centrally on the injector longitudinal axis L. The recesses 111, 111' are preferably located in the same axial position and point with their openings radially in the direction of the injector longitudinal axis L, whereby in the illustrated, pushed-together position of the closing bodies 11, 11' they together form a cavity for receiving the adjusting element 20.

[0049] Fig. 4 shows in the Fig. 3 corresponding view of the injector arrangement 100, the arrangement of the closing bodies 11, 11' in the first configuration. The closing bodies 11, 11' are adjusted and / or pushed radially outwards into the gaseous fuel transfer lines 15, 15', closing the gaseous fuel transfer lines 15, 15' and opening the air inlet opening 10. The closing body channels 17, 17' of the two closing bodies 11, 11' are closed by the inner walls of the gaseous fuel transfer lines 15, 15' so that the gaseous fuel 31 cannot flow through them, wherein the downstream second section of the closing body channels 17, 17' rests with its downstream end against the inner wall of the gaseous fuel transfer lines 15, 15'.

[0050] The change from the second configuration to the first configuration is carried out by closing the fuel valve 16 of the gaseous fuel 31 (cf. Fig. 2 ). This eliminates the pressure force exerted by the gaseous fuel 31. As a result, the two closing bodies 11, 11' are pressed radially apart into the gaseous fuel transfer lines 15 by the spring force applied by the actuating element 20. In this way, the air inlet opening 10 is opened. The first configuration thus forms a rest state in which the actuating element is in the rest position without counteracting the pressure force.

[0051] The change from the first configuration to the second configuration is carried out by opening the fuel valve 16 of the gaseous fuel 31 (cf. Fig. 2 ), whereby the pressure force acts on the two closing bodies 11, 11' and presses them together.

[0052] Fig. 5 shows, in a plan view of the injector arrangement 100 looking toward the combustion chamber BK, an exemplary arrangement of the support elements 7 and / or second swirl elements 70 and the gaseous fuel transfer lines 15, 15' in the second gas channel 5. By way of example, a total of eight support elements 7 and / or swirl elements 70, including the gaseous fuel transfer lines 15, 15', are arranged. To reduce flow resistance, the support elements 7 and / or swirl elements 70 preferably have a smaller cross-sectional structure than the gaseous fuel transfer lines 15, 15'.

[0053] Fig. 6 shows a possible design variant of the injector assembly 100 for an operating scenario with a continuously flowing gaseous fuel. The air inlet opening 10 is permanently closed by a closure 21 that is immovable during operation.

[0054] The proposed injector arrangement 100 advantageously enables extremely low-emission operation within different operating scenarios with different fuels. Bezugszeichenliste

[0055] 1Injector shaft 100Injector arrangement 2Gaseous fuel supply line 3Liquid fuel supply line 4Central body 40First gas channel 5Second gas channel 50Air channel 6Liquid fuel injection 60Liquid fuel outlet opening 7Support element 70Second swirl element 8Liquid fuel ring reservoir 9Gaseous fuel ring reservoir 10Inlet opening 11, 11'Closing body 110, 110'Piston 111Recess 12Flow body 13Swirl elements 131Third gas channel 132Fourth gas channel 133Outer air channel 134Outermost air channel 14Heat shield 15, 15'Gaseous fuel transfer line 16, 16'Fuel valve 17, 17'Closing body channel 18, 18'Wall 19, 19'Sealant 20Actuator 21Closure 22Injector main body 30Air 31Gaseous fuel 32Liquid fuel BKCombustion chamber LInjector longitudinal axis

Claims

1. Injector arrangement (100) for a gas turbine, in particular an aircraft engine, for introducing a gaseous fuel (31) and a liquid fuel (32) as well as air (30) into a combustion chamber (BK), with an injector shaft (1) and an injector main body (22) aligned along an injector longitudinal axis (L), wherein the injector main body (22) comprises: - a first gas channel (40) arranged centrally on the injector longitudinal axis (L) for introducing a gas flow into the combustion chamber (BK), - at least one air channel (50, 133, 134) arranged radially outwardly around the first gas channel (40) and - a liquid fuel injection (6) arranged radially around the first gas channel (40) for introducing the liquid fuel (32) into the combustion chamber (BK), wherein the injector arrangement (100) additionally is arranged to introduce the gaseous fuel (31), characterized by thatthe injector arrangement (100) is designed to assume, in particular, two alternative configurations, between which the injector arrangement (100) can be switched during operation, wherein the first gas channel (40) can be flowed through in a first configuration with air (30), functioning as air injection, and in a second configuration with the gaseous fuel (31), functioning as gaseous fuel injection.

2. Injector arrangement (100) according to claim 1, characterized by that the first gas channel (40) comprises an air inlet opening (10) in an upstream end section, which is arranged in particular centrally on the injector longitudinal axis (L), and thatat least one, preferably two, gas fuel transfer line(s) (15, 15') is / are arranged within the injector main body (22), which is / are arranged between a gas fuel supply line (2), in particular between a gas fuel ring reservoir (9) arranged downstream of the gas fuel supply line (2), and the first gas channel (40), and in particular runs / runs radially, wherein in the first configuration the gas fuel transfer line(s) (15, 15') is / are closed and in the second configuration the air inflow opening (10) is closed.

3. Injector arrangement (100) according to claim 2, characterized by thatfor switching between the configurations, at least one, preferably two, closing bodies (11, 11') are present, which in the first configuration are adjusted radially into the gas fuel transfer line(s) (15, 15') to close the gas fuel transfer line(s) (15, 15') while opening the air inflow opening (10) and are positioned radially centrally in or downstream of the air inflow opening (10) in the first gas channel (40) in the second configuration to close the air inflow opening (10) while opening the gas fuel transfer line(s) (15, 15').

4. Injector arrangement (100) according to claim 3, characterized by thatin which at least one closing body (11, 11') is arranged a closing body channel (17, 17'), in particular for the flow through of the gaseous fuel (31), which is arranged in particular by means of the positioning of the closing body(s) (11, 11') such that it cannot be flowed through in the first configuration and such that it can be flowed through in the second configuration.

5. Injector arrangement (100) according to one of the preceding claims, characterized by that for switching between the configurations, at least one spring-elastic actuating element (20) is provided, which effects the switching between the first configuration and the second configuration by means of spring force in cooperation with a pressure force applied by the gaseous fuel.

6. Injector arrangement (100) according to claim 5, characterized by thatthe first configuration forms a rest state in which the actuating element (20) is in the rest position without counteracting the pressure force and that in the second configuration the actuating element (20) is adjusted with counteracting the pressure force.

7. Injector arrangement (100) according to at least claims 3 and 5, characterized by that the adjusting element (20) is arranged, in particular fastened, to the at least one closing body (11, 11').

8. Injector arrangement (100) according to claim 7, characterized by thattwo closing bodies (11, 11') and two gaseous fuel transfer lines (15, 15') are arranged opposite one another in the circumferential direction with respect to the injector's longitudinal axis (L), wherein the actuating element (20) is fastened at one end to one of the closing bodies (11, 11'), wherein in the first configuration the closing bodies (11, 11') are pressed apart radially into the gaseous fuel transfer lines (15, 15') by means of the actuating element (20) while releasing the air inflow opening (10), and / or in the second configuration the closing bodies (11, 11') are pressed together radially by means of the pressure force of the gaseous fuel against the spring force of the actuating element (20), wherein the closing bodies (11, 11') are positioned centrally within the first gas channel (40) in contact with one another.

9. Injector arrangement (100) according to one of claims 3 to 8, characterized by thatat the axial position of the closing body(s) (11, 11') the first gas channel (40) has a smallest flow cross-section, in particular a smallest diameter.

10. Injector arrangement (100) according to one of the preceding claims, characterized by that the air duct (50) is designed as a second gas duct (5) which runs radially directly around the first gas duct (40), wherein, for example, its upstream end is positioned at least substantially at the axial position of the upstream end of the air inlet opening (10).

11. Injector arrangement (100) according to claim 10, characterized by thatthe first gas channel (40) is arranged in a central body (4) extending coaxially to the injector longitudinal axis (L) within the second gas channel (5), wherein the gas fuel transfer line(s) (15, 15') extend(s) radially through the second gas channel (5) and wherein, in particular, further support elements (7) and / or second swirl elements (70) for holding the central body (12) are arranged radially extending within the second gas channel (5).

12. Injector arrangement (100) according to claim 11, characterized by that the gas fuel transfer line(s) (15, 15') in the second gas channel (5) are aerodynamically shaped and / or lined, wherein the gas fuel transfer line (15, 15'), if appropriate, can each be designed to act in particular as a second swirl element (70).

13. Injector arrangement (100) according to one of claims 10 to 12, characterized by thatthe liquid fuel injector (6) is arranged radially outwardly around the second gas channel (5) and is designed to introduce the liquid fuel at the downstream end of the second gas channel (5) into an air flow flowing through and / or exiting the second gas channel (5), in particular by means of at least one liquid fuel outlet opening (60) opening at the downstream end of the second gas channel (5).

14. Injector arrangement (100) according to one of the preceding claims, characterized by that at least one third gas channel (131) and preferably also a fourth gas channel (132) is / are arranged radially outwardly around the liquid fuel injection (6), wherein the third gas channel (131) is designed as a radially outer air channel (133) and optionally the fourth gas channel (132) is designed as a radially outermost air channel (134).

15. Aircraft with at least one engine comprising an injector arrangement (100) according to one of the preceding claims, and with a fuel periphery comprising at least one tank device each for gaseous fuel and for liquid fuel and line means for conducting the gaseous fuel and the liquid fuel from the respective tank device to the injector arrangement (100), wherein at least one fuel valve (16, 16') for controlling and / or regulating the gaseous fuel and the liquid fuel is arranged in the line means, wherein upon closing of the fuel valve (16) for gaseous fuel, with interruption of the flow of gaseous fuel, the injector arrangement (100) assumes a first configuration and upon opening of the fuel valve (16) for gaseous fuel, the injector arrangement (100) assumes a second configuration.

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