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EP1970133A1 - Dispositif et procédé destinés au nettoyage du réacteur de base d'un turboréacteur - Google Patents

Dispositif et procédé destinés au nettoyage du réacteur de base d'un turboréacteur Download PDF

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Publication number
EP1970133A1
EP1970133A1 EP07005446A EP07005446A EP1970133A1 EP 1970133 A1 EP1970133 A1 EP 1970133A1 EP 07005446 A EP07005446 A EP 07005446A EP 07005446 A EP07005446 A EP 07005446A EP 1970133 A1 EP1970133 A1 EP 1970133A1
Authority
EP
European Patent Office
Prior art keywords
engine
fan
nozzles
nozzle device
cleaning
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.)
Withdrawn
Application number
EP07005446A
Other languages
German (de)
English (en)
Inventor
Sebastian Giljohann
Daniel Göbel
Michael Mensch
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.)
Lufthansa Technik AG
Original Assignee
Lufthansa Technik AG
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=38523401&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1970133(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Lufthansa Technik AG filed Critical Lufthansa Technik AG
Priority to EP07005446A priority Critical patent/EP1970133A1/fr
Priority to PCT/EP2008/001983 priority patent/WO2008113501A1/fr
Priority to MX2009005569A priority patent/MX2009005569A/es
Priority to AT08714267T priority patent/ATE453462T1/de
Priority to CN2008800015279A priority patent/CN101578143B/zh
Priority to EP08714267A priority patent/EP1993744B1/fr
Priority to BRPI0808879-9A priority patent/BRPI0808879A2/pt
Priority to ES08714267T priority patent/ES2338951T3/es
Priority to US12/302,682 priority patent/US8216392B2/en
Priority to AU2008228521A priority patent/AU2008228521B2/en
Priority to DE502008000281T priority patent/DE502008000281D1/de
Publication of EP1970133A1 publication Critical patent/EP1970133A1/fr
Priority to HK09103785.4A priority patent/HK1128257A1/xx
Priority to US12/769,514 priority patent/US10539040B2/en
Priority to US15/218,669 priority patent/US10634004B2/en
Withdrawn 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B08—CLEANING
    • B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
    • B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
    • B08B3/02—Cleaning by the force of jets or sprays
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B08—CLEANING
    • B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
    • B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
    • B08B3/04—Cleaning involving contact with liquid
    • B08B3/10—Cleaning involving contact with liquid with additional treatment of the liquid or of the object being cleaned, e.g. by heat, by electricity or by vibration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B08—CLEANING
    • B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
    • B08B9/00—Cleaning hollow articles by methods or apparatus specially adapted thereto
    • B08B9/02—Cleaning pipes or tubes or systems of pipes or tubes
    • B08B9/027—Cleaning the internal surfaces; Removal of blockages
    • B08B9/032—Cleaning the internal surfaces; Removal of blockages by the mechanical action of a moving fluid, e.g. by flushing
    • B08B9/0321—Cleaning the internal surfaces; Removal of blockages by the mechanical action of a moving fluid, e.g. by flushing using pressurised, pulsating or purging fluid
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines

Definitions

  • the invention relates to a device, an arrangement and a method for cleaning the core engine of a jet engine.
  • Jet engines of commercial subsonic aircraft are nowadays predominantly so-called turbofan jet engines.
  • Such a turbofan engine has a so-called core engine, in which the actual combustion process of kerosene takes place.
  • the core engine has in a known manner one or more compressor stages, a combustion chamber, and one or more turbine stages in which the hot combustion gases give off part of their mechanical energy.
  • this mechanical energy is required for driving the compressor stages, and on the other hand, a so-called turbofan arranged upstream of the core engine is driven, which usually has a considerably larger diameter than the core engine and a considerable part of the air flowing through the engine as a whole as a so-called mantle or side airflow to flow past the Core Engine.
  • the turbofan brings about this shell air flow on a considerable part of the thrust of the engine, also ensures the high Mantel Kunststoffstromteil for better environmental performance of the engine, in particular a better efficiency at subsonic speeds, as well An improved noise reduction of the hot exhaust gas flow of the Core Engine.
  • Jet engines are contaminated during operation by combustion residues of the core engine as well as air pollutants sucked in with the combustion or shell air, such as dust, insects, salt mist or other environmental contaminants.
  • these impurities also form a coating on the rotor and / or stator blades of the compressor of the core engine, which impairs the surface quality and thus ultimately the thermodynamic efficiency of the engine.
  • the invention has for its object to provide a device, a method and an arrangement of the type mentioned, which allow an effective and efficient cleaning of the core engine of a jet engine.
  • the device according to the invention has a supply device, which provides cleaning medium, a nozzle device, which is designed to introduce the cleaning medium into the core engine, and a line connection between the supply device and the nozzle device.
  • the nozzle device comprises means for non-rotatable connection with the shaft of the fan of the jet engine, and that a Rotary coupling between the nozzle device and the line connection is provided.
  • jet engine means any mobile gas turbine for aerospace applications.
  • the term refers in particular to turbofan engines in which the actual gas turbine forms a so-called core engine and upstream of the core engine is arranged a larger diameter turbofan, which generates a fan airflow around the core engine.
  • core engine refers to the actual gas turbine of the jet engine, in which the combustion process of the fuel, in particular kerosene takes place.
  • Such a core engine typically includes one or more compressor stages, a combustor, and one or more turbine stages driven by the hot combustion gases.
  • the supply device provides cleaning medium available (for example, in one or more tanks) and can be provided with operating and drive devices, pumps, energy storage or the like. It is preferably designed as a mobile, in particular mobile unit.
  • the nozzle device has one or more nozzles for the cleaning medium and means explained below in more detail for the rotationally fixed connection of this nozzle device and thus of the nozzles with the shaft of the fan of the jet engine.
  • these nozzles are not stationary in the region of the inlet of the jet engine are arranged, but rotatably connected to the wave of the fan and thus can rotate with a slow spin of the engine without injecting kerosene (the so-called dry-cranking) with the fan.
  • the supply device and the nozzle device are connected to one another via a line connection.
  • This line connection is used in particular to supply the (preferably pressurized and possibly heated) cleaning medium to the nozzles of the nozzle device.
  • the line connection is preferably flexible and may in particular have a possibly pressure-resistant hose.
  • the line connection is connected by means of a rotary coupling to the nozzle device.
  • the term rotary joint is to be understood functionally and refers to any device which is suitable for producing a sufficiently stable, preferably pressure-resistant and liquid-tight connection between the stationary part of the line connection and the fan device co-rotating with the fan.
  • the purpose of the rotary joint is to direct the cleaning medium from the stationary supply device into the co-rotating nozzle device and then to let it out of the nozzles.
  • the invention enables a targeted cleaning of the core engine.
  • the dry-cranking nozzles spray the core engine inlet evenly over the entire circumference.
  • the co-rotating arrangement of the nozzles allows a targeted introduction of the cleaning medium in the flow direction behind the blades (blades) of the fan and thus an immediate brushing the core engine without being affected by the flow direction before arranged turbofan.
  • a substantial part of the cleaning medium strikes the blades of the fan and therefore can not or at least not directly contribute to the cleaning of the core engine.
  • the invention has recognized that the targeted cleaning of the core engine is essential for the desired improvement of the thermodynamic efficiency.
  • the invention has also recognized that a possibly desired additional cleaning of fan blades can be achieved much easier by an additional manual cleaning with hose and brush.
  • Brushing the fan blades as provided in the prior art, can not remove a significant portion of the impurities of the fan blades, as they sit increasingly on the back (pressure side) of the fan blades.
  • cleaning medium there removed dirt and in particular in the area of the blade root leached lubricant are entered into the core engine and pollute them in addition.
  • the mass distribution of the nozzle device is preferably rotationally symmetrical about its axis of rotation.
  • the rotary coupling preferably sits essentially centrally on the axis of rotation of the device according to the invention in the mounted state.
  • the nozzle device has at least two or more nozzles, which are preferably distributed rotationally symmetrically about the axis of rotation.
  • the outlet opening of the nozzles is preferably in the direction away from the rotary coupling axial end portion of the nozzle device arranged.
  • the rotary coupling is preferably located in the front region of the nozzle device, ie in that region which, in the mounted state, faces upstream, ie away from the inlet of the jet engine.
  • the outlet opening of the nozzles is accordingly provided in the axial end region of the nozzle device pointing away from it, ie in the assembled state in the current-repellent end region.
  • nozzles to be mounted on the shaft of the fan of a turbofan engine during assembly either through the interstices of the fan blades, so that they are located immediately in front of the core engine, or at least to be targeted so that they pass through Gap spaces between fanblades directly onto the core engine.
  • the nozzles are preferably flat jet nozzles, but other shapes such as round jet nozzles or a combination of different nozzles may also be used.
  • the beam plane is preferably oriented radially, i. it is spanned by two axes, one of which points in the radial direction. In this way, the rotating flat jet can particularly effectively cover substantially the entire area of the inlet of the core engine.
  • the beam plane includes an angle of attack with the axis of rotation.
  • This means that the beam direction is not parallel to the axis of rotation, but forms an angle with this axis.
  • the beam direction deviates at this angle from the axial direction. It is preferable if this angle depends on the angle of attack of the front compressor blades of the core engine. As a rule, these are stator blades which, with a suitable setting of the beam angle to the setting angle of the flat jet can be partially passed through, so that it comes to a more effective cleaning of the behind it arranged parts of the Core Engine.
  • the means for non-rotatable connection with the shaft of the fan of the jet engine preferably comprise fastening means for attachment to the fan blades such as suitably formed hooks, with which the nozzle means at the trailing edge (downstream) of the fan blades can be hooked.
  • the nozzle device may have a device for substantially positive engagement with the shaft of the fan for rotationally fixed fixation with the shaft of the fan.
  • Turbofan engines generally have a conically curved hub on the upstream shaft end of the turbofan shaft to improve the flow characteristics of the air.
  • this hub On this hub, the appropriate means for non-rotatable connection can be placed.
  • “Substantially positive” in this context means that the shape of the shaft hub is used for the intended positioning of the nozzle device and for fixing in the desired position. It does not mean that the entire surface of the shaft hub must be positively enclosed.
  • the device may have one or more ring parts, with which it can be placed on the shaft hub. In a plurality of ring parts, these have a different diameter, adapted is at the diameter of the shaft hub in the corresponding areas. For example, two axially spaced rings of different diameters can be provided, with which the nozzle device is positioned and centered on the shaft hub.
  • Tensioning cables can preferably be provided for further fixing.
  • the nozzle device can be centered by means of the ring parts on the shaft hub of the fan and then tensioned with tension cables which are fixed to the trailing edge of the fan blades.
  • spring means for biasing the tension cables may be provided so that the nozzle device is pressed with a defined force to the shaft hub.
  • the tensioning cables are preferably fastened (for example by means of hooks) to the fan blades, preferably at the rear edge thereof.
  • the supply device for the cleaning medium preferably has at least one storage tank for cleaning medium and at least one pump for pressurizing the nozzle device with cleaning medium.
  • the storage tank may have a heating device to provide tempered cleaning medium available.
  • the supply device has at least two storage tanks, from which the nozzle device can be fed optionally. This has the advantage that after a cleaning process in a cleaning tank freshly filled cleaning medium can be heated to the desired temperature, while at the same time from the second cleaning tank another cleaning process is fed.
  • the cleaning medium used may preferably be a liquid, in particular an aqueous liquid, or a dispersion of a liquid in a gaseous medium, in particular air.
  • a aqueous solution is used, which is atomized on leaving the nozzles to form an aqueous dispersion in air.
  • the nozzle device is rotatably connected to the shaft of the fan of the jet engine.
  • the axes of rotation of the fan of the jet engine and the nozzle device are arranged substantially concentric.
  • the axis of rotation of the nozzle means is that axis about which the nozzles rotate concentrically during operation.
  • the radial distance of the nozzles of the nozzle device from the common axis of rotation of the jet engine and the device is such that these nozzles sweep the input of the core engine.
  • the exit orifices of the nozzles are aligned behind the plane of the turbofan or so in front of or between the fanblades, allowing for substantially unhindered passage therethrough.
  • the angle of incidence of the jet plane of the nozzles with the axis of rotation is adapted to the angle of attack of the front engine blade in the flow direction of the engine. In this way, the cleaning effect is also improved in the back of the core engine.
  • the dry-cranking or rotation of the jet engine during the cleaning process is preferably carried out at a speed of 50 to 500 min -1 , preferably 100 to 300 min -1 , more preferably 120 to 250 min -1 . Particularly preferred is a speed between 150 and 250 min -1 .
  • the cleaning can also take place in the idling mode of the engine, the speed is because preferably 500 to 1500 min -1 .
  • the cleaning medium used is preferably a dispersion of a liquid in a gaseous medium.
  • This dispersion can be prepared before the nozzle outlet opening, for example by the addition of gaseous medium such as air to a cleaning liquid.
  • gaseous medium such as air
  • This dispersion or aerosol is then carried through the core engine.
  • the cleaning medium (or the liquid portion of the aerosol) is preferably further in the range of 200 to 100 ° C, more preferably 30 to 80 ° C preferably tempered at 50 to 70 ° C.
  • the pressure at which the cleaning medium is discharged at the nozzle opening is preferably in the range from 20 to 100 bar, more preferably from 30 to 80 bar, more preferably from 50 to 70 bar.
  • the liquid cleaning medium at the nozzle opening is preferably torn into droplets whose average droplet size is 50 to 500 ⁇ m, more preferably 100 to 300 ⁇ m, more preferably 150 to 250 ⁇ m.
  • the throughput of liquid cleaning medium is preferably between 10 and 200 l / min, more preferably 20 to 150 l / min, more preferably 20 to 100 l / min, particularly preferably between 20 and 60 l / min.
  • the duration of the cleaning process is preferably 1 to 15 minutes, more preferably 2 to 10 minutes, more preferably 3 to 7 minutes.
  • the tank or each tank for cleaning medium of the supply device may, for example, have a volume of 400 l. This volume allows, for example, a 5 min. Cleaning with a throughput of 80 1 / min.
  • the nozzle device has two ring elements 1, 2, by means of which the nozzle device is placed on a shaft hub 3 of the fan of a jet engine (see Fig. 2 and 3 ).
  • the ring elements 1, 2 enclose the shaft hub 3 in a substantially positive fit.
  • the two ring elements 1, 2 are connected to each other by radial struts 4.
  • a generally designated 5 rotary coupling is arranged at the current-carrying tip of the nozzle device (with respect to the flow direction of the engine). From this rotary coupling extending two radially outwardly leading pressure lines 6, the two flat-jet nozzles 7 feed with cleaning medium.
  • the two pressure lines 6 via radial channels 8 and an axial channel 9 of the rotary joint 5 are in fluid communication with a supply line 10 which connects the rotary coupling with the supply unit, not shown in the drawing.
  • the pressure lines 6 are fixed at the intersection points with the ring elements 1, 2 at these ring elements and thus part of the support structure of the entire nozzle device.
  • tensioning cables are provided, which are hooked by means of hooks 12 at the trailing edges of the fan blade.
  • tensioning cables 11 are guided via attached to the rotary coupling tensioning cable guides 17 to the rotary coupling and fastened there to an axially displaceable clamping ring 13.
  • Compression springs 14 are based on an annular shoulder 15 of the rotary coupling and bring on the clamping ring 13 in a direction away from the annular shoulder 15 acting force. In the fitted state, the compression springs 14 bring a tension on the tensioning cables 11 and thus ensure a fixation of the nozzle device with the hub of the fan.
  • the nozzle device in the particular of the Figures 2 and 3 recognizable manner placed on the shaft hub of the fan and fixed to the fan blades by means of the hook 12.
  • the engine is rotated (dry-cranking).
  • the rotary joint 5 and the pressure lines 6, the flat jet nozzles 7 are fed with cleaning medium from the supply device, not shown. This cleaning medium sweeps the core engine inlet over its entire circumference, cleaning it out.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Nozzles (AREA)
  • Cleaning In General (AREA)
  • Cleaning By Liquid Or Steam (AREA)
EP07005446A 2007-03-16 2007-03-16 Dispositif et procédé destinés au nettoyage du réacteur de base d'un turboréacteur Withdrawn EP1970133A1 (fr)

Priority Applications (14)

Application Number Priority Date Filing Date Title
EP07005446A EP1970133A1 (fr) 2007-03-16 2007-03-16 Dispositif et procédé destinés au nettoyage du réacteur de base d'un turboréacteur
DE502008000281T DE502008000281D1 (de) 2007-03-16 2008-03-12 Vorrichtung und verfahren zum reinigen der core engine eines strahltriebwerks
BRPI0808879-9A BRPI0808879A2 (pt) 2007-03-16 2008-03-12 Dispositivo e método de limpeza do motor central de um motor a jato
US12/302,682 US8216392B2 (en) 2007-03-16 2008-03-12 Device and method for cleaning the core engine of a jet power plant
AT08714267T ATE453462T1 (de) 2007-03-16 2008-03-12 Vorrichtung und verfahren zum reinigen der core engine eines strahltriebwerks
CN2008800015279A CN101578143B (zh) 2007-03-16 2008-03-12 用于清洗喷气发动机的核心机的装置和方法
EP08714267A EP1993744B1 (fr) 2007-03-16 2008-03-12 Dispositif et procédé pour nettoyer le moteur central d'un moteur à réaction
PCT/EP2008/001983 WO2008113501A1 (fr) 2007-03-16 2008-03-12 Dispositif et procédé pour le nettoyage du moteur central d'un moteur à réaction
ES08714267T ES2338951T3 (es) 2007-03-16 2008-03-12 Dispositivo y procedimiento para la limpieza del nucleo motriz de un motor de reaccion.
MX2009005569A MX2009005569A (es) 2007-03-16 2008-03-12 Dispositivo y metodo para limpiar el nucleo del motor de la turbina de un motor a reaccion.
AU2008228521A AU2008228521B2 (en) 2007-03-16 2008-03-12 Device and method for cleaning the core engine of a jet engine
HK09103785.4A HK1128257A1 (en) 2007-03-16 2009-04-23 Device and method for cleaning the core engine of a jet engine
US12/769,514 US10539040B2 (en) 2007-03-16 2010-04-28 Device and method for cleaning the core engine of a jet engine
US15/218,669 US10634004B2 (en) 2007-03-16 2016-07-25 Device and method for cleaning the core engine of a jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07005446A EP1970133A1 (fr) 2007-03-16 2007-03-16 Dispositif et procédé destinés au nettoyage du réacteur de base d'un turboréacteur

Publications (1)

Publication Number Publication Date
EP1970133A1 true EP1970133A1 (fr) 2008-09-17

Family

ID=38523401

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07005446A Withdrawn EP1970133A1 (fr) 2007-03-16 2007-03-16 Dispositif et procédé destinés au nettoyage du réacteur de base d'un turboréacteur
EP08714267A Active EP1993744B1 (fr) 2007-03-16 2008-03-12 Dispositif et procédé pour nettoyer le moteur central d'un moteur à réaction

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08714267A Active EP1993744B1 (fr) 2007-03-16 2008-03-12 Dispositif et procédé pour nettoyer le moteur central d'un moteur à réaction

Country Status (11)

Country Link
US (3) US8216392B2 (fr)
EP (2) EP1970133A1 (fr)
CN (1) CN101578143B (fr)
AT (1) ATE453462T1 (fr)
AU (1) AU2008228521B2 (fr)
BR (1) BRPI0808879A2 (fr)
DE (1) DE502008000281D1 (fr)
ES (1) ES2338951T3 (fr)
HK (1) HK1128257A1 (fr)
MX (1) MX2009005569A (fr)
WO (1) WO2008113501A1 (fr)

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WO2009132847A1 (fr) * 2008-04-30 2009-11-05 Lufthansa Technik Ag Procédé et système pour nettoyer un moteur à réaction au moyen de dioxyde de carbone solide
DE102008014607A1 (de) 2008-03-17 2010-02-25 Lufthansa Technik Ag Vorrichtung zum Auffangen von Waschflüssigkeit aus einer Strahltriebwerkswäsche
DE202013005524U1 (de) 2013-02-19 2014-05-20 Lufthansa Technik Ag Vorrichtung zum Reinigen der Core Engine eines Strahltriebwerks
ITMI20132042A1 (it) * 2013-12-06 2015-06-07 Nuovo Pignone Srl Metodi per lavare motori con turbina a gas e motori con turbina a gas
DE102014206084A1 (de) 2014-03-31 2015-10-01 Lufthansa Technik Ag Vorrichtung und Verfahren zur Triebwerksreinigung
US10539040B2 (en) 2007-03-16 2020-01-21 Lufthansa Technik Ag Device and method for cleaning the core engine of a jet engine
US10669884B2 (en) 2013-12-06 2020-06-02 Nuovo Pignone Srl Washing nozzles and gas turbine engines

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HK1128257A1 (en) 2009-10-23
US20160333732A1 (en) 2016-11-17
EP1993744B1 (fr) 2009-12-30
CN101578143B (zh) 2011-08-31
US20110146729A1 (en) 2011-06-23
US8216392B2 (en) 2012-07-10
ATE453462T1 (de) 2010-01-15
EP1993744A1 (fr) 2008-11-26
US10634004B2 (en) 2020-04-28
ES2338951T3 (es) 2010-05-13
US10539040B2 (en) 2020-01-21
WO2008113501A1 (fr) 2008-09-25
AU2008228521A1 (en) 2008-09-25
US20100200023A1 (en) 2010-08-12
BRPI0808879A2 (pt) 2014-08-26
AU2008228521B2 (en) 2011-02-24
MX2009005569A (es) 2009-08-27
CN101578143A (zh) 2009-11-11

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