WO2020030516A1 - Procédé, dispositif et système permettant le nettoyage du moteur central d'un moteur à réaction - Google Patents

Procédé, dispositif et système permettant le nettoyage du moteur central d'un moteur à réaction Download PDF

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Publication number
WO2020030516A1
WO2020030516A1 PCT/EP2019/070744 EP2019070744W WO2020030516A1 WO 2020030516 A1 WO2020030516 A1 WO 2020030516A1 EP 2019070744 W EP2019070744 W EP 2019070744W WO 2020030516 A1 WO2020030516 A1 WO 2020030516A1
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WO
WIPO (PCT)
Prior art keywords
nozzle
nozzles
engine
cleaning medium
jet
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/EP2019/070744
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German (de)
English (en)
Inventor
Holger Stefan APPEL
Dirk DEJA
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
Application filed by Lufthansa Technik AG filed Critical Lufthansa Technik AG
Publication of WO2020030516A1 publication Critical patent/WO2020030516A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • B08B9/00—Cleaning hollow articles by methods or apparatus specially adapted thereto
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/30—Cleaning aircraft
    • 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
    • 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
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines

Definitions

  • the invention relates to a method, a device and an arrangement for cleaning the core engine of a jet engine.
  • Jet engines testify to commercial subsonic air traffic today are predominantly so-called turbofan jet engines.
  • Such a turbofan engine has a so-called core engine, in which the actual combustion process of the kerosene takes place.
  • the core engine has one or more compressor stages, a combustion chamber, and one or more turbine stages, in which the hot combustion gases emit part of their mechanical energy.
  • This mechanical energy is required on the one hand to drive the compressor stages, and on the other hand a so-called turbofan is driven upstream of the core engine, which generally has a considerably larger diameter than the core engine and a significant part of it Air flowing through the engine as a so-called sheath or secondary air flow past the core engine.
  • the turbofan provides a significant part of the thrust output of the engine via this jacket air flow, and the high jacket air flow share also ensures better environmental compatibility of the engine, in particular better efficiency at subsonic speeds, as well improved noise insulation of the hot exhaust gas flow from the core engine.
  • Jet engines are contaminated in operation by combustion residues of the core engine as well as air pollutants drawn in with the combustion or jacket air, such as dust, insects, salt spray or other environmental contaminants. These impurities in particular also form a coating on the rotor and / or stator blades of the compressor of the core engine which affects the surface quality and thus ultimately the thermodynamic efficiency of the engine.
  • WO 2008/113501 A1 discloses a method and a device of the type mentioned at the beginning.
  • the invention has for its object to provide a method, a device and an arrangement of the type mentioned that enable an effective and efficient cleaning of the core engine of a jet engine.
  • this object is achieved in that the liquid cleaning medium is discharged from the nozzle device at a pressure of less than 20 bar.
  • jet engine describes any mobile gas turbine for aviation applications.
  • the term in particular denotes turbofan engines in which the actual gas turbine forms a so-called core engine and upstream of the core Engine is arranged a turbofan larger in diameter, which generates a jacket air flow around the core engine.
  • core engine describes 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 usually has one or more compressor stages, a combustion chamber and one or more turbine stages that are driven by the hot combustion gases.
  • the nozzle device has one or more nozzles for the cleaning medium. As explained in more detail below, it preferably has means for the rotationally fixed connection of this nozzle device and thus of the nozzles to the shaft of the fan of the jet engine.
  • liquid cleaning medium Water or an aqueous solution is preferably used as the liquid cleaning medium.
  • the liquid cleaning medium can preferably be applied in dispersed form with a gaseous medium.
  • the liquid cleaning medium is applied from the nozzle device or its nozzles at a pressure of less than 20 bar. This means that the liquid cleaning medium is fed to these nozzles at a pressure of less than 20 bar.
  • the invention has recognized that, surprisingly, the application of liquid cleaning medium with a low pressure according to the invention enables effective cleaning with low consumption of cleaning medium.
  • the cleaning medium is introduced into the engine under high pressure. This was deemed necessary, on the one hand to support cleaning by the kinetic effect of the impact and on the other hand to promote the cleaning medium into the engine with sufficient speed.
  • the present invention has recognized that this prior art approach leads to the fact that, on the one hand, the kinetic energy is largely lost on impact on the fan blades or the first stage of the core engine and, on the other hand, the cleaning medium is not distributed sufficiently finely, so that there is insufficient wetting of the surfaces to be cleaned. This requires the use of relatively large volumes for adequate cleaning.
  • the introduction according to the invention with low pressure allows a finer distribution of the medium even before impacting on the first surface to be cleaned and causes better wetting of the surfaces with lower liquid volumes.
  • the invention also recognized that the air flow induced by the engine during cleaning according to the invention (for example caused by the so-called dry cranking) is sufficient to carry the liquid cleaning medium through the entire engine without causing a high kinetic energy of the cleaning medium in front of the engine.
  • the pressure is preferably between 0.5 and less than 20 bar, more preferably between 0.5 and 15 bar, more preferably 0.5 and 10 bar, further preferably 0.5 and 6 bar. With this low pressure, an effective one Achieve cleaning using small amounts of liquid.
  • the throughput of liquid cleaning medium in the process according to the invention is preferably 1 to 25 1 / min, more preferably 1 to 10 1 / min.
  • the outlet openings of the nozzles are sufficiently spaced from the engine so that the escaping liquid can be finely distributed behind the nozzles.
  • the outlet openings of the nozzles are preferably at a distance of 1 to 25 cm, preferably 4 to 15 cm, from the inlet guide vanes of the first stator stage in the axial direction of the engine.
  • the nozzles are preferably designed as flat jet nozzles, hollow cone nozzles or full jet nozzles. Hollow cone nozzles achieve a good cleaning effect with low pressure and low fluid consumption.
  • Cone nozzles have an essentially rotationally symmetrical spray jet, which has the shape of a hollow cone (hollow cone nozzles) or full cone (full cone nozzles).
  • the main exit direction corresponds to the axis of symmetry of the cone.
  • Flat jet nozzles have a flat spray jet, which has a substantially larger spray angle or opening angle in a first spatial direction perpendicular to the main outlet direction than in a second spatial direction perpendicular to the main outlet direction and the first spatial direction.
  • the small (acute) opening angle can be, for example, 1 ° to 5 °.
  • the full cone nozzles are preferred.
  • the invention has recognized that the combination of flat jet nozzles and cone nozzles, in particular full cone nozzles, significantly improves the cleaning performance in the core engine.
  • Flat jet nozzles ensure good cleaning performance in the front (upstream) compressor area.
  • Cone nozzles result in better cleaning in the rear (downstream) area of the core engine, since under otherwise identical operating conditions (supply quantity and pressure of the cleaning medium) they atomize liquid cleaning medium more finely and allow it to escape more slowly. In this way, the cleaning medium can better follow the flow through the core engine and penetrate deeper as finely divided droplets.
  • the method according to the invention preferably uses at least one, preferably two flat jet nozzles and full cone nozzles.
  • the combination of two flat jet nozzles and two full cone nozzles results in particularly good cleaning performance.
  • the jet axis of the nozzles includes an angle of attack with the axis of rotation of the engine.
  • This means that the beam direction is not parallel to the axis of rotation, but includes an angle with this axis.
  • the beam direction deviates from the axial direction by this angle. It is preferred 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 or inlet guide vanes that with a suitable setting of the jet angle to their setting angle can be partially crossed out, so that there is a more effective cleaning of the parts of the core engine arranged behind it.
  • each nozzle has a spray angle of 20 ° to 120 °, preferably 60 ° to 90 °.
  • spray angle denotes the largest opening angle of the spray cone or spray fan.
  • the jet axis of the nozzles includes an angle of attack with the axis of rotation, which is -45 to + 45 °, preferably -5 to 30 °.
  • a negative sign of the angle denotes a main exit direction pointing away from the axis of rotation.
  • a positive sign of the angle denotes a main exit direction pointing towards the axis of rotation, which is usually preferred.
  • These are angles that enable common jet engines to allow the cleaning medium to penetrate as deep as possible into the core engine.
  • a plurality of nozzles can also include different angles with the axis of rotation from the mentioned areas.
  • some of the nozzles may include a relatively small angle with the axis of rotation. This flat angle allows a relatively deep penetration into the core engine; there are minimal losses at the inner and outer compressor limits.
  • the outlet openings of the nozzles preferably have a distance from the inlet plane of the inlet guide vanes of the core engine of 1 to 25 cm, preferably 4 to 15 cm.
  • the invention has recognized that the choice of this distance can make a significant contribution to ensuring that the spray jet reaches the desired degree of distribution or the desired droplet size before entering the core engine, so that on the one hand the complete width and height of the inlet opening or the Inlet Guide Vanes of the core engine can be painted over and on the other hand the entry occurs with the desired degree of distribution or degree of division, so that the desired cleaning effect occurs.
  • the combination of this distance range with the preferred ranges of the angle defined above is particularly advantageous.
  • the distance of the nozzles from the inlet plane of the inlet guide vanes is selected within the range mentioned in such a way that the inlet guide vanes at the given opening angle (spray angle)
  • Spray cones are recorded over the entire surface.
  • the central axis of the spray cone is preferably essentially centered on the inlet guide vanes.
  • the main outlet direction of each nozzle with the chord of the inlet guide vanes of the core engine forms an angle ⁇ of -75 ° to 75 °, preferably - 35 ° to 35 °.
  • This adjustment of the main outlet direction relative to the chord of the Inlet Guide Vanes allows the spray to pass through the front area or the front compressor stages of the core engine more easily.
  • a corresponding angle can be defined based on the axis of rotation instead of the chord. For example, with the engine model CF6-50, an angle ⁇ of 21 in relation to the chord is preferred, this corresponds to an angle of 0 ° in relation to the axis of rotation.
  • the average drop size of the liquid cleaning medium applied is preferably 0.01 to 0.5 mm, preferably 0.01 to 0.15 mm. This fine distribution allows the surfaces to be effectively wetted with small amounts of liquid.
  • the nozzle device preferably has at least one two-substance nozzle which is fed with liquid cleaning medium and a gas.
  • the gas can be used to separate the liquid better and more finely, so the use of a two-substance nozzle makes it easier to apply a fine dispersion of the liquid cleaning medium in gas.
  • a suitable pressure of the gas when the two-component nozzle is applied is preferably 20 bar or less, more preferably 0.4 to 20 bar, more preferably 0.4 to 9 bar. It is therefore in a range similar to the preferred pressure of the liquid cleaning medium.
  • the method according to the invention is preferably carried out when the jet engine is dry-cranked or rotated. This is preferably done at a speed of 50 to 500 min -1 , preferably 100 to 300 min -1 , more preferably 120 to 250 min l. A speed between 150 and 250 min -1 is particularly preferred.
  • the cleaning can also take place in idle mode of the engine, the speed is then preferably 500 to 1,500 min -1 .
  • the duration of the cleaning process is preferably 1 to 15 minutes, more preferably 2 to 10 minutes, more preferably 3 to 7 minutes.
  • Another object of the invention is a device for performing the method according to the invention in the embodiment with two-substance nozzles.
  • This device has a nozzle device with at least one nozzle which is designed for introducing cleaning medium into a jet engine, furthermore has means for rotationally fixed connection to the shaft of the turbofan of a jet engine, and a rotary coupling to which a feed line can be closed.
  • a nozzle device with at least one nozzle which is designed for introducing cleaning medium into a jet engine, furthermore has means for rotationally fixed connection to the shaft of the turbofan of a jet engine, and a rotary coupling to which a feed line can be closed.
  • a device is known from WO 2008/113501 A1.
  • the nozzle or the nozzles is / are designed as a two-substance nozzle, that the rotary coupling is designed to connect two supply lines for liquid cleaning medium and gas, and that separate line connections for liquid cleaning medium and gas from the nozzle-side outlet of the rotary coupling the inlet of the at least one nozzle are provided.
  • the device allows the inventive method to be carried out in the advantageous variant in which the liquid cleaning medium is additionally finely dispersed by a gas.
  • the device can have a supply device.
  • the supply device provides cleaning medium (for example in one or more tanks) and can be equipped with operating and drive devices, pumps, Energy storage or the like may be provided. It is preferably designed as a mobile, in particular mobile unit.
  • the separate line connections for liquid cleaning medium and gas from the nozzle-side outlet of the rotary coupling to the inlet of the at least one nozzle are designed as a concentric pipe-in-pipe line. This allows a stable construction of the device and is easily practicable due to the relatively small volumes of liquid cleaning medium required.
  • the device according to the invention can be supplied with liquid and compressed gas from external sources.
  • it can have a compressed air connection and, if appropriate, suitable pressure reducers. If liquid can be supplied from an external supply, this supply may already have been tempered.
  • liquid and / or gas can be stored or generated locally (compressed air).
  • the device can have a pressure accumulator for gas.
  • This can have, for example, a volume of 1 to 50 l and a pressure which is in the range of the intended feed pressure of the nozzles. The pressure therefore preferably does not exceed 20 bar.
  • a storage tank for liquid cleaning medium according to the invention can have a volume of 50 to 250 1, preferably 50 to 100 1.
  • Another object of the invention is an arrangement of a jet engine and a device according to the invention attached to it for cleaning the core engine, as described above. This arrangement has the following features: a. the nozzle device is rotatably connected to the shaft of the fan of the jet engine; b. the axes of rotation of the fan of the jet engine and the nozzle device are arranged essentially concentrically; c. the outlet openings of the nozzles (7) have a distance of at least 5 cm from the inlet guide vanes of the first stator stage in the axial direction of the engine.
  • these nozzles are not arranged in a stationary manner in the area of the jet engine inlet, but are non-rotatably connected to the shaft of the fan and thus when the engine is turned slowly without injecting kerosene (the so-called dry cranking). can rotate 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 (before preferably under pressure and possibly heated) cleaning medium to the nozzles of the nozzle device.
  • the line connection is preferably flexible and in particular may have a pressure-resistant hose.
  • the line connection is connected to the nozzle device by means of a rotary coupling.
  • the term rotary coupling is to be understood functionally and refers to any device that is suitable for producing a sufficiently stable, preferably pressure-resistant and liquid-tight connection between the stationary part of the line connection and the nozzle device rotating with the fan. The purpose of the rotary coupling is to guide the cleaning medium from the stationary supply device into the rotating nozzle device and then to let it exit from the nozzles.
  • the mass distribution of the nozzle device is preferably rotationally symmetrical about its axis of rotation. In this way, no significant additional imbalance is introduced when the nozzle device rotates as well.
  • the rotary coupling preferably sits essentially centrally on the axis of rotation of the device according to the invention in the assembled state.
  • the nozzle device preferably 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 arranged in the axial end region of the nozzle device pointing away from the rotary coupling.
  • the rotary coupling is located before in the front area of the nozzle device, ie in the area which, in the assembled state, points upstream, that is to say away from the inlet of the jet engine.
  • the outlet opening of the nozzles is accordingly hen in the axially pointing away end region of the nozzle device, ie in the assembled state in the current-repellent end region.
  • This arrangement enables the nozzles the assembly on the shaft of the fan of a turbofan engine either through the gaps between the fan blades so that they are arranged directly in front of the core engine, or at least specifically so that they pass through the gaps between the fan blades Radiate fan blades through directly to the core engine.
  • the arrangement is accordingly preferably designed such that the nozzles are arranged with jet angles and distances as described above in the context of the method according to the invention.
  • Fig. 1 is a view of a nozzle according to the invention
  • Fig. 2 shows a section through the plane B-B of FIG. 1 of a nozzle device which is placed on the shaft nose of a fan;
  • Fig. 3 shows a section through the plane A-A of FIG. 1 of a nozzle device which is placed on the shaft nose of a fan;
  • FIG. 4 Schematic of the arrangement of the nozzles behind the
  • Fig. 5 shows schematically the possible angles of attack of the Dü sen.
  • the nozzle device has two ring elements 1, 2, with the aid of which the nozzle device is placed on a shaft hub 3 of the fan of a jet engine (see FIGS. 2 and 3).
  • the ring elements 1, 2 enclose the shaft hub 3 essentially in a form-fitting manner.
  • the two ring elements 1, 2 are connected to one another by radial struts 4.
  • a rotary coupling designated 5 At the upstream-facing tip of the nozzle device (based on the direction of flow of the engine), a rotary coupling designated 5 overall is arranged.
  • Inner line 13 and outer line 14 are via the rotary coupling 5 in gas or liquid connection with a supply line 10, which the rotary coupling with the in
  • the pressure lines 6 are fixed at the intersection points with the ring elements 1, 2 on these ring elements and thus with part of the supporting structure of the entire nozzle device.
  • tensioning ropes are indicated at 11, which are attached to the rear edges of the fan blade by means of hooks 12. be hooked.
  • the tensioning cables 11 are guided over the tensioning cable guides 17 to the rotating coupling and fastened there.
  • the nozzle device To clean the core engine of a turbofan jet engine, the nozzle device is placed on the shaft hub of the fan in the manner shown in FIGS. 2 and 3 and fixed to the fan blades by means of the hooks 12.
  • the engine is rotated (dry-crane- ing).
  • the rotary coupling 5 and the pressure lines 6, the hollow cone nozzles 7 are fed with cleaning medium (liquid and gas) from the supply device, not shown. This cleaning medium sweeps the inlet of the core engine over its entire circumference and thus carries out the cleaning.
  • Fig. 5 shows schematically the range of technically meaningful angle of attack of the nozzles 7 in order to allow the spray as deep as possible to penetrate along the walls of the inlet guide vanes into the core engine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Cleaning By Liquid Or Steam (AREA)
  • Nozzles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention a pour objet un procédé nettoyer le moteur central d'un moteur à réaction à l'aide d'un agent de nettoyage liquide distribué à partir d'un dispositif à buse. Selon l'invention, l'agent de nettoyage liquide est distribué à partir du dispositif à buse avec une pression inférieure à 20 bar.
PCT/EP2019/070744 2018-08-06 2019-08-01 Procédé, dispositif et système permettant le nettoyage du moteur central d'un moteur à réaction Ceased WO2020030516A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102018119091.3A DE102018119091A1 (de) 2018-08-06 2018-08-06 Verfahren, Vorrichtung und Anordnung zum Reinigen der Core Engine eines Strahltriebwerks
DE102018119091.3 2018-08-06

Publications (1)

Publication Number Publication Date
WO2020030516A1 true WO2020030516A1 (fr) 2020-02-13

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DE (1) DE102018119091A1 (fr)
WO (1) WO2020030516A1 (fr)

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CN112474097A (zh) * 2020-11-19 2021-03-12 中国航发沈阳发动机研究所 一种航空发动机流道清洗喷射装置
US11371385B2 (en) 2018-04-19 2022-06-28 General Electric Company Machine foam cleaning system with integrated sensing
US11371425B2 (en) 2020-09-22 2022-06-28 General Electric Company System and method for cleaning deposit from a component of an assembled, on-wing gas turbine engine
US11441446B2 (en) 2016-01-20 2022-09-13 General Electric Company System and method for cleaning a gas turbine engine and related wash stand
US11555413B2 (en) 2020-09-22 2023-01-17 General Electric Company System and method for treating an installed and assembled gas turbine engine
US11649735B2 (en) 2017-04-26 2023-05-16 General Electric Company Methods of cleaning a component within a turbine engine
US11801536B2 (en) 2016-09-30 2023-10-31 General Electric Company Wash system for a gas turbine engine
US11834632B2 (en) 2013-12-09 2023-12-05 General Electric Company Cleaning solution and methods of cleaning a turbine engine
US12031446B2 (en) 2022-03-29 2024-07-09 General Electric Company Turbine engine servicing tool and method for using thereof
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US12187986B2 (en) 2013-12-09 2025-01-07 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
US12228041B2 (en) 2016-01-20 2025-02-18 General Electric Company System and method for cleaning a gas turbine engine and related wash stand
US11441446B2 (en) 2016-01-20 2022-09-13 General Electric Company System and method for cleaning a gas turbine engine and related wash stand
US11801536B2 (en) 2016-09-30 2023-10-31 General Electric Company Wash system for a gas turbine engine
US12442312B2 (en) 2017-02-27 2025-10-14 General Electric Company Methods and system for cleaning gas turbine engine
US11649735B2 (en) 2017-04-26 2023-05-16 General Electric Company Methods of cleaning a component within a turbine engine
US12435643B2 (en) 2017-04-26 2025-10-07 General Electric Company Methods of cleaning a component within a turbine engine
US11952906B2 (en) 2018-04-19 2024-04-09 General Electric Company Machine foam cleaning system with integrated sensing
US12577887B2 (en) 2018-04-19 2026-03-17 General Electric Company Machine foam cleaning system with integrated sensing
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