WO2007102738A1 - Procede et dispositif de nettoyage d'un compresseur axial - Google Patents

Procede et dispositif de nettoyage d'un compresseur axial Download PDF

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Publication number
WO2007102738A1
WO2007102738A1 PCT/NO2006/000089 NO2006000089W WO2007102738A1 WO 2007102738 A1 WO2007102738 A1 WO 2007102738A1 NO 2006000089 W NO2006000089 W NO 2006000089W WO 2007102738 A1 WO2007102738 A1 WO 2007102738A1
Authority
WO
WIPO (PCT)
Prior art keywords
detergent
cleaning
compressor
axial compressor
accordance
Prior art date
Application number
PCT/NO2006/000089
Other languages
English (en)
Inventor
Lyder Moen
Original Assignee
Dynatrend As
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 Dynatrend As filed Critical Dynatrend As
Priority to PCT/NO2006/000089 priority Critical patent/WO2007102738A1/fr
Publication of WO2007102738A1 publication Critical patent/WO2007102738A1/fr

Links

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
    • F04D29/70—Suction grids; Strainers; Dust separation; Cleaning
    • F04D29/701—Suction grids; Strainers; Dust separation; Cleaning especially adapted for elastic fluid pumps
    • F04D29/705—Adding liquids
    • 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
    • F01D25/002—Cleaning of turbomachines

Definitions

  • This invention regards a method of cleaning compressor blades in an axial compressor. More particularly, it regards a method in which fluid jet-shaping nozzles are moved into a compressor stage through an opening in the compressor casing, pressurized fluid being sprayed through the nozzles against the blades while the compressor rotates relatively slowly about its rotor axis.
  • the invention also comprises a device for implementing the method.
  • the invention is aimed especially at an axial compressor it may advantageously be adapted for an axial turbine, and the invention also includes these. However, the following only refers to axial compressors.
  • axial compressors are cleaned of e.g. salt or other undesirable materials by spraying a detergent into the compressor inlet while the rotor is rotated by the starting motor.
  • a detergent is then drawn into the axial compressor and on through the turbine, and out at the discharge side of the turbine.
  • the detergent may be injected into the compressor air intake, as described in e.g. US patent no. 6 073 637, or through bores in the compressor casing between the rows of blades in the compressor, as shown in e.g. US patent application no. 2003/0133789.
  • This type of cleaning process is supposed to work by dissolving deposits and then transporting these to the outlet of the machine.
  • the detergent flow has only a minimal mechanical effect on the blade surfaces.
  • the detergent flows out of the machine along with a flushing medium and a significant amount of air. This only allows a certain amount of the detergent to be recovered, and thus it will flow to a nearby drain system or another undesirable recipient such as a municipal sewage system.
  • this type of detergent must satisfy- relatively strict environmental requirements, essentially preventing the use of effective detergents.
  • the object of the invention is to remedy or reduce at least one of the drawbacks of prior art.
  • Cleaning of an axial compressor or an axial turbine is performed by adding detergent via apertures in the compressor or turbine casing, the detergent being sprayed against the compressor or turbine blades under pressure, whereby the jet of detergent effects mechanical cleaning of the surface of the blade .
  • the pressure of the cleaning nozzles may vary between a few tens of bar up to several hundred bar.
  • the compressor is rotated in the opposite direction of the normal rotating direction. By so doing, dissolved contaminants will not be transported further on to a connected turbine but flows out of the axial compressor at the inlet of the axial compressor.
  • a low rotation speed will cause that each blade passes its respective cleaning nozzle at a relatively low speed, thus contributing to a thorough cleaning of the blade.
  • the detergent is collected after use, by means of e.g. a mantle enclosing the compressor inlet.
  • the detergent and entrained air is directed to a separator in which the detergent is separated from the air.
  • the method of the invention allows the blades to be subjected to both chemical and mechanical cleaning, thereby achieving significantly improved cleaning results compared with prior art. Due to the relatively slow rotation of the compressor in the opposite direction of the normal operating direction, the detergent is mixed only with a moderate amount of air, and the detergent is also transported to the compressor inlet, all of which makes it easy to collect and recover the detergent .
  • Fig. 1 shows an axial compressor in which it is provided cleaning nozzles connected to a cleaning aggregate
  • Fig. 2 shows the location of the cleaning nozzles relative to the rows of blades in the axial compressor.
  • reference number 1 denotes an axial compressor comprising a rotor 2 and a casing 4 (compressor casing) .
  • a plurality of rotor blades 6 are distributed in a row about the rotor 2, forming, in a manner that is known per se, together with a plurality of stator vanes 8 distributed in a row internally of the casing 4, a compressor stage 10, see Figure 2.
  • a plurality of compressor stages 10 are provided one after the other in the longitudinal direction of the axial compressor 1.
  • the casing 4 is provided with an opening, typically an inspection window 12, at each row of stator vanes 8.
  • the inspection windows 12 are arranged primarily to allow the probe of a borescope (not shown) to be inserted into the casing 4 for inspection of the rotor blades 6.
  • a nozzle tube 14 is moved in through the inspection window 12 , towards the rotor 2 in each compressor stage 10.
  • the nozzle tube 14 is provided with cleaning nozzles 16 designed so as to ensure that jets 18 of detergent from the cleaning nozzles 16 cover the longitudinal extent of the corresponding rotor blade 6, see Figure 2.
  • a nozzle tube 14 may be connected to other nozzle tubes 14 to form an array 20 of nozzles.
  • the array 20 of nozzles is connected to a supply pipe 22 via an array valve 24.
  • the number of arrays 20 of nozzles is adapted for the axial compressor in question.
  • the supply pipe 22 receives a sequential supply of detergent and rinse water from a feed pump 26.
  • the feed pump 26 is part of a cleaning aggregate 28.
  • the cleaning aggregate 28 comprises a carriage 30 provided with an air/liquid separator 32, a first receptacle 34 for used detergent and rinse water, a cleaning unit 36 of a type that is known per se, for used detergent, comprising filters (not shown) , a second receptacle 38 for detergent and a third receptacle 40 for rinse water.
  • the feed pump 26 receives detergent via a detergent pipe 42 and a detergent valve 44, and rinse water via a rinse water pipe 46 and a rinse water valve 48.
  • Used detergent and rinse water is passed to the air/liquid separator 32 by a blower 50 and a tubing connection 52 from a mantel 54 covering the inlet to the compressor 1.
  • the separated air is evacuated from the air/liquid separator 32 via an outlet 56, while liquid flows into the first receptacle 34.
  • the cleaning aggregate 28 is supplied with the required power via a control system (not shown) which also controls the array valves 24 plus the detergent valve 44 and the rinse water valve 48.
  • the nozzle, arrays 20, which must be adapted for the axial compressor 1 in question, must first be placed in the inspection windows 12.
  • the nozzle tubes 14 are arranged in a gap between two stator vanes 8, with their respective cleaning nozzles 16 directed at the adjacent rotor blade 6.
  • the mantle 54 is sealingly mounted about the compressor 1 inlet.
  • the rotor 2 is then slowly rotated in a manner that is known per se, in the opposite direction of the normal rotating direction, by means of equipment commonly used to rotate the rotor 2 during inspection.
  • This equipment is well known to a person skilled in the art and will not be described in any greater detail.
  • Pressurized detergent is pumped to the array valves 24 while the rotor 2 is rotated as described.
  • the array valves are opened one after the other in order to achieve efficient cleaning of the blades 6 and vanes 8, and also to ensure that any loosened deposits are transported out of the axial compressor 1.
  • the detergent valve 44 is closed, and then the rinse water valve 48 is opened.
  • the array valves 24 are again controlled in a certain sequence to achieve optimum flushing of the axial compressor 1.
  • Detergent, rinse water and entrained air all flow to the air/liquid separator 32 via the blower 50 and the tubing connection 52, in which separator 32 the liquid collects in the first receptacle 34.
  • the nozzle tube 14 is connected directly to the supply pipe 22 to allow the use of a low capacity feed pump 26.
  • the compressor stages 10 are cleaned sequentially.
  • purification of used detergent may be performed in a separate installation (not shown) .

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un procédé et un dispositif de nettoyage d'un compresseur axial (1), du détergent étant admis par des ouvertures (12) dans le carter de compresseur (4), et le détergent étant, par le biais de buses de nettoyage (16), pulvérisé au niveau de l'aube mobile (6) du compresseur axial sous pression, ce par quoi un jet (18) de détergent effectue le nettoyage mécanique de la surface de l'aube mobile (6).
PCT/NO2006/000089 2006-03-08 2006-03-08 Procede et dispositif de nettoyage d'un compresseur axial WO2007102738A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/NO2006/000089 WO2007102738A1 (fr) 2006-03-08 2006-03-08 Procede et dispositif de nettoyage d'un compresseur axial

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/NO2006/000089 WO2007102738A1 (fr) 2006-03-08 2006-03-08 Procede et dispositif de nettoyage d'un compresseur axial

Publications (1)

Publication Number Publication Date
WO2007102738A1 true WO2007102738A1 (fr) 2007-09-13

Family

ID=38475116

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NO2006/000089 WO2007102738A1 (fr) 2006-03-08 2006-03-08 Procede et dispositif de nettoyage d'un compresseur axial

Country Status (1)

Country Link
WO (1) WO2007102738A1 (fr)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2009115079A (ja) * 2007-10-09 2009-05-28 Gas Turbine Efficiency Sweden Ab ガスタービンコンプレッサの水洗浄装置と洗浄方法
EP1927408A3 (fr) * 2006-11-28 2009-12-02 Gas Turbine Efficiency Sweden AB Détection automatique et système et procédé de commande pour application de lavage haute pression et collecte appliquée au lavage à l'aérocompresseur
KR101207688B1 (ko) 2009-08-21 2012-12-03 가스 터빈 이피션시 스웨덴 에이비 압축기 물 세정 시스템
FR2979264A1 (fr) * 2011-08-30 2013-03-01 Snecma Procede de nettoyage des aubes d'un rotor interne d'un turbomoteur et organe de projection de pellets de glace seche correspondant.
WO2014084969A1 (fr) * 2012-11-29 2014-06-05 United Technologies Corporation Système de lavage de compresseur de moteur
KR101576132B1 (ko) * 2014-07-11 2015-12-09 서울대학교 산학협력단 터빈용 블레이드의 세정장치
WO2019129952A1 (fr) * 2017-12-29 2019-07-04 Safran Aircraft Engines Procede de demarrage de turbomachine par temps froid et systeme de demarrage de turbomachine
US20190203610A1 (en) * 2018-01-02 2019-07-04 General Electric Company In situ foam generation within a turbine engine
CN110050107A (zh) * 2016-10-14 2019-07-23 通用电气公司 燃气涡轮发动机清洗系统
US20200040763A1 (en) * 2016-10-14 2020-02-06 Peng Wang Gas turbine engine wash system
EP3805528A1 (fr) * 2019-10-11 2021-04-14 Rolls-Royce plc Système et procédé pour le nettoyage des canaux d'écoulement dans des moteurs à turbine à gaz
US11028727B2 (en) 2017-10-06 2021-06-08 General Electric Company Foaming nozzle of a cleaning system for turbine engines
US11053813B2 (en) 2017-04-18 2021-07-06 General Electric Company Turbine component cleaning system and method having detergent recovery and regeneration
CN113586529A (zh) * 2020-07-02 2021-11-02 中国航发常州兰翔机械有限责任公司 一种航空发动机两级热态清洗装置的工作方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1366727A1 (ru) * 1985-12-02 1988-01-15 Всесоюзный Научно-Исследовательский И Проектный Институт По Переработке Газа Способ очистки центробежного компрессора
US5899217A (en) * 1998-02-10 1999-05-04 Testman, Jr.; Frank L. Engine wash recovery system
US20030133789A1 (en) * 2002-01-17 2003-07-17 Bernhard Kuesters Axial compressor and method of cleaning an axial compressor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1366727A1 (ru) * 1985-12-02 1988-01-15 Всесоюзный Научно-Исследовательский И Проектный Институт По Переработке Газа Способ очистки центробежного компрессора
US5899217A (en) * 1998-02-10 1999-05-04 Testman, Jr.; Frank L. Engine wash recovery system
US20030133789A1 (en) * 2002-01-17 2003-07-17 Bernhard Kuesters Axial compressor and method of cleaning an axial compressor

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1927408A3 (fr) * 2006-11-28 2009-12-02 Gas Turbine Efficiency Sweden AB Détection automatique et système et procédé de commande pour application de lavage haute pression et collecte appliquée au lavage à l'aérocompresseur
EP2243562A1 (fr) * 2006-11-28 2010-10-27 Gas Turbine Efficiency Sweden AB Détection automatique et système et procédé de commande pour application de lavage haute pression et collecte appliquée au lavage à l'aérocompresseur
US8197609B2 (en) 2006-11-28 2012-06-12 Pratt & Whitney Line Maintenance Services, Inc. Automated detection and control system and method for high pressure water wash application and collection applied to aero compressor washing
US9162262B2 (en) 2006-11-28 2015-10-20 Ecoservices, Llc Automated detection and control system and method for high pressure water wash application and collection applied to aero compressor washing
JP2009115079A (ja) * 2007-10-09 2009-05-28 Gas Turbine Efficiency Sweden Ab ガスタービンコンプレッサの水洗浄装置と洗浄方法
KR101207688B1 (ko) 2009-08-21 2012-12-03 가스 터빈 이피션시 스웨덴 에이비 압축기 물 세정 시스템
FR2979264A1 (fr) * 2011-08-30 2013-03-01 Snecma Procede de nettoyage des aubes d'un rotor interne d'un turbomoteur et organe de projection de pellets de glace seche correspondant.
WO2014084969A1 (fr) * 2012-11-29 2014-06-05 United Technologies Corporation Système de lavage de compresseur de moteur
KR101576132B1 (ko) * 2014-07-11 2015-12-09 서울대학교 산학협력단 터빈용 블레이드의 세정장치
CN110050107A (zh) * 2016-10-14 2019-07-23 通用电气公司 燃气涡轮发动机清洗系统
US20200040763A1 (en) * 2016-10-14 2020-02-06 Peng Wang Gas turbine engine wash system
EP3510254A4 (fr) * 2016-10-14 2020-04-01 General Electric Company Système de lavage pour moteur à turbine à gaz
US11053813B2 (en) 2017-04-18 2021-07-06 General Electric Company Turbine component cleaning system and method having detergent recovery and regeneration
US11028727B2 (en) 2017-10-06 2021-06-08 General Electric Company Foaming nozzle of a cleaning system for turbine engines
WO2019129952A1 (fr) * 2017-12-29 2019-07-04 Safran Aircraft Engines Procede de demarrage de turbomachine par temps froid et systeme de demarrage de turbomachine
FR3076321A1 (fr) * 2017-12-29 2019-07-05 Safran Aircraft Engines Procede de demarrage de turbomachine par temps froid et systeme de demarrage de turbomachine
US11339683B2 (en) 2017-12-29 2022-05-24 Safran Aircraft Engines Method for starting a turbine engine in cold weather and system for starting a turbine engine
US20190203610A1 (en) * 2018-01-02 2019-07-04 General Electric Company In situ foam generation within a turbine engine
US10871082B2 (en) * 2018-01-02 2020-12-22 General Electric Company In situ foam generation within a turbine engine
US11702956B2 (en) 2018-01-02 2023-07-18 General Electric Company In situ foam generation within a turbine engine
EP3805528A1 (fr) * 2019-10-11 2021-04-14 Rolls-Royce plc Système et procédé pour le nettoyage des canaux d'écoulement dans des moteurs à turbine à gaz
US11519293B2 (en) 2019-10-11 2022-12-06 Rolls-Royce Plc Cleaning system and a method of cleaning
CN113586529A (zh) * 2020-07-02 2021-11-02 中国航发常州兰翔机械有限责任公司 一种航空发动机两级热态清洗装置的工作方法

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