DE10390644B4 - Turbo compressor and method of operating a turbocompressor - Google Patents

Abstract

A turbocompressor comprising a device (8, 9) for introducing a liquid medium (81, 91) for cooling the working fluid flow of the turbocompressor by evaporation and / or heat transfer to the liquid phase during at least part of the compression process, characterized in that 1, 4, 5, 10, 50, 51, 52, 53, 54, 55, 56, 57) of the compressor and the compressor inflow channel (2), means (100, 101, 102, 103, 106, 107, 110, 111, 112, 113, 114, 115, 116, 503) for skimming two-phase boundary layers, the means for skimming two-phase boundary layers communicate with means for deriving the skimmed two-phase boundary layers, and at least part of the means for deriving the two-phase boundary layers with a barrier air system or a cooling air system (40) of a gas turbine in fluid communication.

Description

Technical area

The present invention relates to a turbocompressor according to the preamble of claim 1.

State of the art

It is well known that injecting a liquid upstream of a compressor or in a compressor by evaporating the liquid results in intense internal cooling of the compressor and thus in a reduction in the power consumption of the compressor at a constant mass flow and pressure ratio. A suitable device gives the US 4,478,553 A on. From the FR 1 563 749 A It is known that this also improves the performance of a gas turbine. FR 1 563 749 A emphasizes the relevance of good atomization of the liquid. The US 6 216 443 B1 and the WO 99/67519 A1 have proposed arrangements that produce sufficiently small drops, with diameters below 50 μ. However, it must be expected that moisture deposits on blades, channel walls, and other internals arranged in the flow channel, where they form large drops or water films. Such shear stress-driven liquid films and two-phase boundary layers have a number of negative effects. Liquid films, which are particularly able to form on compressor blades, potentially adversely affect the aerodynamics of the slim blade profiles excessively negatively, with corresponding effects on the component efficiency and the operational and in particular detachment behavior. From the EP 0444913 A1 a device for introducing a liquid medium for cooling the working fluid flow of a turbocompressor is known. Next discloses the EP 0444913 A 1 a heat exchanger for cooling the working medium flow and a drainage for the discharge of condensate.
The DE 20 38 047 A discloses a steam turbine having drainage openings on vanes and in the housing.
From the JP 11-173 162 A is a gas turbine with a drainage in the intake known.
From the FR 2 088 680 A5 For example, a turbine separator is known in which a liquid is separated from a two-phase flow.
From the DE 101 34 612 A1 is a gas turbine plant known with at least one intake air compressing compressor. In order to limit the temperature of the intake air at the end of the compression, it is intended to inject water or another fluid into the intake air.

Presentation of the invention

It is an object of the present invention to provide a turbocompressor which has a device for introducing a liquid medium for evaporative cooling of the working medium flow while avoiding the stated disadvantages of the prior art. According to the invention this object is achieved by using the entirety of the features of claim 1.

The essence of the invention is therefore to provide means by which the potentially forming two-phase boundary layer can be skimmed off from the surface of the components of the compressor. The term of the two-phase boundary layer is to be understood in the broadest sense, such that both drops and gas flow occur side by side, as well as for a closed liquid film with a gas flow flowing over it.

A location at which these means for skimming the two-phase flow are to be arranged particularly advantageously is in the downstream third in the vicinity of the trailing edge or directly at the trailing edge of compressor guide vanes or a downstream end of other in a compressor channel associated flow channel protruding internals, such as in the intake passage the compressor arranged support and stiffening elements. Such means are in particular holes, slots, or other openings through which the two-phase boundary layer can flow. Furthermore, porous elements, for example of ceramic, can also be used here. The skimming agents may also be such that capillary forces are used to separate the liquid and gas phases. Furthermore, means for skimming the two-phase boundary layer are advantageously also arranged on the walls of the flow channel for the working medium, wherein here also the arrangement in a wall of an upstream of the compressor arranged inlet channel is to be subsumed. It is also interesting an arrangement on the wall of the compressor, in the immediate area of a compressor barrel row, in particular immediately downstream of the barrel or the Leitreihe. Liquid, which is deposited on the blades and is thrown by them against the wall, is thus skimmed off before it can be detrimental. The means by which the two-phase boundary layer is skimmed off are preferably associated with further means for removing the skimmed off fluid, basically a drainage system. Preferably, in this drainage system, at least in a part of the means for removing the skimmed boundary layer, water separator. If the skimmed medium, in particular a water-air mixture is separated in this way, the Gas phase, generally air, readily be used as cooling air or sealing air. In this way, film and biphase boundary layer skimming can be implemented very efficiently, particularly in compressor stages of already elevated pressure levels: connection with a lower pressure system readily provides the vacuum required or necessary for skimming; the skimmed medium covers at least part of the cooling or purging air requirement at an appropriate pressure level. For example, separated water can be returned to the circulation. The conditions are somewhat different if, as a skimming agent, porous elements are used which are already capable of phase separation by capillary forces.

Advantageously built vanes are used in conjunction with the extraction on compressor vanes. The airfoils consist, for example, of a suction-side and a pressure-side segment, which essentially have the shape of an airfoil divided along the skeleton line. Channels are incorporated into the segments at the parting surfaces, which form inner drainage channels of the blades after assembly. This makes it possible to arrange the drainage channels necessary for the realization of the invention comparatively easily in the slender compressor blade profiles. The comparatively low temperature load and lack of centrifugal loading of the compressor vanes allows the use of such assembled, suitable means of soldering, welding, adhesive, or other suitable joining technique assembled blades easily. Such a design also makes it particularly easy to use porous, such as ceramic, elements for the removal of the boundary layers.

list of figures

• - 1 einen Längsschnitt durch einen erfindungsgemässen Verdichter;
• - 2 einen Erfindungsgemässen Verdichter im Zusammenhang einer Gasturbine;
• - 3 gebaute Verdichterleitschaufeln;
• - 4 verschiedene Ausführungsformen von im Ansaugkanal anzuordnenden Ablaufrinnen;
• - 5 ein Beispiel für eine Steuerung der Grenzschichtabschöpfung eines erfindungsgemässen Verdichters;
• - 6 ein weiteres Beispiel für eine Steuerung der Grenzschichtabschöpfung eines erfindungsgemässen Verdichters.

The invention will be explained in more detail with reference to embodiments shown in the drawing. Show in detail

• - 1 a longitudinal section through a compressor according to the invention;
• - 2 a compressor according to the invention in the context of a gas turbine;
• - 3 built compressor vanes;
• - 4 various embodiments of gutters to be arranged in the intake duct;
• - 5 an example of a control of the boundary layer levy of a compressor according to the invention;
• - 6 Another example of a control of the boundary layer levy of a compressor according to the invention.

The drawing is greatly schematized in the interest of clarity, and should be understood to be instructive only.

Way to carry out the invention

In 1 is shown a turbo compressor of a gas turbine group including inlet channel. It is tacitly assumed that it is an air-breathing compressor, without thereby restricting the generality of the following statements for other in particular gaseous media. The canal walls 1 define an inflow channel 2 through which air to the actual compressor inlet 3 and from there into the compressor flows. The compressor inlet 3 has the shape of a lying bell with attached inflow channel 2 , Downstream of the compressor inlet 3 the configuration shown in the components essential to the invention is substantially rotationally symmetrical, which is why only one half is shown. In the compressor inlet are support and stiffening elements 4 arranged, which ensure the structural rigidity of the housing. In the further course of the flow path are on a rotor 7 fixed blades 61 - 67 and in the compressor housing 10 fixed vanes 51 - 57 arranged alternately, and form the compressor stages, wherein the number of illustrated compressor stages for a real turbocompressor of a gas turbine is by no means representative: The compressors of stationary power plant gas groups usually have 13 to 17 axial compressor stages, wherein the specified range is by no means exhaustive. For the sake of clarity of presentation, however, the restriction has been made which does not limit the generality of the representation with reference to the details essential to the invention. Upstream through the blade row 61 and the vane row 51 formed first compressor stages is a Vorleitreihe 50 arranged; downstream of the last compressor stage, an outlet diffuser 11 ; its task is, on the one hand to further delay the compressor outflow and so build up further pressure, and on the other hand, the flow as possible loss-free in a 1 Not shown combustion chamber - or another consumer - to lead. The blades of the preliminary row 50 and the first two rows of vanes are designed as adjustable blades and by means of journals 12 in the case 10 stored. In the inflow channel 2 is a device provided with spray nozzles 8th arranged. A additional spraying device 9 is arranged between two compressor stages The sprayers 8th . 9 can be arranged completely independently of each other, that is, the presence of a spray device does not require the presence of others. About the sprayers 8th . 9 becomes a liquid, preferably water or a water-based mixture, in the form of sprays 81 . 91 Added to the flow The liquid, on the one hand, cools the air immediately downstream of the injection position by evaporation and by the absorption of sensible heat; At the same time, the amount of water is dimensioned such that drops also flow into the downstream compressor stages. These absorb heat during compression of the air and evaporate successively, providing intensive internal cooling of the compressor. The over-humidification of the compressor intake air of a compressor is also referred to as "Overfogging", "High Fogging" or "Wet Compression". Ideally, the temperature profile within the compressor corresponds to the course of the boiling temperature of the liquid, or the cooling limit temperature, at the respective pressure in one stage. The increase in the gas temperature is significantly limited; the gas temperature at the compressor outlet, corresponding to the final pressure associated boiling point of water, is at compression from ambient pressure to a final pressure of 15 bar slightly less than 200 ° C, at a final pressure of 30 bar about 234 ° C. For comparison, these values are about 351 ° C and 488 ° C respectively for isentropper compaction and an inlet temperature of 15 ° C. It is therefore - also a bit imprecise - this process also referred to as "quasi-isothermal compression". The importance of good atomization of the liquid has been set out in the introduction. Nevertheless, the possibility can not be ruled out that liquid films are deposited on compressor components. Adverse effects potentially resulting therefrom are the influence on the aerodynamics of the slender compressor blade profiles, as well as an increased degree of occlusion, and an increased separation sensitivity of the flow due to the thickened boundary layer. Upstream of the compressor stages on the walls of the intake duct 2 and the compressor inlet 3 , as well as on the supporting and stiffening elements 4 attached liquid films harbor the possibility of forming strands of liquid and large droplets which, in turn, tend to become more concentrated downstream. A first potential accumulation of liquid may occur on the walls of the suction channel when liquid from the spray device 8th directly on the walls 1 arrives. In the vertical part of the intake duct 2 The compressor shown as an example are therefore actual gutters 116 arranged, which accumulate the accumulated liquid and direct to a suitable extraction point. A next point where liquid accumulation is especially to be expected is the radially inner wall of a flow deflection from the intake channel 2 in the compressor inlet 3 , Due to the prevailing there low flow velocity and the low pressure and there is potentially forming Totwassergebietes conditions are present, which are beneficial to the attachment of liquid to the wall. According to the invention therefore means at the mentioned point 110 arranged over which skimming liquid and two-phase boundary layers skimmed off and, indicated by an arrow, are derived. Among other things, these means are arranged distributed transversely to the main flow direction, in this case perpendicular to the illustrated sectional plane, which is why only one of the means 110 is shown. On in the working fluid flow projecting support and stiffening elements 4 are, preferably on the downstream side, rows of means 114 arranged to skim the liquid film or the two-phase boundary layer. Further levy funds 115 are arranged near the hub on the shaft cover. Likewise, are rows of means 100 . 101 . 102 . 103 , 106, 107 for skimming two phase boundary layers at the trailing edges of the pilot row blades 50 and the blades of a few pilot lines 51 . 52 . 53 . 56 . 57 arranged. The skimmed medium is via corresponding lines from the housing 10 led out of the compressor. For the illustrated compressor are the Vorleitreihe 50 as well as the Leitreihen 51 . 52 the first two compressor stage made adjustable. Here is the removal of the skimmed medium expediently by hollowed storage elements 12 , In the compressor stages immediately downstream of an injection device must also be expected with an accumulation of liquid on the walls of the flow channel. This is to be expected to a greater extent in the area of compressor blades: There, water droplets are centrifuged on the one hand with the flow lines to the wall, on the other hand, the blades potentially hurls drops of water on the wall. Therefore, on the wall 10 , preferably in the axial region of the blade trailing edges or slightly downstream therefrom, circumferential rows of means 111 . 112 arranged over which two-phase boundary layers can be skimmed off. The means are, for example, rows of bores, which are either arranged substantially along the downstream edge of components projecting into the flow channel or distributed on the circumference of the outer walls of the flow channel for the working medium substantially at an axial position, and which are provided with corresponding means for the removal of the skimmed medium, such as a drainage system, in connection. If, as in the example shown, a water injection device 9 in the back of the compressor is arranged, the compressor stages downstream of it are meaningful means in an analogous manner 106 . 107 . 113 provided for film and two-phase boundary layer skimming. The advantageous effects of the invention are manifold: on the one hand, liquid films, from which large drops of water and strands can be introduced into the flow, are avoided. The thickening of the boundary layers by liquid films, which could adversely affect the efficiency of the compressor by an enlarged obstruction and effects on the aerodynamics of the slim blade profiles, is avoided; conversely, a general boundary layer reduction can bring about very advantageous consequences, including a reduced tendency for the compressor flow to dissipate. When a turbocompressor is operated with cooling, the pressure build-up shifts into the rear compressor stages, which increases the risk of separation on heavily loaded blading; In this context, the application of the invention in the rear compressor stages can make sense even if here no or only small amounts of liquid are expected, since the resulting reduction of the boundary layer reduces the risk of separation. The means 113 are strictly speaking already downstream of the actual compressor, arranged in the diffuser, at the periphery of the flow channel. In addition to the pure effect of liquid extraction, the risk of separation in the diffuser 11 reduces, and the illustrated radially outwardly directed flow deflection, for example, in a plenum of a Ringbrennkamer is effectively supported.

2 shows the invention in connection with a possible embodiment of the means for removing the extracted medium, the turbo-compressor is part of a gas turbine group shown schematically. In a few words, compresses the compressor 21 Air to a working pressure, and promotes this in an example annular combustion chamber 22 , There, fuel is burned in the compressed air. The hot flue gas gets into the turbine 23 while delivering a wave power to the shaft 7 relaxed. The described process control can be modified in various ways, for example by two turbines being arranged in series, between which one, further combustion chamber is arranged, or series-connected partial compressors with coolers interposed therebetween can be implemented. Also, instead of a combustion chamber, a heat exchanger could be arranged in which the working fluid is heated, and the process could be closed and operate with helium instead of air as working fluid, and the like, but without affecting the essence of the invention. The shaft is at a compressor end in a combined radial thrust bearing 71 stored; Turbine side is a floating bearing 72 arranged with free axial mobility of the shaft. The wave 7 is led out at the end faces of the housing of the gas turbine group; In these places are non-contact seals, such as labyrinth seals 24 . 25 arranged. As in 1 is shown in more detail in the intake 2 a first spraying device 8th arranged, and a second spray device 9 is, in the figure only hinted, in the rear part of the compressor 21 arranged. The skimmers 100 . 101 . 102 . 103 . 106 . 107 . 110 . 111 . 112 . 113 . 114 are indicated only by their position on the compressor, the representation is by no means to the scale, but only schematically shows the relative positions of the various skimming and injectors. The different levels of pressure applied to the film stripping means and the resulting different uses of the scavenged medium make it desirable to implement different drainage systems for different pressure levels. So the pressure is at least at the skimming points 110 . 114 , and 100 due to the flow velocity under the ambient pressure. Although pressure is built up in the first compressor stages, in the case of a strongly closed series of precursors, a pressure below ambient pressure or only slightly above can readily exist there as well. According to the present exemplary embodiment, therefore, the skimming points located upstream of the compressor and those of the first two compressor stages are connected to a vacuum drainage system. The skimming points 101 . 102 stand with the motive nozzles of ejectors operating on the principle of jet pumping and cascading 31 . 32 in conjunction, so that the skimmed off fluid acts as a driving medium in the ejectors. These ejectors convey medium from the upstream upstream skimmers lower form. The ejector 32 the highest pressure is downstream of the top of a container with downpipe 33 connected, which in the figure through the fluid interface A is shown. In the container with downpipe 33 a liquid column of height h is maintained, which communicates with the atmosphere at the lower end. In the upper part of the container thus creates a corresponding to the height of the liquid column negative pressure to the atmosphere. The drain from the downpipe can be controlled by an actuator 34 be varied; a complete closure of this actuator switches off the film suction. The height of the liquid column can via the actuator 34 and via an additional fluid supply 35 be regulated, the suction effect on the height of the liquid column is variable. The outflowing liquid is advantageously returned to a treatment and returned to the process. Of course, a suction fan can be used instead of the "hanging liquid column". At the point 103 Skimmed fluid is already at an elevated pressure level under all circumstances, which is compatible, for example, with the pressure of a blocking air system. The scavenged fluid therefore becomes a mist eliminator 36 The air scavenged with the two-phase boundary layer therefore becomes as through the fluid interface B indicated as blocking air to the labyrinth seals 24 . 25 guided. At the skimming points 106 . 107 , and 113 is already reached a fairly high pressure; These are associated with a high pressure drainage system. In the example shown, this again contains two cascading ejectors 37 and 38 to which the skimming points are connected according to the prevailing pressure conditions as a propellant or conveying fluid supply line. The skimmed fluid is passed through a mist eliminator 39 into a pressure-compatible medium or low pressure cooling system or cooling line 40 out. In a gas turbine with sequential combustion, as for example from the EP 620 362 has become known, this is for example the cooling system of the second turbine. Of course, in the illustrated drainage systems also not shown here concluding means for adjusting the skimmed mass flow must be provided either to a fixed or a variable value. In the example, the means for removing the skimmed medium in the high pressure system by an actuator 41 variably designed.

This actuator is dependent on the measurement signal of a flow measuring point 42 for the sprayer 9 supplied liquid mass flow controlled.

It goes without saying that that in conjunction with the 1 and 2 illustrated example does not represent a conclusive representation of the invention characterized in the claims, but only one among many ways to realize the invention. The arrangement of the means for skimming two-phase boundary layers within the scope of the invention characterized in the claims must be selected according to the specific circumstances, with parameters such as the "depth of penetration" of water droplets in the compressor downstream of a spray device or aerodynamic conditions, which Either promote or counteract liquid films are to be considered. The arrangement of the means for removing the skimmed boundary layers and the interconnection with the Abschöpfungsmitteln can in the context of marked in the claims invention clearly from the in 2 differ from the example shown. The application of the invention is further by no means limited to compressors of gas turbines.

The vanes to be provided with skimming means may, for example, be provided in the manner known from the manufacture of cooled turbine blades with suction holes and internal drainage channels which connect the suction holes to a drainage system. Especially with compressor blades with very slim profiles, however, these production methods can prove to be very complicated due to the necessary high manufacturing accuracy. Here comes the designer - comparatively! - Low thermal load and the absence of centrifugal load on vanes very contrary. This allows the use of in 3 illustrated built vanes 5 , which by means of suitable joining method of a plurality of vane elements, in particular a pressure-side vane element 501 and a suction-side vane member 502 to be put together. This production variant saves the time-consuming production of components to be machined channels. In an in 3a illustrated embodiment, the guide vane 5 from two bowls 501 and 502 assembled, and along a seam 505 by a suitable joining method, such as welding, soldering, gluing, and so on, which is also determined by the materials used, connected. Into one of the shells are suction openings 503 brought in; the entire blade interior is hollow and acts as a scoop-in drainage channel 504 , In extreme cases, there are the blade elements 501 and 502 made of pressed into the appropriate shape sheets, wherein in the element 501 the openings were simply stamped and deburred; the halves will then be along the seam 505 bonded. This example illustrates the impressively simple possible production of a built-up guide vane with a device for boundary layer extraction. 3b further shows the possible design of a built-up blade 5 as a solid profile. The scoop elements 501 and 503 are cast, for example, and along a joint 505 connected together in a suitable and known manner. The suction holes 503 and the inner drainage channel 504 are in the illustrated blade only in a blade element 501 incorporated, so that the second blade element must not be subjected to a processing step aligned thereto, whereby the production is again simplified. Although 3 shows only constructed blades with suction side arranged on the suction side, the above statements to the skilled person immediately also built blades with suction or two-sided suction or other means for skimming two-phase boundary layers. It remains to be noted that this flow can of course be operated in the reverse direction, by passing over the channel 504 Liquid is supplied; the openings 503 are then as spray nozzles - for example, by screwing nozzles into the openings - and the corresponding row of blades then acts as a spray device.

4 shows - of course not conclusive - different forms of gutters 116 as they are used as a sweetener in the intake 2 can be arranged. In 4a is a simplest form shown. A gutter 116 is here in the manner of a Dachkandel suitable manner on a wall 1 of the flow channel 2 attached, for example screwed. On the one hand, this embodiment is particularly easy to retrofit to existing plants, on the other hand, the burden of aerodynamic forces and the disturbance of the flow must be considered. These disadvantages have the in the 4b and 4c illustrated embodiments, whereas these comparatively expensive in the channel wall 1 must be incorporated, and thus less suitable for retrofitting existing installations.

In connection with 2 the setting of the skimmed fluid depending on an introduced amount of water was shown. The 5 and 6 not conclusively show further possibilities to control the fluid exhaustion. In 5 is one out on a wave 7 arranged blades 6 and in the case 5 attached vanes 5 existing compressor stage shown. The vanes 5 are with means 503 for the removal of two-phase boundary layers provided, in turn, by means 44 for the removal of the skimmed fluid in connection. In conjunction with the means 44 is an actuator 45 arranged over which the amount of the discharged fluid is adjustable. On the vane 5 is a humidity sensor 43 arranged; the actuator 45 is opened with increasing measured humidity. In 6 is shown an identical compressor stage, wherein the actuator 45 is controlled depending on another parameter. It has been indicated above that a decreasing boundary layer thickness is able to reduce the tendency to detach aerodynamically highly loaded blade profiles. It was further indicated that generally when using cooling in a compressor, the pressure build-up shifts into the rear compressor stages, that is, the load on the rear compressor stages then increases further. This was in the in 6 illustrated circuit taken into account. A first pressure measuring point measures the pressure p1 before the compressor stage. A second pressure measuring point measures the pressure p2 after the compressor stage. A computing and control unit 46 forms a difference of pressures. Depending on the pressure build-up p2 - p1 Via the compressor stage, the actuator is opened with increasing pressure build-up and thus greater risk of separation. As a result of the resulting skimmed-off fluid quantity, the wall-near flow on the blade 5 accelerates, and the boundary layer thickness, thus the Ablöseabigung, decreases. It may prove advantageous in this context, Abschöpfungsmittel 503 In a downstream, close to the trailing edge, to arrange located region of the suction side, since there are the largest pressure gradients. On the other hand, if the main objective is to suction liquid films to reduce drop breakage, the arrangement on the pressure side of the profiles will be preferable in a downstream region near the trailing edge, for example in the last third of the profile length of the pressure side. Since the described measure to reduce the tendency to detachment acts in the compressor nozzle, it will also be advantageous to shift the pressure build-up of the illustrated axial compressor stage in the Leitreihe; It is then selected a degree of reaction which is less than 0.5, and for example in the range between 0.3 and 0.45, in particular 0.35 to 0.4, is located.

Although the invention is explained above with reference to an axial compressor, the person skilled in the art will readily be able to transfer the teachings of the invention to radial or semi-axial machines.

LIST OF REFERENCE NUMBERS

1

channel walls

2

Intake channel, inflow channel

3

compressor inlet

4

Supporting and stiffening elements

5.

compressor stator

7

Rotor, shaft

8th

sprayer

9

sprayer

10

compressor housing

11

outlet diffuser

12

Bearing journal, bearing element

21

compressor

22

combustion chamber

23

turbine

24

labyrinth seal

25

labyrinth seal

31

Jet pump, ejector

32

Jet pump, ejector

33

Container with downpipe

34

Throttling and shut-off device

35

water supply

36

Droplet

37

Jet pump, ejector

38

Jet pump, ejector

39

Droplet

40

Low and medium pressure cooling system, pipe

41

actuator

42

Flow measuring point for inflow to the spray device 9

43

Means for removing skimmed fluid

44

actuator

45

Computing unit, control unit

50

Leading row, leading row scoop

51, 52, 53, 54, 55, 56, 57

Leitreihen, vanes

61, 62, 63, 64, 65, 66, 67

Run rows, blades

71

warehouse

72

warehouse

81

spray

91

spray

100, 101, 102, 103, 106, 107, 110, 111, 112, 113, 114, 115, 116

Means for skimming two-phase boundary layers, liquid films

501

Guide vane

502

Guide vane

503

Skimming agent, drainage opening, suction opening

504

drainage channel

505

Joint, seam

Claims (10)

A turbocompressor comprising a device (8, 9) for introducing a liquid medium (81, 91) for cooling the working fluid flow of the turbocompressor by evaporation and / or heat transfer to the liquid phase during at least part of the compression process, characterized in that 1, 4, 5, 10, 50, 51, 52, 53, 54, 55, 56, 57) of the compressor and the compressor inflow channel (2), means (100, 101, 102, 103, 106, 107, 110, 111, 112, 113, 114, 115, 116, 503) for skimming two-phase boundary layers, the means for skimming two-phase boundary layers communicate with means for deriving the skimmed two-phase boundary layers, and at least part of the means for deriving the two-phase boundary layers with a barrier air system or a cooling air system (40) of a gas turbine in fluid communication. Turbo compressor after Claim 1 characterized in that the means in the downstream third, in particular at or in the vicinity of the blade trailing edges of vanes (5; 50, 51, 52, 53, 54, 55, 56, 57), or on the downstream side of in a flow channel for the working medium flow of the compressor protruding internals (4) are arranged. Turbo compressor after Claim 2 , characterized in that the means for skimming are arranged in the downstream third of vanes on the pressure side. Turbo compressor according to one of the preceding claims, characterized in that means (111, 112, 113) for skimming two-phase boundary layers are arranged on walls (10) of a flow channel for the working medium flow of the compressor. Turbo compressor according to one of the preceding claims, characterized in that means (110) for skimming two-phase boundary layers are arranged on a wall (1) of an inflow channel (2) arranged upstream of the compressor. Turbo compressor after Claim 1 , characterized in that at least part of the means for discharging the two-phase boundary layers is provided with water separators. Turbo compressor after Claim 4 , characterized in that the means (111, 112, 113) for skimming the two-phase boundary layer are arranged immediately downstream of the position of a compressor run row. Turbo compressor after one of Claims 2 or 3 , characterized in that the compressor guide vanes (5) are constructed of at least two parts (501, 502). Use of a turbocompressor according to one of the preceding claims as a compressor of a gas turbine group. Method for operating a turbocompressor according to one of Claims 1 to 8th in which a liquid is injected upstream of a first compressor stage and / or inside the compressor, wherein the amount of injected liquid is such that non-vaporized liquid is embedded in the fluid to be compressed at least in a compressor stage located downstream of the injection site, characterized in that a two-phase boundary layer accumulating on walls of the flow path of the turbocompressor and / or on components (4, 50, 50, 51, 52, 53, 56, 57) projecting into the flow path is skimmed off.

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