WO2017222516A1 - Procédé et système permettant de réduire des dommages dus à des impacts de gouttelettes de liquide par des surfaces superhydrophobes - Google Patents

Procédé et système permettant de réduire des dommages dus à des impacts de gouttelettes de liquide par des surfaces superhydrophobes Download PDF

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Publication number
WO2017222516A1
WO2017222516A1 PCT/US2016/038707 US2016038707W WO2017222516A1 WO 2017222516 A1 WO2017222516 A1 WO 2017222516A1 US 2016038707 W US2016038707 W US 2016038707W WO 2017222516 A1 WO2017222516 A1 WO 2017222516A1
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WO
WIPO (PCT)
Prior art keywords
component
droplets
fluid droplets
fluid
compressor section
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/US2016/038707
Other languages
English (en)
Inventor
Pawel JEDRZEJOWSKI
Walter Kasimierz Omielan
Ali Dolatabadi
Mason MARZBALI
Moussa TEMBELY
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to PCT/US2016/038707 priority Critical patent/WO2017222516A1/fr
Publication of WO2017222516A1 publication Critical patent/WO2017222516A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
    • F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
    • F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other 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
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/512—Hydrophobic, i.e. being or having non-wettable properties
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the present disclosure relates generally to engineered surfaces, and also to systems and processes for reducing or preventing erosion stemming from fluid droplets.
  • Turbine power plants such as gas turbines, are used in a variety of useful applications. Aviation, shipping, power generation, and chemical processing have all benefited from turbine power plants of various designs.
  • Turbine power plants e.g., combustion turbines
  • natural gas mostly methane
  • kerosene or synthetic gas (such as carbon monoxide) is fed as fuel to the combustion section, but other fuels may be used.
  • the rotor - defined by a rotor shaft, attached turbine section rotor blades, and attached compressor section rotor blades - mechanically powers the compressor section and, in some cases, a compressor used in a chemical process or an electric generator.
  • the exhaust gas from the turbine section can be used to achieve thrust; it also can be a source of heat and energy or, in some cases, it is discarded.
  • wet compression enables power augmentation in turbine power plants by reducing the work required for compression of the inlet air.
  • This thermodynamic benefit is realized within the compressor of a gas turbine through "latent heat intercooling."
  • latent heat intercooling water (or some other appropriate liquid) added to the air and inducted into the compressor cools the air through evaporation as the air is being compressed.
  • the added water can be conceptualized as an "evaporative liquid heat sink".
  • the wet compression approach thus saves an incremental amount of work (which would have been needed to compress air not containing the added water) and makes the incremental amount of work available to either drive the load attached to the gas turbine (in the case of a single shaft machine) or to increase the compressor speed to provide more mass flow (which can have value in both single shaft and multiple shaft machines).
  • the temperature of the air stream may be reduced as it is being compressed, thereby decreasing the energy required for compression therein, and thereby increasing power output and efficiency of the associated turbine.
  • Various methods and apparatuses have been employed to facilitate the introduction of fluid (i.e. , water) to the working fluid of turbine power plants so as to realize the benefits of wet compression.
  • the present inventors have found through significant analytical and numerical modeling along with experimental testing that in order to have sufficient mobility of droplets on the wetted surface for droplets having a Weber number, We, of less than or equal to about 2, a substrate will need to have a surface modification that exhibits a water receding contact angle > about 120° upon contact with the droplets to prevent coalescence of the droplets thereon. If the water droplet receding contact angle on the surface is less than about 120° in such cases, the substrate will be insufficient to prevent or sufficiently reduce droplet coalescence on a surface thereof. At higher Weber numbers, the rebound can happen for receding angles as low as 1 10°.
  • the surface modification comprises a hydrophobic coating on the surface of the substrate.
  • a method for reducing or eliminating damage to a component being subjected to droplets having a Weber number (We) of about 2 or less comprising modifying a surface of the component such that the surface exhibits a water receding contact angle ⁇ about 120° upon contact with said droplets.
  • one exemplary application for the systems and processes described herein is in the area of gas turbine engines, including those comprising a wet compression system as is known in the art.
  • these droplets may increase in size, mobilize or re-atomize from the component, and re-enter the flowing air stream being compressed.
  • These coalesced fluid droplets may travel at high speeds and impact a second component, such as a rotating blade, of the compressor section and cause considerable damage thereto.
  • modifying a surface of the first component such that the surface exhibits a water receding contact angle ⁇ 120° upon contact with the first fluid droplets and such that the modified surface is effective to prevent or reduce coalescence of the first fluid droplets into a film or into second fluid droplets larger than the first fluid droplets on the first component;
  • the film or second fluid droplets would form to a greater degree, enter the flowing air stream, and impact the second component, thereby causing damage thereto.
  • the coatings with large receding contact angles described herein increase droplet mobility and reduce opportunity for fluid coalescence on the first component. In this way, the formation of larger particles on the first component, which may cause significant damage downstream, is avoided.
  • droplets having a greatest dimension of > 100 ⁇ are hereby avoided by application of the coating to the first component.
  • the present inventors have found, in fact, that increased droplet size may exponentially increase component damage. Therefore, reducing fluid droplet coalescence may have substantial impact toward reducing component damage and increasing product lifetime.
  • the surface of the at least one stationary component is effective to limit fluid droplet coalescence on the at least one stationary component, thereby reducing or eliminating a likelihood of downstream fluid droplet impact damage to the at least one rotating component.
  • a component comprising a surface that exhibits a water receding contact angle ⁇ about 120 degrees upon contact with droplets having a Weber number (We) ⁇ 2.
  • the surface modification comprises a hydrophobic coating on a surface of the component.
  • a system for reducing liquid impingement damage comprising:
  • the first component comprises a surface that exhibits a water receding contact angle > about 120 degrees upon contact with the first fluid droplets, the first fluid droplets having a Weber number (We) ⁇ 2, thereby preventing coalescence of the first fluid droplets on the surface of the first component.
  • a gas turbine engine comprising:
  • a compressor section comprising at least one stationary component and at least one rotating component configured to generate compressed air at an outlet thereof;
  • a combustion section for combusting fuel and an amount of the compressed air from the compressor section to produce a working gas
  • a wet air compression system configured for introducing a plurality of fluid droplets into a flowing air stream of the compressor section
  • the at least one stationary component of the compressor section comprises a coating that exhibits a water receding contact angle > about 120 degrees upon contact with first fluid droplets having a Weber number (We) ⁇ 2, thereby preventing coalescence of the first fluid droplets on a surface of the at least one stationary component.
  • FIG. 1 is a schematic of a system for reducing liquid impingement damage in accordance with an aspect of the present invention.
  • FIG. 2 is schematic of a gas turbine engine configured to reduce liquid impingement damage therein in accordance with an aspect of the present invention.
  • FIG. 3 illustrates a portion of a gas turbine engine having a wet compression system in accordance with an aspect of the present invention.
  • FIG. 4 illustrates the formation of larger damage-causing droplets in a typical prior art system.
  • FIG. 5 illustrates a turbine vane having a coating in accordance with an aspect of the present invention.
  • FIG. 6 illustrates a plot of Weber number vs. receding angle in accordance with an aspect of the present invention.
  • the present inventors have developed systems and processes to reduce damage caused by impacting fluid droplets via increasing droplet mobility and reducing fluid droplet coalescence on subject component(s).
  • the component 2 includes a surface, e.g., engineered surface 8, that exhibits a water receding contact angle > about 120 degrees upon contact with moving droplets having a Weber number (We) ⁇ 2.
  • the fluid droplets may readily slide (rebound) off the surface 8 when contacting the same.
  • the component 2 is at least slightly tilted or angled when exposed to a flow of a flowing gas stream.
  • the engineered surface 8 comprises a coating 7 as shown in FIG. 5 which is applied to an outer portion of a body of the component 2 and forms an external surface thereon.
  • the coating 7 may be any suitable material providing the desired properties described herein (a water receding contact angle ⁇ about 120° upon contact with moving droplets having a We ⁇ 2).
  • the coating 7 may comprise any suitable thickness effective to provide the desired water receding contact angle. Without limitation, the coating 7 may have a thickness of from about 0.001 mm to about 3 mm. As used herein, the term “about” refers to a value which is ⁇ 5% of the stated value. Further, when a coating 7 is present, the coating 7 may be applied on an outer portion of the component 2 by any suitable method such as by a chemical vapor deposition (CVD), physical vapor deposition (PVD), thermal spraying, slurry or paint application. Of note, in the embodiment shown in FIG. 5, the component 2 is illustrated as being a turbine component, e.g., a vane 20, as is known in the art. However, it is understood that the present invention is not so limited.
  • a surface must have a minimum receding angle in order to properly dispel fluid droplets having a relatively small Weber number, e.g. ⁇ about 2. If the receding angle is not large enough, the coating will simply be ineffective or not as effective as desired when being contacted by such droplets.
  • Weber number We
  • p w is the water density
  • v is a droplet velocity component normal to the surface
  • D is droplet diameter
  • ⁇ is surface tension.
  • the Weber number for the subject droplets may be measured by any suitable technique known in the art.
  • the droplet diameter may be measured using a laser diffraction technique.
  • the water receding contact angle of the surface 8 may be measured by any suitable technique known in the art.
  • the water receding contact angle may be determined by procedures as disclosed in Burnett et al, J. Vac. Sci. Techn. B, 23(6), pages 2721-2727 (Nov/Dec 2005).
  • discrete phase modeling of air and water droplets in a compressor showed a We below 8 in front of the first static component in the compressor.
  • the values were confirmed by extensive experimentation and measurements in a compressor rig operating under the same conditions in terms of air flow, air speed, volume of injected water and droplet sizes as a real turbine engine. During such experimentation, the present inventors have found via simulating water droplet impact and film formation, a relationship between We values and minimum receding contact angle 6 R that will prevent film formation on components.
  • FIG. 6 presents results of numerical simulation of droplet impact for different impact speeds and surface properties.
  • empty symbols represent wetting behavior where the droplet either splashes or stays on a surface.
  • Full symbols represent droplets rebounding from a surface.
  • the dashed line represents the numerical solution of the rebound condition.
  • the ability for a droplet to rebound from a surface may be influenced by both its respective Weber number (We) and a receding contact angle for the surface.
  • We Weber number
  • a droplet rebounds only for high receding contact angles (y axis).
  • the receding contact angle plays a role in determining the wetting region.
  • We e.g., ⁇ 5 impacts
  • rebound can occur for receding contact angles as low as 1 10°.
  • Very large Weber numbers may also lead to droplet splashing. Again, for lower Weber numbers, higher receding contact angles are necessary for rebound.
  • the present invention is not so limited to forming the subject receding angle of ⁇ 120° by applying a coating thereto.
  • the term "engineered surface” as used herein may also refer to a surface which has been physically or chemically modified to achieve the desired surface properties required herein. Exemplary surface modifications include, but are not limited to: laser patterning; electro-deposition; surface etching or engraving; surface patterning by additive manufacturing; and overlay coating with materials having a desired surface morphology or a combination of all those methods.
  • FIG. 1 illustrates a component 2 described above in a system 1 for reducing fluid droplet impact damage in accordance with an aspect of the present invention.
  • the system 1 comprises the component 2 (first component), a second component 3, a flowing gas stream 4 from a suitable source (not shown) which may flow past or over the first component 2 and the second component 3 at a suitable flow rate.
  • a source 5 of first fluid droplets is in communication with the flowing gas stream 4 and may be configured to introduce first fluid droplets 6 into the flowing gas stream 4.
  • the first component 2 comprises an engineered surface 8 as described above that exhibits a water receding contact angle greater than about 120° upon contact with droplets having a Weber number > 2.
  • the surface 8 is effective to increase mobility of the first fluid droplets 6 upon contact of such droplets with the surface 8. This means that instead of resting on a surface 8 of the first component 2 and coalescing into larger droplet fluid particles or a continuous film, the engineered surface 8 (e.g., a surface coated with a coating 7 as described herein) helps maintain the original droplet size distribution of the first fluid droplets 6, or minimally larger ones, moving into the flowing gas stream 4 as shown in FIG. 1 .
  • droplets may coalesce on the first component 2 into larger droplets or a continuous film which may be carried and/or re-atomize into flowing stream 4 and contact the second component 3. Since larger droplets or the continuous film tend to cause further downstream damage, damage to the second component 3 would occur. However, since such coalescence into larger droplets or a continuous film is prevented by aspects of the present invention, impact by such larger droplets 9 is hereby reduced since the larger droplets 9 are substantially prevented from forming on the first component 2.
  • the first component 2 may be a stationary component while the second component 3 may be a rotating component, although it is understood the present invention is not so limited.
  • Rotating components which are themselves moving, may be particularly prone to stress, strain, erosion, and damage caused by impact of fluid droplets, especially those with a Weber number ⁇ 2.
  • the first component 2 may be a rotating component and the second component 3 may be a stationary or a rotating component.
  • FIG. 2 illustrates a more particular embodiment of a system and process for reducing fluid droplet impact damage involving a stationary component and a rotating component in a gas turbine engine environment.
  • FIG. 2 shows a gas turbine engine 10 employing aspects of the present invention and including an inlet section 1 1 , a compressor section 12, a combustor section 14, a turbine section 16, and an exhaust 17.
  • the compressor section 12 compresses ambient air 18 that enters the inlet section 1 1 .
  • the compressor section 12 there are rows of vanes 20 and rows of rotating blades 22 coupled to a rotor that may define a first component 2 and a second component 3, respectively.
  • Each pair of rows of vanes 20 and blades 22 forms a stage in the compressor section 12.
  • the vane 20 may comprise a VSV (Variable Stator Vane) which may be more static compared to the rotor, but articulates on its own axis to control the air flow into the compressor
  • the compressor section 12 serves as an air pump, converting low pressure, low density ambient air drawn into the compressor section 12 into high pressure air prior to delivering the high pressure air to the combustor section 14.
  • the high pressure air 18 flowing through the compressor section 12 may define a flowing gas stream 4 as described above.
  • the compressor section 12 raises the temperature of the air by about 550°F as the air is compressed.
  • the compressor section 12 includes fourteen stages. Each stage incrementally boosts the pressure from the previous stage. Within each stage, one or more vanes 20 may be positioned at an angle such that the exiting air is directed toward one or more rotor blades 22 of the next stage at the most efficient angle. By way of example, the process may be repeated fourteen times as the air flows from the first stage through the fourteenth stage.
  • the compressor section 12 may also include inlet vanes 24, e.g. , variable inlet guide vanes, and outlet guide vanes (not shown).
  • the inlet vane 24 may neither be divergent or convergent. I n an embodiment, the inlet guide vanes 24 direct air to the first stage compressor blades at the "best" angle.
  • the outlet guide vanes on the other hand, "straighten” the air to provide the combustor section 14 with the proper airflow direction.
  • the turbine 1 0 may employ a wet air compression system 26, such as an Inlet Spray Intercooling (ISI) System, configured to introduce a plurality of droplets 6 of a fluid, such as water, into the flowing gas stream 4 of the compressor section 12.
  • the system 26 may thus define a first fluid droplet source 5 as described above.
  • the system 26 introduces first fluid droplets 6 to the flowing gas stream 4 upstream of the compressor section 12 or within the inlet section 1 1 .
  • an exemplary system 26, e.g., an ISI system comprising a spray bar 28 which is configured to deliver a plurality of first fluid droplets 6 toward flowing gas stream 4 flowing through a portion of the compressor section 12.
  • the first fluid droplets 6 may be of any suitable size, composition, and may be in any suitable form.
  • the droplets comprise water.
  • the droplets 6 may have a particle size of 0.01 to 0.10 mm.
  • the first fluid droplets 6 may be effective to reduce ambient inlet temperature to the compressor section 12 and decrease the energy required for compression of the air stream therein, thereby increasing power output and efficiency of the turbine 10, for example.
  • FIG. 3 For purposes of showing the utility of the present invention in different turbine systems, a different turbine from that of FIG. 2 is shown in FIG. 3.
  • the combustor section 14 combines the compressed air with a fuel and ignites the mixture creating combustion products comprising a hot working gas defining a working fluid.
  • the working fluid then travels to the turbine section 16.
  • Within the turbine section 16 are rows of stationary vanes 32 and rows of rotating blades 34 coupled to a rotor. Each pair of rows of vanes 32 and blades 34 may similarly form a stage in the turbine section 16.
  • the rows of vanes 32 and rows of blades 34 extend radially into an axial flowpath extending through the turbine section 16.
  • the working fluid expands through the turbine section 16 and causes the blades 34, and therefore the rotor to rotate.
  • the rotor extends into and through the compressor 12, and may provide power to the compressor section 12 and output power to an electrical generator, compressor, pump, or other equipment.
  • the present inventors have recognized that not all of the added first fluid droplets 6 will be evaporated, and that without intervention the first fluid droplets 6 may tend to coalesce and form even larger second fluid droplets 9 or a continuous film on components of the compressor section 12.
  • the present inventors have found that without intervention such larger second fluid droplets may be carried or re-atomized by the flowing gas stream 4 off a first component 2, such as vane 20 or 24, and impact a second component 3, such as blade 22, thereby causing damage to the second component 3. This may particularly be the case at the high velocities of the air stream (flowing gas stream 4) being compressed in the compressor section 12.
  • the above phenomenon is again depicted by way of example in FIG.4.
  • the second component 3 may comprise a rotating component, such as blade 22, of the compressor section 12 while the first component 2 may comprise a stationary component thereof, such as a stationary vane 20 or 24.
  • the second fluid droplets 9 may comprise coalesced fluid droplets on the surfaces of a stationary component of the inlet section 1 1 and/or compressor section 12. These coalesced droplets 9 may become increasingly more destructive the larger they grow. In fact, there is an exponential relationship between droplet size and component damage - meaning the larger the droplet size formed, the vastly greater amount of damage which may be brought about by the large droplets.
  • aspects of the present invention again aim to reduce and/or substantially eliminate the coalescence of water droplets on the surface of a first component 2, which could result in the formation of larger- sized second fluid droplets 9 that may cause damage to components downstream of the first component 2.
  • aspects of the present invention propose to accomplish the same by surface engineering
  • any components of the inlet section 1 1 and/or compressor section 10 may be surface engineered, such as by applying a suitable coating 7 thereto, to exhibit a high water fluid receding contact angle as described herein in order to reduce and/or prevent the coalescence of first fluid droplets 6 into larger second fluid droplets or a continuous film.
  • a vane 20 of the compressor section 12 comprising an engineered surface 8, e.g., coating 7, to effect a water receding contact angle ⁇ about 120 degrees upon contact with droplets having a Weber number ⁇ about 2.
  • the coating 7 may thus be effective to prevent the coalescence of fluid droplets thereon into larger droplets or a film thereon.
  • the smaller droplet sizes thus maintained in the compressor section 12 may thus result in considerably less damage to components of the gas turbine 10, such as rotating components of the compressor section 12, since the larger the fluid particles formed, the larger the damage caused by impact by the fluid particles.
  • the engineered surfaces 8 described herein are shown in a gas turbine 10 comprising a wet air compression system 26, the present invention is not so limited and this example is merely illustrative. It is appreciated that the principles applied herein may be applied in other applications.
  • the coating 7 may be applied on a static component of a low pressure steam turbine to avoid condensation as illustrated in FIG. 4 and erosion of a downstream steam turbine blade.
  • the engineered surfaces 8 may also be brought about in other applications, such as in within aeroengines to reduce the erosion of the engine core components when exposed to snow, rain, and the like.
  • the engineered surfaces 8 described herein may be utilized so as to decrease damage due to ice accretion (due to the reduced ability of water to accumulate on the surface 8 due to the coating 7 or the like).

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention a pour objet des systèmes et des procédés qui empêchent des dommages dus à des impacts de gouttelettes de fluide par l'ingénierie de surface d'un composant respectif (2) pour présenter un angle de contact de reculée avec l'eau ≥ environ 120 degrés lors du contact avec des gouttelettes (6) ayant un indice de Weber ≤ 2. Le système peut comprendre un moteur à turbine à gaz ayant un dispositif d'injection d'eau pour la compression de l'air humide.
PCT/US2016/038707 2016-06-22 2016-06-22 Procédé et système permettant de réduire des dommages dus à des impacts de gouttelettes de liquide par des surfaces superhydrophobes Ceased WO2017222516A1 (fr)

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PCT/US2016/038707 WO2017222516A1 (fr) 2016-06-22 2016-06-22 Procédé et système permettant de réduire des dommages dus à des impacts de gouttelettes de liquide par des surfaces superhydrophobes

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PCT/US2016/038707 WO2017222516A1 (fr) 2016-06-22 2016-06-22 Procédé et système permettant de réduire des dommages dus à des impacts de gouttelettes de liquide par des surfaces superhydrophobes

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Citations (6)

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WO2003044374A1 (fr) * 2001-11-19 2003-05-30 Alstom Technology Ltd Compresseur pour turbines a gaz
DE102004001958A1 (de) * 2004-01-13 2005-08-11 Alstom Technology Ltd Lufttechnische Einrichtung
EP1844863A1 (fr) * 2006-04-12 2007-10-17 General Electric Company Article ayant une surface de mouillabilité réduite et sa méthode de production
DE102009003898A1 (de) * 2009-01-03 2010-07-08 Harald Prof. Dr. Dr. habil. Reiss Turbinenschaufeln und andere massive Bauteile
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