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WO1992014557A1 - Procede et appareil pour injecter un fluide nettoyant a base de tensio-actif dans des turbines a gaz en fonctionnement - Google Patents

Procede et appareil pour injecter un fluide nettoyant a base de tensio-actif dans des turbines a gaz en fonctionnement Download PDF

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Publication number
WO1992014557A1
WO1992014557A1 PCT/US1992/001222 US9201222W WO9214557A1 WO 1992014557 A1 WO1992014557 A1 WO 1992014557A1 US 9201222 W US9201222 W US 9201222W WO 9214557 A1 WO9214557 A1 WO 9214557A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
manifold
cleaning fluid
surfactant
fluid
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/US1992/001222
Other languages
English (en)
Inventor
Bruce A. Tassone
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.)
Sermatech Inc
Original Assignee
Sermatech Inc
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 Sermatech Inc filed Critical Sermatech Inc
Publication of WO1992014557A1 publication Critical patent/WO1992014557A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B77/00—Component parts, details or accessories, not otherwise provided for
    • F02B77/04—Cleaning of, preventing corrosion or erosion in, or preventing unwanted deposits in, combustion engines

Definitions

  • the present invention relates to the cleaning and maintenance of gas turbines and, more specifically, to a method and apparatus for delivering cleaning solution into an operating gas turbine to remove contaminants and reduce corrosion.
  • Turbine engines are used in a variety of applications including many types of marine vessels and aircraft, military and commercial, large and small.
  • the operation of a gas turbine involves the intake of a large quantity of air through the turbine. Since the high velocity and high volume of intake make filtering the air difficult, airborne contaminants are drawn into the turbine along with the intake air. Moreover, even if filtering of the intake air were practical, gaseous contaminants would still be forced into the turbine.
  • turbine intake gases may comprise a variety of contaminants such as salt spray, oil mist and environmental pollutants.
  • air pollutants, fuel impurities, dust and other contaminants all may enter the turbine. Any turbine exposed to contaminants over time will build up soft deposits of contamination on its interior surfaces.
  • solvent-based cleaning solutions dissolve only certain types of contaminants, they must be mixed with water so that organic deposits, carbon, and inorganic salts can be dissolved and removed. This requirement further tends to limit the effectiveness of solvent-based cleaning solutions, since the contaminants dissolved in the first compressor stages are carried to later stages and are deposited when the solvents and water flash off. Injecting solvents and "cold cranking" at reduced speeds also does not generate sufficient airflow to properly distribute the solvents, leaving the later stages of the turbine fouled and corroded.
  • U.S. patent 4,059,123 discloses a cart containing a compressor along with pressurized bottles of solvent, cleaner, preservative and water.
  • An internal combustion engine mounted on the cart powers both the compressor and an alternator.
  • a storage battery, charged by the alternator, cranks the turbine at ten percent of its rated speed during cleaning.
  • the patent discloses a spray ring that may be clamped to the hub shroud of the turbine which ring comprises two arcuate tube sections connected by a T-section.
  • U.S. patent 4,196,020—Hornak et al. discloses an engine wash spray apparatus adapted to spray water and solvent-based cleaning fluids into gas turbine engines.
  • the apparatus disclosed comprises several spray nozzles and a specifically configured manifold that locates the nozzles relative to the struts and other supporting structures of the intake.
  • the spray nozzles themselves have two parallel flat projections which ensure that a spray pattern having the shape of a rectangular pyramid is created by each nozzle.
  • Surfactant-based gas turbine cleaning compositions provide a solution to fouling and corrosion problems by cleaning turbines of soft deposits and removing built up, baked on deposits from existing fouled and corroded surfaces.
  • the cleaning process may be undertaken while the turbine is operating, thereby enhancing the distribution of the cleaning fluid throughout the turbine.
  • surfactant-based cleaning solutions In addition to surfactant-based cleaning solutions being preferred because they can be used "on-line,” they have also been found to be more effective. In tests, it has been found that turbine engines cleaned while operating using surfactant-basedcleaning fluids exhibiteddramatic reductions of the salt and dirt deposits throughout the compressor, and a significant reduction of the carbon deposits in the combustion and high pressure turbine sections of the engine. As pointed out above, the accumulation of contaminants within the compressor can be particularly troublesome, reducing power, increasing operating temperature and fuel consumption, and causing stalling and vibration during acceleration. However, since surfactant-based cleaning solutions chemically combine with contaminants, the higher temperatures in the latter stages of the turbine make chemical reactions more effective. Even if a surfactant-based cleaning fluid is volatilized by the heat within the turbine, baked on deposits in the combustion chamber and elsewhere are cleaned by surfactant entrained in the air, and are carried away via the gas stream of the exhaust.
  • a further object of the present invention is to provide a method and apparatus which evenly and effectively distribute a spray of surfactant-based cleaning fluid into the intake of a gas turbine.
  • Another object of the present invention is to mount spraying apparatus to a gas turbine in a manner unaffected by the operation of the turbine.
  • apparatus for cleaning an operating turbine engine to effect removal of contaminants and reduce corrosion of the engine parts comprising a reservoir of a surfactant-based cleaning fluid, a pump cooperatively constructed and arranged with said reservoir for maintaining the cleaning fluid in said reservoir at an elevated pressure, and a manifold cooperatively associated with said pump for directing said fluid at a sufficiently elevated pressure into contact with the interior surfaces of said operating turbine to reduce the contaminant deposits on said interior surfaces.
  • the reservoir of the surfactant-based cleaning fluid comprises a drum with a suitable drum pump capable of pressurizing the cleaning fluid to a suitably elevated value that will facilitate an even spray of the fluid onto the interior surfaces of the turbine.
  • such spraying may be achieved by the use of a manifold, which may be tubular, and which comprises a plurality of nozzles so constructed and arranged on the manifold as to evenly spray the fluid into the turbine and into contact with its interior surfaces containing the contaminant deposits that are to be removed.
  • the manifold is equipped with a suitable connection or connections adapted to attach the manifold assembly directly to the turbine, and thereby facilitate the deposition of the desired cleaning fluid into contact with the internal surfaces of the turbine that require cleaning.
  • Such connection may advantageously be effected with a plurality of suitable fasteners, such as hooks, for example, for releasably attaching the manifold assembly to the turbine.
  • the fasteners, or hooks include a flexibly yieldable or compressible section such that, during a cleaning operation, the manifold secured to the engine through such fasteners is, by virtue of the flexibly yieldable or compressible sections, substantially isolated from the vibrations of the operating turbine that occur during the cleaning cycle.
  • each of the fasteners comprises a rod having a hook shaped portion at one end, a compressible spring, and an adjusting device such as a wing nut, for example, connecting the manifold with the other end of the hook.
  • the spring urges the manifold against the turbine structure.
  • the manifold is substantially circular in shape, and has a mounting arm containing a connection to the drum pump.
  • the drum pump itself comprises an inlet valve for regulating a source of compressed air, an outlet connection comprising an outlet valve for regulating the flow of pressurized cleaning fluid, and a filter for removing contaminants from the pressurized fluid.
  • each of the nozzles has an orifice disposed at an angle to the center line axis of the turbine. In operation, the combined spray pattern of all of the nozzles forms a substantially cone-shaped spray.
  • the cleaning fluid used in accordance with the present invention is most preferably pressurized to a pressure of about one hundred (100) pounds per square inch (psi) and most preferably is a surfactant-based fluid consisting essentially of a cationic surfactant and water. However, other pressures may be used.
  • the method for cleaning a turbine engine to effect removal of contaminant deposits and reduce corrosion of the engine parts in accordance with the present invention comprises pressurizing a surfactant-based cleaning fluid maintained in a reservoir zone, directing the cleaning fluid from the pressurized reservoir zone to a distribution zone maintained in close proximity to the intake of an operating turbine engine whose interior surfaces are to be cleaned, dispersing the surfactant-based cleaning fluid in the distribution zone into a plurality of streams, and directing each of such streams onto the interior surfaces of the operating turbine engine at an angle to the centerline axis of the turbine thereby to reduce the contaminant deposits on the interior surfaces of the turbine engine.
  • FIG. 1 is an elevation view of spray cleaning apparatus made in accordance with the present invention.
  • FIG. 2 is a plan view of the ring-shaped manifold of the present invention.
  • FIG. 3 is an elevation view of the apparatus illustrated in FIG. 2.
  • FIG. 1 there is shown a preferred embodiment of the apparatus of the present invention 100.
  • a cart 102 is provided which contains a reservoir of surfactant- based cleaning fluid suitable for cleaning gas turbines contained in a suitable container, such as drum 104.
  • the cart 102 will be provided with casters 103 to enable the apparatus of the present invention to be moved into the proximity of the gas turbine being cleaned.
  • the cart 102 may be replaced by a cradle for restraining the drum 104, or may be dispensed with altogether if the drum 104 is sufficiently free standing.
  • the drum 104 is provided with a drum pump assembly 106 which takes pressurized air and causes the flow of pressurized fluid.
  • Pressure on the cleaning fluid in drum 104 is provided by a source of compressed air 110 (not illustrated) which may either be mounted in the cart 102 or remotely located.
  • the present invention provides surfactant-basedcleaning fluidpressurized to about 100 psi.
  • the source of compressed air 110 is connected to the drum pump 106 at an inlet connection 107, which most preferably includes a ball valve 117 and other necessary connecting hardware.
  • the outlet connection 108 is most preferably comprised of a ball valve 118 and also preferably includes filters and traps 109 as shown.
  • the outlet connection 108 is connected to a flexible hose 112 which carries pressurized surfactant-based cleaning fluid to the ring-shaped manifold 120.
  • the flexible hose 112 is preferably a stainless steel-jacket flexible hose, encased in a rubber outer jacket, suitable for carrying pressurized fluids in the environment of the turbine being cleaned.
  • the ring-shaped manifold 120 of the present invention is most preferably a continuous, tubular apparatus having a plurality of spaced-apart spray nozzles 122.
  • six nozzles 122 are equally spaced around the circumference of the manifold 120.
  • twelve nozzles 122 are provided.
  • Each nozzle 122 has an orifice which is disposed at an angle to the centerline of the turbine such that when fluid is pumped through the orifices, the combined spray patterns of the nozzles 122 will form a cone- shaped spray suitable for introduction into the intake of an operating turbine.
  • the exact number and spacing of the nozzles will depend to some extent upon the amount of cleaning fluid that must be delivered into the intake, as well as the airflow at the intake and the concentration and formulation of the surfactant-based cleaning fluid.
  • fasteners, or hooks 128 for mounting the manifold 120 to the turbine are also provided. As explained in greater detail below, in a preferred embodiment, these hooks permit the manifold to be flexibly mounted to the turbine.
  • a mounting arm 124 extends from the manifold 120, permitting the manifold 120 to be handled and correctly positioned.
  • the mounting arm 124 includes also a hook 128.
  • the manifold 120 is an integral, welded stainless steel assembly, including both the ring- shaped section and the mounting arm 124.
  • the manifold assembly may be cast, formed or otherwise fabricated from any number of individual parts which are later welded, brazed or affixed together, or joined using mechanical fasteners or threaded connections.
  • FIG. 3 there is illustrated an elevation view of the manifold 120 illustrated in FIG. 2.
  • the mounting arm 124 is most preferably bent at approximately a right angle to the plane of the ring-shaped portion of the manifold 120 to provide a convenient position for a connection 126 for joining the flexible hose 122 to the manifold 120.
  • the connection 126 is preferably a quick- disconnect fitting, suitable for pressurized applications.
  • FIG. 3 also illustrates the fasteners or hooks 128 described above, used to fasten the manifold 120 to the turbine in a flexible fashion.
  • the hooks 128 comprise a hook-shaped portion 129 of a rod, or other structure adapted to engage a portion of the turbine.
  • a coil spring 130 or other flexible means is provided and is adjustably fastened by a wing nut 132 or the like, in a position whereby the spring 130 will be compressed and flexibly urge the manifold 120 against the turbine when installed.
  • the wing nut 132 or similar adjusting means may be threaded up or down the hooks 128 to adjust the relative distance between the hook-shaped portion 129 and the manifold 120. When properly adjusted, the engagement of the wing nut 132 and the spring will produce a compressible anchorage when the hook portion 129 is engaged with the turbine structure.
  • the present invention also provides a method of cleaning operating gas turbines using surfactant-based cleaning fluids.
  • a quantity of pressurized cleaning fluid is supplied and a manifold connected to the fluid supply is attached to the turbine.
  • the connection of the manifold to the turbine is created by one or more flexible hook means.
  • the pressurized fluid is then transported to the manifold and then to a plurality of nozzles that spray the pressurized fluid into the turbine.
  • the fluid is sprayed in streams which are disposed at an angle to the centerline axis of the turbine to form a cone-shaped spray pattern.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cleaning By Liquid Or Steam (AREA)

Abstract

L'invention se rapporte à des procédés et à un appareil (100) qui servent à nettoyer des turbines à gaz en fonctionnement au moyen de fluides nettoyants à base de tensio-actifs. On a découvert que les fluides nettoyants à base de tensio-actifs peuvent effectivement débarrasser les surfaces intérieures de turbines à gaz de leurs dépôts contaminants et qu'ils sont particulièrement adaptés à être utilisés pendant que la turbine fonctionne. L'invention décrit un réservoir (104), une pompe (106) et un collecteur (120) destinés à vaporiser les fluides nettoyants à base de tensio-actifs dans les turbines à gaz. Le collecteur (120) est de préférence de forme annulaire et il contient plusieurs injecteurs disposés de façon à créer un modèle de vaporisation en forme de cône. Dans un mode de réalisation préféré, le collecteur (120) est monté sur la turbine au moyen de plusieurs crochets sollicités par ressorts, ces crochets servant à isoler efficacement le collecteur des vibrations de la turbine.
PCT/US1992/001222 1991-02-13 1992-02-13 Procede et appareil pour injecter un fluide nettoyant a base de tensio-actif dans des turbines a gaz en fonctionnement Ceased WO1992014557A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US65481291A 1991-02-13 1991-02-13
US654,812 1991-02-13

Publications (1)

Publication Number Publication Date
WO1992014557A1 true WO1992014557A1 (fr) 1992-09-03

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PCT/US1992/001222 Ceased WO1992014557A1 (fr) 1991-02-13 1992-02-13 Procede et appareil pour injecter un fluide nettoyant a base de tensio-actif dans des turbines a gaz en fonctionnement

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6712080B1 (en) * 2002-02-15 2004-03-30 The United States Of America As Represented By The Secretary Of The Army Flushing system for removing lubricant coking in gas turbine bearings
WO2005028119A1 (fr) * 2003-09-25 2005-03-31 Gas Turbine Efficiency Ab Buse et procede destines au lavage de compresseurs de turbines a gaz
US7445677B1 (en) 2008-05-21 2008-11-04 Gas Turbine Efficiency Sweden Ab Method and apparatus for washing objects
EP2263809A3 (fr) * 2004-06-14 2011-11-02 Gas Turbine Efficiency AB Système de lavage d'un moteur de turbine à gaz aérienne
US8216392B2 (en) 2007-03-16 2012-07-10 Lufthansa Technik Ag Device and method for cleaning the core engine of a jet power plant
CN104438177A (zh) * 2014-11-11 2015-03-25 沈阳黎明航空发动机(集团)有限责任公司 一种高涡叶片内腔残留荧光液的清理方法及清洗夹头
EP2213845B1 (fr) 2004-02-16 2016-05-04 EcoServices, LLC Procédé pour le lavage du moteur central d'un moteur à turbine à gaz
EP3055532A4 (fr) * 2013-10-10 2017-04-12 EcoServices, LLC Collecteur de lavage de moteur à passage radial
EP1882823A3 (fr) * 2006-07-27 2018-01-03 Rolls-Royce plc Système et procédé de nettoyage d'avion
US9926517B2 (en) 2013-12-09 2018-03-27 General Electric Company Cleaning solution and methods of cleaning a turbine engine
RU180997U1 (ru) * 2017-04-21 2018-07-03 Общество с ограниченной ответственностью "Газпром трансгаз Уфа" Устройство для очистки осевого компрессора газотурбинной установки
US11834632B2 (en) 2013-12-09 2023-12-05 General Electric Company Cleaning solution and methods of cleaning a turbine engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2974925A (en) * 1957-02-11 1961-03-14 John C Freche External liquid-spray cooling of turbine blades
US3623668A (en) * 1968-03-04 1971-11-30 Gen Electric Wash manifold
US3779213A (en) * 1970-11-10 1973-12-18 Rivenaes Ivar Cleaning internal combustion engines or the like
US4059123A (en) * 1976-10-18 1977-11-22 Avco Corporation Cleaning and preservation unit for turbine engine
US4196020A (en) * 1978-11-15 1980-04-01 Avco Corporation Removable wash spray apparatus for gas turbine engine
US4808235A (en) * 1987-01-20 1989-02-28 The Dow Chemical Company Cleaning gas turbine compressors

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2974925A (en) * 1957-02-11 1961-03-14 John C Freche External liquid-spray cooling of turbine blades
US3623668A (en) * 1968-03-04 1971-11-30 Gen Electric Wash manifold
US3779213A (en) * 1970-11-10 1973-12-18 Rivenaes Ivar Cleaning internal combustion engines or the like
US4059123A (en) * 1976-10-18 1977-11-22 Avco Corporation Cleaning and preservation unit for turbine engine
US4196020A (en) * 1978-11-15 1980-04-01 Avco Corporation Removable wash spray apparatus for gas turbine engine
US4808235A (en) * 1987-01-20 1989-02-28 The Dow Chemical Company Cleaning gas turbine compressors

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6712080B1 (en) * 2002-02-15 2004-03-30 The United States Of America As Represented By The Secretary Of The Army Flushing system for removing lubricant coking in gas turbine bearings
US7670440B2 (en) 2003-09-25 2010-03-02 Gas Turbine Efficiency Ab Nozzle and method for washing gas turbine compressors
US7938910B2 (en) 2003-09-25 2011-05-10 Gas Turbine Efficiency Ab Method for washing gas turbine compressor with nozzle
RU2343299C2 (ru) * 2003-09-25 2009-01-10 Газ Турбин Эффишенси Аб Форсунка и способ промывки компрессоров газотурбинных установок
WO2005028119A1 (fr) * 2003-09-25 2005-03-31 Gas Turbine Efficiency Ab Buse et procede destines au lavage de compresseurs de turbines a gaz
EP2213845B1 (fr) 2004-02-16 2016-05-04 EcoServices, LLC Procédé pour le lavage du moteur central d'un moteur à turbine à gaz
EP2263809A3 (fr) * 2004-06-14 2011-11-02 Gas Turbine Efficiency AB Système de lavage d'un moteur de turbine à gaz aérienne
US8479754B2 (en) 2004-06-14 2013-07-09 Ecoservices, Llc System for washing an aero gas turbine engine
US9376932B2 (en) 2004-06-14 2016-06-28 Ecoservices, Llc Turboengine water wash system
US10041372B2 (en) 2004-06-14 2018-08-07 Ecoservices, Llc System for washing an aero gas turbine engine
US9657589B2 (en) 2004-06-14 2017-05-23 Ecoservices, Llc System for washing an aero gas turbine engine
US9708928B2 (en) 2004-06-14 2017-07-18 Ecoservices, Llc Turboengine water wash system
EP1882823A3 (fr) * 2006-07-27 2018-01-03 Rolls-Royce plc Système et procédé de nettoyage d'avion
US8216392B2 (en) 2007-03-16 2012-07-10 Lufthansa Technik Ag Device and method for cleaning the core engine of a jet power plant
US10634004B2 (en) 2007-03-16 2020-04-28 Lufthansa Technik Ag Device and method for cleaning the core engine of a jet engine
US10539040B2 (en) 2007-03-16 2020-01-21 Lufthansa Technik Ag Device and method for cleaning the core engine of a jet engine
US7445677B1 (en) 2008-05-21 2008-11-04 Gas Turbine Efficiency Sweden Ab Method and apparatus for washing objects
EP3055532A4 (fr) * 2013-10-10 2017-04-12 EcoServices, LLC Collecteur de lavage de moteur à passage radial
US9932895B2 (en) 2013-10-10 2018-04-03 Ecoservices, Llc Radial passage engine wash manifold
AU2014374334B2 (en) * 2013-10-10 2019-05-16 Ecoservices, Llc Radial passage engine wash manifold
US9926517B2 (en) 2013-12-09 2018-03-27 General Electric Company Cleaning solution and methods of cleaning a turbine engine
US11834632B2 (en) 2013-12-09 2023-12-05 General Electric Company Cleaning solution and methods of cleaning a turbine engine
US12187986B2 (en) 2013-12-09 2025-01-07 General Electric Company Cleaning solution and methods of cleaning a turbine engine
CN104438177A (zh) * 2014-11-11 2015-03-25 沈阳黎明航空发动机(集团)有限责任公司 一种高涡叶片内腔残留荧光液的清理方法及清洗夹头
RU180997U1 (ru) * 2017-04-21 2018-07-03 Общество с ограниченной ответственностью "Газпром трансгаз Уфа" Устройство для очистки осевого компрессора газотурбинной установки

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