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WO2003071113A1 - Turbocompresseur et procede pour faire fonctionner un tel turbocompresseur - Google Patents

Turbocompresseur et procede pour faire fonctionner un tel turbocompresseur Download PDF

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Publication number
WO2003071113A1
WO2003071113A1 PCT/IB2003/000305 IB0300305W WO03071113A1 WO 2003071113 A1 WO2003071113 A1 WO 2003071113A1 IB 0300305 W IB0300305 W IB 0300305W WO 03071113 A1 WO03071113 A1 WO 03071113A1
Authority
WO
WIPO (PCT)
Prior art keywords
compressor
skimming
liquid
phase boundary
flow
Prior art date
Application number
PCT/IB2003/000305
Other languages
German (de)
English (en)
Inventor
Hans Wettstein
Jürgen Hoffmann
Original Assignee
Alstom Technology Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Alstom Technology Ltd filed Critical Alstom Technology Ltd
Priority to AU2003205939A priority Critical patent/AU2003205939A1/en
Priority to DE10390644.4T priority patent/DE10390644B4/de
Publication of WO2003071113A1 publication Critical patent/WO2003071113A1/fr

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps
    • F04D29/5846—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps cooling by injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • F02C7/1435—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages by water injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
    • F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
    • F04D29/706—Humidity separation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/212—Heat transfer, e.g. cooling by water injection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/602—Drainage

Definitions

  • the present invention relates to a turbocompressor according to the preamble 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 the surface of the components of the compressor.
  • the term two-phase boundary layer is to be understood in the broadest sense in such a way 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 place where these means for skimming off the two-phase flow are to be arranged particularly advantageously is in the downstream third near the rear edge or directly at the rear edge of compressor guide vanes or a downstream end of other internals projecting into a flow channel assigned to the compressor, such as in the intake duct of the compressor arranged support and stiffening elements.
  • Such means are in particular bores, slots, or other openings through which the two-phase boundary layer can flow.
  • porous elements for example made of ceramic, can also be used here.
  • the skimming means can also be such that capillary forces are used to separate the liquid and gas phases.
  • means for skimming the two-phase boundary layer are advantageously also arranged on the walls of the flow channel for the working medium, the arrangement in a wall of an inlet channel arranged upstream of the compressor also having to be subsumed here.
  • An arrangement on the wall of the compressor, in the immediate area of one, is also interesting
  • Compressor run row in particular immediately downstream of the run or the lead row. Liquid that is deposited on the blades and thrown against the wall by them is skimmed off before it can be harmful.
  • the means by which the two-phase boundary layer is skimmed off are preferably connected to further means for removing the skimmed-off fluid, basically a drainage system. Water separators are preferably located in this drainage system, at least in part of the means for removing the skimmed boundary layer. If the skimmed-off medium, in particular a water-air mixture, is separated in this way, the gas phase, generally air, can readily be used as cooling air or sealing air.
  • the film and two-phase boundary layer skimming can be implemented very efficiently, particularly in compression stages of an already increased pressure level: a connection to a system of lower pressure readily provides the vacuum required or necessary for the skimming; the skimmed medium covers at least part of the cooling or sealing air requirements at an appropriate pressure level. Separated water can be returned to the cycle, for example.
  • the situation is somewhat different if porous elements are used as skimming agents, which are already capable of phase separation by capillary forces.
  • advantageously built blades are used.
  • 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 worked into the segments at the dividing surfaces, which form inner drainage channels of the blades after assembly. This makes it possible to arrange the drainage channels necessary for the implementation of the invention comparatively simply in the slim compressor blade profiles.
  • Centrifugal force loading of the compressor guide vanes enables the use of such built blades, which are joined together using a suitable soldering, welding, adhesive or other suitable joining technology, without further ado.
  • a suitable soldering, welding, adhesive or other suitable joining technology without further ado.
  • Such a design also makes it particularly easy to use porous, for example ceramic, elements for skimming the boundary layers.
  • FIG. 1 shows a longitudinal section through a compressor according to the invention
  • FIG. 2 shows a compressor according to the invention in connection with a gas turbine
  • FIG. 3 built compressor guide vanes
  • FIG. 4 different embodiments of drainage channels to be arranged in the intake duct
  • FIG. 5 shows an example for controlling the boundary layer skimming of a compressor according to the invention
  • Figure 6 shows another example of a control of
  • Boundary layer skimming of a compressor according to the invention is highly schematic and should only be understood as an instruction.
  • FIG. 1 shows a turbocompressor of a gas turbine group including the inlet duct. It is also implicitly assumed that it is an air-breathing compressor, without thereby restricting the generality of the following statements for other, in particular gaseous, media.
  • the channel walls 1 define an inflow channel 2, through which air flows to the actual compressor inlet 3 and from there into the compressor.
  • the compressor inlet 3 has the shape of a lying bell with an attached inflow channel 2. Downstream of the compressor inlet 3, the configuration shown is essentially rotationally symmetrical in the components essential to the invention, which is why only one half is shown. Support and stiffening elements 4 are arranged in the compressor inlet, which ensure the structural rigidity of the housing.
  • rotor blades 61-67 fastened on a rotor 7 and guide blades 51-57 fastened in the compressor housing 10 are arranged alternately and form the compressor stages, the number of compressor stages shown being in no way representative of a real turbocompressor of a gas turbine: the compressors Stationary power plant gas turbine groups usually have 13 to 17 axial compressor stages, the range specified being by no means to be understood as conclusive. In the interest of clarity of the illustration, however, the restriction was made which does not restrict the generality of the illustration with reference to the details essential to the invention.
  • a preliminary guide row 50 is arranged upstream of the first compressor stages formed by the rotor blade row 61 and the guide blade row 51; an outlet diffuser 11 downstream of the last compressor stage; Its task is to further delay the compressor outflow and so on to build up further pressure, and on the other hand to direct the flow into a combustion chamber - or another consumer - not shown in FIG.
  • the blades of the preliminary guide row 50 and the first two guide vane rows are designed as adjustable blades and are mounted in the housing 10 by means of bearing pins 12.
  • a device 8 provided with spray nozzles is arranged in the inflow channel 2.
  • Another spray device 9 is arranged between two compressor stages.
  • the spray devices 8, 9 can be arranged completely independently of one another, that is to say that the presence of one spray device does not also necessitate the presence of the other.
  • Spray devices 8, 9 are added to the flow in the form of spray jets 81, 91, preferably water or a water-based mixture.
  • the liquid cools the air directly downstream of the injection position by evaporation and by absorbing heat.
  • the amount of water is measured so that drops also flow into the downstream compressor stages. These absorb heat during the compression of the air and gradually evaporate, and ensure 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”.
  • the temperature profile within the compressor corresponds to the profile of the boiling point of the liquid or the cooling limit temperature at the respective pressure in one step.
  • the rise in gas temperature is clearly limited; the gas temperature at the compressor outlet, corresponding to that assigned to the final pressure
  • the boiling point of water is slightly less than 200 ° C when compressed from ambient pressure to a final pressure of 15 bar, and around 234 ° C at a final pressure of 30 bar.
  • these values for isentropic compression and an inlet temperature of 15 ° C are around 351 ° C and 488 ° C, respectively. It is therefore also - although somewhat imprecise - this process is also referred to as "quasi-isothermal compression".
  • the importance of good atomization of the liquid was explained in the introduction. It still cannot the possibility of liquid films being deposited on compressor components is excluded. Adverse effects that potentially result from this are influencing the aerodynamics of the slim compressor blade profiles, as well as an increased degree of obstruction, and an increased sensitivity to flow separation due to the thickened boundary layer.
  • means 110 are therefore arranged at the point mentioned, via which liquid and two-phase boundary layers which form are skimmed off and, as indicated by an arrow, are derived. These funds are used across the board
  • Rows of means 114 for skimming off the liquid film or the two-phase boundary layer are arranged, preferably on the outflow side, on support and stiffening elements 4 protruding into the working medium flow. Further skimming means 115 are arranged on the shaft cover near the hub. Likewise are Rows of means 100, 101, 102, 103, 106, 107 for skimming two-phase boundary layers are arranged on the trailing edges of the leading row blades 50 and the blades of some leading rows 51, 52, 53, 56, 57. The skimmed medium is led out of the housing 10 of the compressor via corresponding lines.
  • the preliminary guide row 50 and the guide rows 51, 52 of the first two compressor stages are designed to be adjustable.
  • the skimmed-off medium is expediently carried out by means of hollow-drilled bearing elements 12.
  • the compressor stages immediately downstream of an injection device there must also be an accumulation of liquid on the walls of the
  • Flow channel can be expected. This is to be expected to a greater extent in the area of compressor blades: there, water drops are centrifuged on the wall with the streamlines on the one hand, and on the other hand, the blades potentially throw water drops against the wall. Therefore, circumferential rows of means 111, 112 are arranged on the wall 10, preferably in the axial region of the blade trailing edges or somewhat downstream thereof, via 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 are essentially distributed in an axial position on the circumference of the outer walls of the flow channel for the working medium, and with corresponding means to discharge the skimmed off medium, such as a drainage system.
  • a water injection device 9 is arranged in the rear part of the compressor, the compressor stages located downstream therefrom are expediently provided in an analogous manner with means 106, 107, 113 for film and two-phase boundary layer skimming.
  • the advantageous effects of the invention are diverse in nature: on the one hand, liquid films from which large water drops and streaks of water can be introduced into the flow are avoided.
  • the means 113 are already arranged downstream of the actual compressor, in the diffuser, on the circumference of the flow channel.
  • the risk of detachment in the diffuser 11 is reduced, and the radially outward flow deflection shown, for example into a plenum of a ring burner, is effectively supported.
  • FIG. 2 shows the invention in connection with a possible embodiment of the means for removing the extracted medium, the turbocompressor being part of a schematically represented gas turbine group.
  • the compressor 21 compresses air to a working pressure and conveys it into an annular combustion chamber 22 in the example. There, fuel is burned in the compressed air.
  • the hot flue gas is expanded in the turbine 23 by delivering a shaft power to the shaft 7.
  • the process control described can be modified in many ways, for example by arranging two turbines in series, between which a further combustion chamber is arranged, or partial compressors connected in series with coolers connected in between can be implemented. Likewise, instead of a combustion chamber
  • Heat exchanger can be arranged in which the working fluid is heated, and the process could be carried out closed and using helium instead of air Work equipment work, and the like, but without affecting the essence of the invention.
  • the shaft is supported at one end on the compressor side in a combined radial / axial bearing 71; On the turbine side, a floating bearing 72 with free axial mobility of the shaft is arranged.
  • the shaft 7 is led out of the housing of the gas turbine group at the end faces; contactless seals, such as labyrinth seals 24, 25, are arranged at these points.
  • a first spray device 8 is arranged in the intake duct 2
  • a second spray device 9 is arranged in the rear part of the compressor 21, only indicated in the figure.
  • the skimming means 100, 101, 102, 103, 106, 107, 110, 111, 112, 113, 114 are only indicated by their position on the compressor, whereby the representation is by no means to be understood to scale, but only schematically the relative positions of the different skimming - And reproduces injectors.
  • the different pressure levels with which the film skimming agent is applied and the resulting different uses of the skimmed off medium make the implementation of different drainage systems for different pressure levels desirable.
  • the pressure is at least at the skimming points 110, 114 and 100 due to the flow rate below the ambient pressure.
  • pressure is built up in the first compressor stages, in the case of a strongly closed preliminary line, a pressure below or just slightly above the ambient pressure can still be present. According to the present exemplary embodiment, the skimming points located upstream of the compressor and those of the first two compressor stages are therefore in a vacuum drainage system
  • the skimming points 101, 102 are connected to the driving nozzles of ejectors 31, 32 which work and are cascaded and work according to the jet pump principle, so that the fluid skimmed off there acts as a driving medium in the ejectors.
  • These ejectors convey medium from the lower upstream pressure points located further upstream.
  • the ejector 32 of the highest pressure is connected on the outflow side to the upper part of a container with a downpipe 33, which in the figure is represented by the fluid interface A. is shown.
  • a liquid column of height h which is in communication with the atmosphere at the lower end, is maintained in the container with downpipe 33.
  • a negative pressure with respect to the atmosphere is created, which corresponds to the height of the liquid column.
  • the outflow from the downpipe can be varied by an actuator 34; a complete closure of this actuator switches off the film suction.
  • the height of the liquid column can be regulated via the actuator 34 and via an additional liquid supply 35, the suction effect being variable over the height of the liquid column.
  • the outflowing liquid is advantageously reprocessed and returned to the process.
  • a suction fan can of course also be used.
  • the fluid skimmed off at point 103 is already at an elevated pressure level which is compatible, for example, with the pressure of a sealing air system. The skimmed fluid is therefore passed into a droplet separator 36.
  • the air skimmed off with the two-phase boundary layer is therefore, as indicated by the fluid interface B, conducted as sealing air to the labyrinth seals 24, 25.
  • a very high pressure has already been reached at the skimming points 106, 107 and 113; these are connected to a high pressure drainage system.
  • this in turn includes two cascaded ejectors 37 and 38, to which the skimming points are connected as a driving or conveying fluid supply line in accordance with the prevailing pressure conditions.
  • the skimmed-off fluid is fed via a droplet separator 39 into a pressure-compatible medium or low-pressure cooling system or cooling line 40.
  • the guide blades which are to be provided with skimming means, can be provided, for example in the manner known from the production of cooled turbine blades, with suction openings and internal drainage channels which connect the suction bores to a drainage system.
  • these manufacturing processes can prove to be very complex due to the necessary high manufacturing accuracy.
  • the - comparatively! - Very low thermal load and the centrifugal force load not present in the guide vanes is very counter.
  • Guide vane elements in particular a guide vane element 501 on the pressure side and a guide vane element 502 on the suction side, are assembled.
  • the guide vane 5 is composed of two shells 501 and 502, and connected 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 , Suction openings 503 are made in one of the shells; the entire interior of the blade is hollow and functions as an internal drainage channel 504.
  • the blade elements 501 and 502 consist of sheets pressed into the corresponding shape, the openings in element 501 simply being punched and deburred; the halves are then glued along seam 505.
  • FIG. 3b illustrates the impressively simple possible manufacture of a built guide vane with a device for boundary layer suction.
  • Figure 3b also shows the possible configuration of a built blade 5 as a full profile.
  • the blade elements 501 and 503 are cast, for example, and connected to one another along a joint 505 in a suitable and known manner.
  • the suction openings 503 and the inner drainage channel 504 are only incorporated in one blade element 501, so that the second blade element does not have to be subjected to a processing step which is oriented thereon, which in turn simplifies production.
  • Openings 503 are then to be designed as spray nozzles - for example, by Nozzles are screwed into the openings - and the corresponding row of guide vanes then acts as a spraying device.
  • FIG. 4 shows - of course not conclusively - different forms of drainage channels 116, as they can be arranged in the intake duct 2 as skimming means.
  • a simplest form is shown in FIG. 4a.
  • a drainage channel 116 is fastened here in the manner of a roof panel in a suitable manner to a wall 1 of the flow channel 2, for example screwed.
  • this embodiment is particularly easy to retrofit on existing systems, on the other hand, the stress caused by aerodynamic forces and the disturbance of the flow must be taken into account.
  • FIG. 5 shows a compressor stage consisting of rotor blades 6 arranged on a shaft 7 and guide blades 5 fastened in the housing 5.
  • the guide vanes 5 are provided with means 503 for skimming two-phase boundary layers, which in turn are connected to means 44 for removing the skimmed-off fluid.
  • an actuator 45 is arranged, by means of which the amount of the removed fluid can be adjusted.
  • a moisture sensor 43 is arranged on the guide vane 5; the actuator 45 is opened with increasing measured moisture.
  • An identical compressor stage is shown in FIG. 6, the actuator 45 being controlled as a function of another parameter. It was hinted above that a sinking
  • Boundary layer thickness is able to reduce the tendency to detach aerodynamically highly loaded blade profiles. It has also been suggested that Generally, when using cooling in a compressor, the pressure build-up shifts to the rear compressor stages, so the load on the rear compressor stages then increases further. This was taken into account in the circuit shown in FIG. 6. 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 in the pressures. Depending on the pressure build-up p2-p1 via the compressor stage, the actuator is opened when the pressure builds up and there is therefore a greater risk of separation.
  • skimming means 503 in a region of the suction side located downstream, close to the rear edge, since the greatest pressure gradients are present there.
  • the main objective is the suction of liquid films to reduce tear-off
  • a degree of reaction is then selected which is less than 0.5 and is, for example, in the range between 0.3 and 0.45, in particular 0.35 to 0.4.
  • Duct walls Intake duct, inflow duct Compressor inlet Support and stiffening elements Compressor guide vane Rotor, shaft Spraying device Spraying device Compressor housing Outlet diffuser Bearing journal, bearing element Compressor Combustion chamber Turbine Labyrinth seal Labyrinth seal Jet pump, ejector jet pump, ejector container with downpipe Throttle and shut-off valve, water pump, water pump Medium-pressure cooling system, line Actuator Flow measuring point for inflow to the spray device 9 Means for removing skimmed fluid Actuator Computing unit, control unit, preliminary row, preliminary row vane, 52,53,54,55,56,57

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Thermal Sciences (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un turbocompresseur qui est équipé de systèmes (8, 9) pour injecter des gouttes de liquide (81, 91) afin d'assurer le refroidissement par évaporation d'un flux de substances actives. Des systèmes (100, 101, 102, 103, 106, 107, 110, 111, 112, 113, 114, 115, 116) conçus pour prélever des couches limites entre deux phases, notamment des films liquides à proximité des parois, permettent de s'opposer à la formation de films liquides indésirables pour diverses raisons sur des parois (1, 10) et de composants (4, 50, 51, 52, 53, 54, 55, 56, 57) faisant saillie dans le canal d'écoulement.
PCT/IB2003/000305 2002-02-19 2003-01-29 Turbocompresseur et procede pour faire fonctionner un tel turbocompresseur WO2003071113A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
AU2003205939A AU2003205939A1 (en) 2002-02-19 2003-01-29 Turboblower and method for operating such a turboblower
DE10390644.4T DE10390644B4 (de) 2002-02-19 2003-01-29 Turboverdichter und Verfahren zum Betrieb eines Turboverdichters

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH0286/02 2002-02-19
CH2862002 2002-02-19

Publications (1)

Publication Number Publication Date
WO2003071113A1 true WO2003071113A1 (fr) 2003-08-28

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DE (1) DE10390644B4 (fr)
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Cited By (12)

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WO2005057019A1 (fr) * 2003-12-09 2005-06-23 Abb Turbo Systems Ag Procede de refroidissement
EP1621741A1 (fr) * 2004-07-28 2006-02-01 Hitachi, Ltd. Turbine à gaz
WO2007017498A1 (fr) * 2005-08-10 2007-02-15 Alstom Technology Ltd Procede de conception aerodynamique d'un compresseur d'une turbomachine
FR2900692A1 (fr) * 2006-05-05 2007-11-09 Snecma Sa Pale de compresseur comprenant un dispositif d'aspiration
US7353654B2 (en) 2001-12-06 2008-04-08 Alstom Technology Ltd Method and apparatus for achieving power augmentation in gas turbines using wet compression
US7353655B2 (en) 2001-12-06 2008-04-08 Alstom Technology Ltd Method and apparatus for achieving power augmentation in gas turbine using wet compression
US7520137B2 (en) 2002-12-02 2009-04-21 Alstom Technology Ltd Method of controlling the injection of liquid into an inflow duct of a prime mover or driven machine
JP2011099450A (ja) * 2006-09-11 2011-05-19 Gas Turbine Efficiency Sweden Ab タービン出力を増加するためのシステム及びその増加方法
DE102010023703A1 (de) * 2010-06-14 2011-12-15 Rolls-Royce Deutschland Ltd & Co Kg Turbomaschine mit Geräuschreduzierung
JP2014190253A (ja) * 2013-03-27 2014-10-06 Mitsubishi Heavy Ind Ltd 吸気冷却システム
EP2669489A3 (fr) * 2012-06-01 2017-11-22 Mitsubishi Hitachi Power Systems, Ltd. Compresseur axial et turbine à gaz avec compresseur axial
EP2484912A3 (fr) * 2011-02-04 2018-05-02 General Electric Company Systèmes de compresseur de gaz humide

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