RU2774255C1 - Aerodynamic components of the stator with nozzles and methods for cleaning the turbomachine - Google Patents

Abstract

FIELD: mechanical engineering.

SUBSTANCE: invention relates to the field of turbomachines. An aerodynamic component (130, 250) of the stator is proposed to be located inside the path (500) of the working fluid flow of the turbomachine (1000); moreover, the aerodynamic component (130, 250) of the stator has a removable part (137-2, 137-3, 137-4) on which one or more nozzles (135, 255) are located for liquid injection into the path (500) of the stream; in this case, the injected liquid comes from a pipeline (134, 254) located inside relative to the aerodynamic component (130, 250) of the stator and communicating through the fluid with a tube (120, 220) located outside the component (130, 250). In addition, a method for cleaning a turbomachine by injecting a washing liquid from one or more aerodynamic components of the stator is described.

EFFECT: invention makes it possible to increase the efficiency of cleaning the surfaces of rotating vanes and fixed blades of a turbomachine.

13 cl, 11 dwg

Description

FIELD OF THE INVENTION

[0001] The subject matter described herein relates to nozzle stator aerodynamic components and methods for cleaning a turbomachine, as well as turbomachines comprising and/or being cleaned by such methods.

BACKGROUND OF THE INVENTION

[0002] Turbomachines, such as rotary compressors and rotary turbines, are machines configured to process a working fluid flowing within the flow path during operation of the machine. The turbine transfers energy from the working fluid to the rotor of the machine. The compressor transfers energy from the machine rotor to the working fluid. The flow path is partly determined by the machine rotor surfaces and partly by the machine stator surfaces.

[0003] During operation, the turbomachine, in particular the surfaces delimiting its flow path, become contaminated; this is especially true for turbomachines used in the oil and gas industry. Contaminants can form from the working fluid composition and/or from the substances or droplets or particles carried by the working fluid. Dirt is even capable of firmly adhering to surfaces, restricting the flow path; typical surfaces subject to contamination are the airfoils of (rotating) blades and (stationary) blades of a turbomachine.

[0004] A solution for cleaning a gas turbine compressor is known from US patent application US 2007/0028947 A1. In accordance with this solution, the flushing unit is located at the compressor bell in front of its struts and includes a number of nozzles that release water droplets.

[0005] The flushing assembly, located at the compressor bell in front of its struts, is easy to install because the bell is large enough and easily accessible due to its location on the inlet of the machine.

[0006] However, the flushing unit, located at the bell of the compressor in front of its struts, is only fully effective for cleaning the struts.

[0007] Accordingly, it would be desirable to have a cleaning system and method that effectively cleans the (stationary) blades and/or (rotating) blades of a turbomachine, preferably also the (stationary) blades and/or (rotating) blades away from the inlet of the turbomachine.

SUMMARY OF THE INVENTION

[0008] In accordance with one aspect, the subject matter described herein relates to an aerodynamic stator component for positioning within a turbomachine working fluid flow path; the component comprising: a conduit configured to receive fluid from the tube and one or more nozzles in fluid communication with said conduit and configured to inject fluid into the flow path; wherein the component further comprises a removable part, and one or more nozzles are located in the removable part.

[0009] In accordance with another aspect, the subject matter described herein relates to an aerodynamic stator component for positioning within a turbomachine working fluid flow path; the component comprising: a conduit configured to receive fluid from the tube and one or more nozzles in fluid communication with said conduit and configured to inject fluid into the flow path; wherein one or more nozzles are located inside relative to the posts protruding from the aerodynamic surfaces of the aerodynamic component of the stator.

[0010] The stator aerodynamic components described herein can be used to inject a flushing fluid, such as water, in particular demineralized water, and possibly detergent; however, they can also be used to eject other fluids suitable for particular turbomachine applications.

[0011] In accordance with another aspect, the subject matter described herein relates to a method for cleaning a turbomachine; and the method includes the step of washing the blades and/or blades of the turbomachine by injecting a washing liquid from at least one stator aerodynamic component located in the flow path of the working fluid of the turbomachine.

[0012] According to another aspect, the subject matter described herein relates to a turbomachine comprising at least one stator aerodynamic component; wherein the aerodynamic component of the stator is located within the working fluid flow path of the turbomachine; wherein the component comprises: a pipeline configured to receive liquid from the tube, and one or more nozzles in fluid communication with said pipeline and configured to inject liquid into the flow path.

BRIEF DESCRIPTION OF GRAPHICS

[0013] A more complete appreciation of the described embodiments of the invention and many of its attendant advantages can be easily obtained and a better understanding of the invention in the course of studying the following detailed description, considered in connection with the accompanying drawings, and:

in Fig. 1 is a partial schematic longitudinal sectional view of one embodiment of a turbomachine, namely a compressor;

in Fig. 2 is a schematic cross-sectional view of the first embodiment of the turbomachine brace shown in FIG. one;

in Fig. 3 is a schematic cross-sectional view of the second embodiment of the turbomachine brace shown in FIG. one;

in Fig. 4 is a schematic cross-sectional view of a third embodiment of the turbomachine brace shown in FIG. one;

in Fig. 5 is a schematic front sectional view of an embodiment of the struts of the turbomachine shown in FIG. one;

in Fig. 6 is a schematic cross-sectional view of a first embodiment of a (fixed) blade and an embodiment of a set of (rotating) blades of the turbomachine shown in FIG. one;

in Fig. 7 is a schematic cross-sectional view of a second embodiment of the (fixed) blade and an embodiment of the (rotating) blade assembly of the turbomachine shown in FIG. one;

in Fig. 8 is a schematic cross-sectional view of a third embodiment of a (fixed) blade and an embodiment of a set of (rotating) blades of the turbomachine shown in FIG. one;

in Fig. 9 is a schematic cross-sectional view of the fourth embodiment of the turbomachine brace shown in FIG. one;

in Fig. 10 is a schematic cross-sectional view of the fifth embodiment of the turbomachine brace shown in FIG. one; and

in Fig. 11 shows a block diagram of an embodiment of a purification method.

DETAILED DESCRIPTION OF EMBODIMENTS

[0014] To clean a contaminated surface, a washing liquid, such as water, can be sprayed onto the surface from one or more nozzles. Cleaning is very effective if the nozzle is very close to the surface to be cleaned. Dirt deposits on the blades disrupt the aerodynamic flow around them, resulting in a reduction in the efficiency of the entire turbine; in addition, uneven deposits of dirt on the blades can cause vibration; thus, efficient cleaning of the blades is an advantage.

[0015] In a turbomachine, a strut or (fixed) vane is located proximate a set of (rotating) vanes immediately behind the strut or vane. As the rotor rotates, the distance between the blade of the blade set and the spacer or blade first decreases, reaches a minimum value, and then increases. More precisely, during the rotation of the rotor, the distance between the leading edge region of the blade of the set of blades and the region of the trailing edge of the spacer or blade first decreases, reaches a minimum value, and then increases.

[0016] As described herein, it has been found that a specially designed stator aerodynamic component, such as a strut or a (fixed) vane, equipped with at least one nozzle can advantageously be used to inject flush fluid from at least one nozzle, which bathes the (rotating) vanes and/or (stationary) vanes downstream, preferably immediately downstream of the brace or vane. The flush fluid injection nozzles can be located in the region of the trailing edge of the stator aerodynamic component, which is advantageous.

[0017] Since the strut or vane is stationary, the flushing liquid can be easily supplied to the strut or vane continuously, for example, through a supply pipe, which may be located outside the turbomachine.

[0018] The use of embodiments of the new stator aerodynamic component differs from traditional turbomachine washing methods in which washing is performed from outside the turbomachine. Advantageously, embodiments of the new stator aerodynamic component and turbomachine "internal" flushing method can be used for any (rotating) blades and/or (stationary) blades, even if they are located far from the inlet and outlet of the turbomachine, since the system cleaning (e.g., at least an aerodynamic stator component equipped with at least one flushing nozzle) is integrated into components considered standard for a turbomachine and/or matches the internal dimensions/space volume of the turbomachine to clean the inside (or interior) of the turbomachine.

[0019] Below will be given detailed reference to embodiments of the description, one or more examples of which are illustrated in the drawings. Each of the examples is provided to clarify the description and not to limit the present description. As such, it will be apparent to those skilled in the art that various modifications and variations can be made within the scope of this disclosure without departing from the scope or spirit of this disclosure. Reference in this specification to "one embodiment" or "an embodiment" or "some embodiments" means that a particular feature, structure, or characteristic described in connection with an embodiment is included in at least one embodiment of the described subject matter. Thus, the occurrence of the phrase "in one embodiment", "in an embodiment" or "in some embodiments" in various places throughout this specification does not necessarily refer to one(s) and the same(s) ) implementation of the invention. In addition, specific features, structures, or characteristics can be combined in any suitable manner in one or more embodiments.

[0020] When representing elements of various embodiments, the singular and plural forms and the word "specified" are intended to indicate that one or more elements exist. The terms "comprising", "including" and "having" are intended to indicate inclusion and mean that additional elements may exist in addition to the listed elements.

[0021] Referring now to the drawings: FIG. 1 shows a partial schematic longitudinal sectional view of an embodiment of a turbomachine, namely a compressor 1000.

[0022] The compressor 1000 is divided into a bell section 100 and a compression section 200. Section 100 is enclosed in a housing 110 of the bell section, which is part of the compressor stator. Section 200 is enclosed in a compression section housing 210 which is part of the compressor stator. Housings 110 and 210 are connected to each other and may be a single unit or consist of multiple parts attached to each other. The flow path 500 runs inside the compressor 1000. The axis of rotation of the compressor 1000 is indicated by XX.

[0023] The bell section 100 includes a set of spacers 130 that are parts of the compressor stator.

[0024] The compression section 200 includes stator blades and rotor blades. In particular, in the direction from the inlet to the outlet, i.e. from the low pressure side of the compressor (in Fig. 1 on the left) to the high pressure side of the compressor (in Fig. 1 on the right), the first set of blades 230 is located, the first set of blades 240 (compressor first stage), second blade set 250, second blade set 260 (compressor second stage). Blades 230 and 250 are parts of the stator and blades 240 and 260 are parts of the rotor.

[0025] The flow path 500 is partially defined by the airfoils of the struts 130, vanes 230 and 250, vanes 240 and 260; in other words, these aerodynamic components are located in the working fluid flow path 500 of the turbomachine 1000.

[0026] In accordance with the embodiment shown in FIG. 1, compressor 1000 includes two cleaning units, one in bell section 100 and one in compression section 200. It should be noted that according to modifications of this embodiment, only one cleaning unit is provided (for example, only one node in the bell section 100 or only one node in the compression section 200), or three cleaning nodes (i.e., one node in the section 100 bell and two nodes in the compression section 200, one for each compression stage of the compressor), or even more cleaning nodes.

[0027] The first cleaning unit shown in FIG. 1 includes conduit 134 and, for example, three nozzles 135 fluidly connected to conduit 134 through, for example, three conduits 136. Flushing fluid enters conduit 134 from tube 120; in particular, conduit 134 is positioned entirely within brace 130, and conduit 120 extends outside compressor 1000, passes through casing 110, and reaches conduit 134. Injection of flushing fluid into flow path 500 is accomplished by nozzles. It should be noted that according to the modifications of this embodiment, the number of nozzles may vary, but is more than one.

[0028] As can be understood from FIG. 5, the compressor 1000 has several struts 130, namely six struts. In the embodiment shown in FIG. 1, at least one of the spacers has a pipeline and one or more nozzles; however, it is preferred that this configuration be similar to one more, or two, or three, or more, or all of the spacers (as shown in Fig. 5).

[0029] The washing liquid injected from the nozzles 135 is very effective in cleaning the blades 230 of the turbomachine 1000 located immediately downstream of the struts 130 of the turbomachine 1000. The washing liquid injected from the nozzles 135 is also effective in cleaning the blades 240 of the turbomachine 1000, which, in turn, are located immediately downstream of the blades 230 of the turbomachine 1000.

[0030] The second cleaning unit shown in FIG. 1 includes conduit 254 and, for example, two nozzles 255 fluidly connected to conduit 254 through, for example, two conduits 256. Flushing fluid enters conduit 254 from tube 220; in particular, conduit 254 is positioned entirely within vane 250, and conduit 220 extends outside compressor 1000, passes through housing 210, and reaches conduit 254. Injection of flushing fluid into flow path 500 is accomplished by nozzles. It should be noted that according to the modifications of this embodiment, the number of nozzles may vary, but is more than one.

[0031] As can be understood, compressor 1000 has a set of blades 250. In the embodiment shown in FIG. 1, at least one of the vanes 250 has a conduit and one or more nozzles, however it is preferred that this configuration be the same as one or more or all of the vanes.

[0032] The washing liquid injected from the nozzles 255 is very effective in cleaning the vanes 260 of the turbomachine 1000 immediately downstream of the vanes 250 of the turbomachine 1000.

[0033] From the foregoing, it is clear that the stator aerodynamic component containing the cleaning assembly can be a bell brace (for example, brace 130), or an input guide vane (for example, vane 230), or an intermediate guide vane (for example, vane 250).

[0034] As shown in FIG. 2 and FIG. 3 and FIG. 4, the aerodynamic component of the stator, such as the brace 130, may be divided into a leading edge region 131, a trailing edge region 132, and an intermediate region 133. According to these embodiments, component nozzles 135-2, 135-3, 135-4 are located in the region 132 trailing edge so as to be in the optimum position for effective injection of flushing fluid; however, the nozzles 135-2, 135-3, 135-4 are positioned differently as explained below. According to these embodiments, the component conduit 134 is located in the leading edge region 131, where there is enough space to accommodate even a large spacer; and it should be noted that the position of the pipeline 134 in these three figures is the same, but may differ according to other embodiments.

[0035] As shown in FIG. 2, there is at least one nozzle 135-2 (for receiving the washing liquid from the channel 136-2) configured to inject the washing liquid in the injection direction ED-2 corresponding to the flow direction FD of the flow path 500; the angle has a tolerance of +/-5°. In this case, the nozzle is at the end of the trailing edge region 132.

[0036] As shown in FIG. 3, there is at least one nozzle 135-3 (for receiving flushing liquid from channel 136-3) configured to inject flushing fluid in the injection direction ED-3 at an angle to the flow direction FD of the flow path 500, wherein the angle of inclination is in the range from -5° to -90°; the angle has a tolerance of +/-5°. In this case, the nozzle is located on the first side surface of the region 132 of the trailing edge.

[0037] As shown in FIG. 4, there is at least one nozzle 135-4 (for receiving flushing fluid from channel 136-4) configured to inject flushing fluid in the injection direction ED-4 at an angle to the flow direction FD of the flow path 500, wherein the angle of inclination is in the range from +5° to +90°; the angle has a tolerance of +/-5°. In this case, the nozzle is located on the second side surface of the region 132 trailing edge.

[0038] It should be noted that the nozzle can be configured to inject liquid in different directions, i.e., the injected liquid takes the form of a wide cone; alternatively, the shape of the wide cone of the injected liquid can be achieved by a combination of the operation of a set of nozzles mounted on the component.

[0039] Additionally, it should be noted that the nozzles of the same component can be configured to inject liquid in different directions. For example, as shown in FIG. 1, the upper (first radial position) nozzle of the brace 130 can inject liquid in the first direction, the middle nozzle (second radial position) of the brace 130 can inject liquid in the second direction, and the lower nozzle (third radial position) of the brace 130 can inject liquid in the third direction. .

[0040] As shown in FIG. 2, Fig. 3 and FIG. 4, the component has a removable part 137-2, 137-3, 137-4, and nozzles 135-2, 135-3, 135-4 are located in the removable part 137-2, 137-3, 137-4. As a rule, in embodiments other than those shown in these figures, the nozzles of the cleaning unit and/or the pipeline of the cleaning unit can be located in a removable part. The detachable part can be used to simplify the repair of the compressor 1000. The detachable part can be used to simplify the configuration of the compressor 1000 according to the requirements of, for example, the customer; in fact, for example, the spacer body 130 in these figures remains unchanged, and part 137-2, or part 137-3, or part 137-4 can be easily installed on the body based on an application or requirement.

[0041] In FIG. 5 shows a possible arrangement of a plurality of nozzles on struts 130 of the compressor 1000 shown in FIG. 1. Nozzles are located at the ends of the strut trailing edge areas. Also, the nozzles 137 are located on the inner wall defining the flow path 500 in the socket section 100. In addition, the nozzles 138 are located on the outer wall defining the flow path 500 in the bell section 100. These three arrangements can be combined in any possible way, regardless of the arrangement shown in FIG. 5.

[0042] It should be noted that even if not shown in any figure, the nozzles may be located on the inner and/or outer wall delimiting the flow path 500 in positions other than the position of the bell. In this case, they may be located between the first stage (eg, vanes 240) of compressor 1000 and the last stage (eg, vanes 260) of compressor 1000, such as near the vanes (eg, vanes 250).

[0043] In FIG. 6, FIG. 7 and FIG. 8 shows three embodiments of fixed vane 250, namely 250-6, 250-7, and 250-8, and their effect on rotating vanes 260 of compression stage compressor 1000. Arrow R indicates the direction of rotation of vanes 260. In the embodiment shown in FIG. . 6, the nozzle 135-6 is located at the end of the trailing edge; it injects the washing liquid in the injection direction ED-6 corresponding to the flow direction FD of the flow path 500. In the embodiment shown in FIG. 7, a nozzle 135-7 is positioned at the end of the trailing edge and injects the flushing fluid in the injection direction ED-7 at an angle to the flow direction FD of the flow path 500, the angle of inclination A-7 being approximately -15°, for example. In the embodiment shown in FIG. 8, a nozzle 135-8 is located at the end of the trailing edge and injects the flushing liquid in the injection direction ED-8, at an angle to the flow direction FD of the flow path 500, the angle of inclination A-8 being approximately +15°, for example.

[0044] The nozzles 135-6, 135-7, 135-8 inject the washing liquid so that it reaches the blades 260; in particular, injection from a single nozzle only reaches one vane at a time (or a limited number of vanes at a time, such as two or three or four). According to these embodiments, the nozzles 135-6, 135-7, 135-8 inject the washing liquid so that it reaches both the pressure side and the suction side of the vanes 260; in FIG. 6, the flushing liquid reaches the section from V to P1-6 of the suction side, as well as the section from V to P2-6 of the discharge side; in FIG. 7, the flushing liquid reaches the section from V to P1-7 (that is, the whole) of the suction side, and the (small) section from V to P2-7 of the discharge side; in FIG. 8, the flushing liquid reaches a (small) section from V to P1-8 of the suction side, as well as a section from V to P2-8 of the (entire) pressure side. Generally, the amount of flushing liquid reaching the pressure side may be equal to or different from the amount of flushing liquid reaching the suction side.

[0045] It is apparent from the above description that the cleaning methods described herein provide for washing the blades and/or vanes of a turbomachine by injecting a washing liquid from at least one stator aerodynamic component located in the turbomachine working fluid flow path; in particular, the flushing liquid is injected from one or more nozzles of at least one stator aerodynamic component. The blades may be first stage turbomachine blades and/or intermediate turbomachine stage blades and/or last turbomachine stage blades. The blades may be the blades of the first set of turbomachine blades and/or the blades of the intermediate set of turbomachine blades and/or the blades of the last set of turbomachine blades.

[0046] The stator aerodynamic components described herein can be used to inject a flushing fluid, such as water, in particular demineralized water, and possibly detergent. The composition of the washing liquid may depend on the period (eg, operating or non-operating mode) and/or the location of the cleaning. However, the stator aerodynamic components described herein can be used to inject other fluids used for specific turbomachine applications.

[0047] The cleaning method described herein can be performed on-line and/or offline. In other words, the nozzles in the aerodynamic components of the stator can be activated when the turbomachine is running or not running (but rotating), as well as in operation and in idle mode.

[0048] The washing liquid may be injected, for example, continuously or intermittently.

[0049] During the cleaning described herein, when washing the blades and/or blades, at least one parameter can be set or adjusted. Such a parameter may be, for example, washing liquid temperature, washing liquid pressure, washing liquid composition, washing liquid injection rate, washing liquid injection direction.

[0050]In Fig. 9 and Fig. ten shows embodiments of the aerodynamic component of the stator, in particular the strut, of the turbomachine shown in FIG. 1, with the fluid connection between the nozzle and the pipeline corresponding to exceptional cases.

[0051] In FIG. 9, conduit 134-9 is in direct fluid communication with nozzle 135-9 injecting flushing fluid in direction ED-9; in other words, the connection channel has a length equal to zero (i.e., there is no connection channel); moreover, the pipeline has approximately the same cross-sectional area as the aerodynamic component of the stator.

[0052] In FIG. 10, conduit 134 is fluidly connected to at least two nozzles 135-10 injecting flushing liquid in the direction of ED-10 through a long channel 136-10, which in particular is branched (the first branch is connected to the first nozzle 135-10, and the second branch is connected to the second nozzle 135-10); nozzles 135-10 are respectively located on struts 139 which may protrude from the airfoil of the stator aerodynamic component (the first branch is located inside relative to the first strut and the second branch is located inside relative to the second strut) and which may have an aerodynamic cross section, for example, less than the cross section component (as shown, for example, in Fig. 10). The struts 139 may be movable (eg, they may rotate and/or move) so that they may be positioned internally relative to the aerodynamic component of the stator when not being used for fluid injection. The advantage is that this movement can be caused by the pressure of the injected fluid, for example, when the pressure rises, the pressure column extends from the component and fluid is injected, and when the pressure decreases, the column retracts into the component and fluid injection stops.

[0053]In Fig. eleven shows a block diagram 1100 of an embodiment of the cleaning method. This cleaning method includes the following steps: step 1102: washing the blades and/or blades of the turbomachine by injecting a washing liquid from at least one aerodynamic component of the stator located in the flow path of the working fluid of the turbomachine, and

- step 1104: setting or adjusting at least one parameter when washing the blades and/or blades.

At least one parameter is selected from the group consisting of flushing fluid temperature, flushing fluid pressure, flushing fluid composition, flushing fluid injection rate, flushing fluid injection direction. It should be noted that these two steps may be performed in any suitable order and/or repeated one or more times, although FIG. 11 shows only one step 1102 and only one step 1104, with step 1102 preceding step 1104.

[0054] It should be noted that, in accordance with the embodiments just described and shown, the stator aerodynamic component is a component that is already part of an existing turbomachine. However, in accordance with other embodiments, the turbomachine may include stator aerodynamic components specially designed and installed within the flushing flow path. In this case, the (longitudinal and/or transverse) size of one or more components may be small and/or the shape of one or more components may be such as to provide a low pressure drop, and/or the location and/or orientation of one or more components may be such as to ensure proper rinsing.

Claims (21)

1. Aerodynamic component (130, 230, 250) of the stator for location in the path (500) of the flow of the working fluid of the turbomachine (1000), and the aerodynamic component (130, 230, 250) of the stator contains: - a pipeline (134, 254) configured to receive liquid from the tube (120, 220), and - one or more nozzles (135, 255) connected (136, 256) in a fluid medium with the specified pipeline (134, 254) and configured to inject liquid into the specified flow path (500); while the aerodynamic component (130, 230, 250) of the stator additionally contains a removable part (137-2, 137-3, 137-4), and while these one or more nozzles (135-2, 135-3, 135-4 ) are located in the specified removable part (137-2, 137-3, 137-4). 2. The aerodynamic component (130, 230, 250) of the stator according to claim 1, wherein the component (130) has a leading edge region (131) and a trailing edge region (132), and said one or more nozzles (135-2, 135-3, 135-4) are located in the region (132) of the trailing edge. 3. The aerodynamic component (130, 230, 250) of the stator according to claim 1, wherein the component (130) has a region (131) of the leading edge and a region (132) of the trailing edge, and the specified pipeline (134) is located in the region (131 ) of the leading edge. 4. Aerodynamic component (130, 230, 250) of the stator according to claim 1, in which at least one of these nozzles (135-2) is configured to inject liquid in the injection direction (ED-2) corresponding to the direction (FD) stream of the specified path (500) stream. 5. Aerodynamic component (130, 230, 250) of the stator according to claim 1, in which at least one of these nozzles (135-3, 135-4) is configured to inject liquid in the direction (ED-3, ED-4 ) injection, located at an angle to the direction (FD) flow of the specified path (500) flow. 6. Aerodynamic component (130, 230, 250) of the stator according to claim 5, wherein said injection direction (ED-4) is located at an angle of +5° to +90°, or said injection direction (ED-5) is located at an angle from -5° to -90°. 7. Aerodynamic component (130, 230, 250) of the stator according to claim 1, in which said nozzles are configured to inject liquid in different directions. 8. The aerodynamic component (130, 230, 250) of the stator according to claim 1, wherein said one or more nozzles (135-6, 135-7, 135-8) are configured to inject liquid so that it reaches one or more blades (260) and/or one or more turbomachine blades (1000). 9. Aerodynamic component (130, 230, 250) of the stator according to claim 1, wherein said one or more nozzles (135-6, 135-7, 135-8) are configured to inject liquid so that it reaches the side (V P 1-6, V-P1-7, V-P1-8) suction and side (V-P2-6, V-P2-7, V-P2-8) of one or more blades (260) and/or one or more blades of the turbomachine (1000), wherein the amount of liquid reaching the pressure side is equal to or different from the amount of liquid reaching the suction side. 10. Aerodynamic component (130, 230, 250) of the stator according to claim 1, in which said pipelines are located in said removable part (137-2, 137-3, 137-4). 11. Turbomachine (1000), containing at least one aerodynamic component (130, 230, 250) of the stator, located in the path (500) of the working fluid flow of the turbomachine (1000); and at least one aerodynamic component (130, 230, 250) of the stator contains: - a pipeline (134, 254) configured to receive liquid from the tube (120, 220), and - one or more nozzles (135, 255) connected (136, 256) in a fluid medium with the specified pipeline (134, 254) and configured to inject liquid into the specified flow path (500); while the aerodynamic component of the stator additionally contains a removable part (137-2, 137-3, 137-4), and wherein said one or more nozzles (135-2, 135-3, 135-4) are located in said removable part (137-2, 137-3, 137-4). 12. The turbomachine (1000) according to claim 11, further comprising at least one nozzle (137, 138), wherein said nozzle is configured to inject liquid into the path (500) of the working fluid flow and is located on the wall limiting the specified path ( 500) flow in the socket (100) of the turbomachine (1000). 13. The turbomachine according to claim 11, further comprising at least one nozzle, wherein the specified nozzle is configured to inject liquid into the working fluid flow path (500) and is located on the wall delimiting the specified flow path (500), between the first stage ( 240) and the last stage (260) of the turbomachine (1000).

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