EP3443203A1 - Method and device for cleaning turbine blades - Google Patents
Method and device for cleaning turbine bladesInfo
- Publication number
- EP3443203A1 EP3443203A1 EP17717423.2A EP17717423A EP3443203A1 EP 3443203 A1 EP3443203 A1 EP 3443203A1 EP 17717423 A EP17717423 A EP 17717423A EP 3443203 A1 EP3443203 A1 EP 3443203A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- cleaning
- turbine
- engine
- jet
- lance
- 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- Withdrawn
Links
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
- B08B7/00—Cleaning by methods not provided for in a single other subclass or a single group in this subclass
- B08B7/0064—Cleaning by methods not provided for in a single other subclass or a single group in this subclass by temperature changes
- B08B7/0071—Cleaning by methods not provided for in a single other subclass or a single group in this subclass by temperature changes by heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/003—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods using material which dissolves or changes phase after the treatment, e.g. ice, CO2
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
- B24C1/08—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for polishing surfaces, e.g. smoothing a surface by making use of liquid-borne abrasives
- B24C1/086—Descaling; Removing coating films
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C3/00—Abrasive blasting machines or devices; Plants
- B24C3/32—Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B24—GRINDING; POLISHING
- B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
- B24C3/00—Abrasive blasting machines or devices; Plants
- B24C3/32—Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks
- B24C3/325—Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks for internal surfaces, e.g. of tubes
- B24C3/327—Abrasive blasting machines or devices; Plants designed for abrasive blasting of particular work, e.g. the internal surfaces of cylinder blocks for internal surfaces, e.g. of tubes by an axially-moving flow of abrasive particles without passing a blast gun, impeller or the like along the internal surface
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
- C23G5/00—Cleaning or de-greasing metallic material by other methods; Apparatus for cleaning or de-greasing metallic material with organic solvents
Definitions
- the invention relates to a method for cleaning turbine blades of a turbine stage, in particular a high-pressure turbine stage, of a jet engine. Furthermore, the invention relates to a particularly suitable for carrying out the method device.
- Aircraft jet engines have in known manner one or more compressor stages, a combustion chamber, and one or more turbine stages. In the turbine stages, the hot combustion gases from the combustion chamber release some of their thermal and mechanical energy, which is used to drive the compressor stages. Contamination of an aircraft jet engine can lead to a reduction of the effect ⁇ degree, which has an increased fuel consumption and thus increased environmental impact. This applies in particular ⁇ when the contaminants form a coating on the air flowed through parts of an aircraft engine and thereby affect the surface quality.
- the invention has for its object to provide a method for cleaning turbine blades of a turbine stage, in particular a high-pressure turbine stage, as well as a device particularly suitable for this, which are improved over the prior art.
- This object is achieved by a method according to the main claim and a device according to claim 5.
- Advantageous developments are the subject of the dependent claims.
- the invention relates to a method for cleaning turbine blades of a turbine stage of a jet engine, with the successive steps to be performed in chronological order: a. Heating the turbine blades at least in a cleaning area; and then b. Cleaning the turbine blades in the cleaning area by compressed-gas blasting with a cleaning medium comprising solid carbon dioxide, the cleaning area being the blade surface which can be reached directly by the compressed-gas jet.
- the invention relates to a device particularly suitable for carrying out the method according to the invention for cleaning turbine blades of a turbine stage
- a jet engine comprising a cleaning lance with an outlet opening for the cleaning medium designed for compressed-gas jetting with a cleaning medium comprising solid carbon dioxide at its one end and a feed connection for supplying cleaning medium at its other end, which is designed for insertion into a jet engine through a lateral opening the outlet opening can be aligned with a turbine blade of a turbine stage.
- the turbine blades may in particular be the turbine blade of a high-pressure turbine stage.
- the turbine blades may in particular be the turbine blade of a high-pressure turbine stage.
- the "cleaning area” is defined as "blade surface accessible by the compressed gas jet". This means that region of the surfaces of the blades of a turbine stage, to which the compressed gas jet can impinge unhindered and directly.
- the cleaning portion of a turbine stage is dependent from ⁇ particular to shadowing of adjacent turbine blades of the same turbine stage and / or upstream stage, and by the alignment and width of the pressure gas jet.
- the cleaning area can be determined individually for different cleaning tasks (eg cleaning of the profile nose), for example by changing the compressed-gas jet guide. Ends in the cleaning area of a blade, for example.
- Cooling air ducts to form a film cooling during operation of the engine or there are other openings provided the compressed gas jet can also get into the cooling air ducts or other openings, which then the inner wall of the cooling air ducts or other openings can be cleaned.
- the inventive method achieved over the prior art, an improved cleaning effect in the cleaning of turbine blades of a turbine stage of a jet engine. Because of the solid carbon dioxide in a rotatesme ⁇ dium to a cleaning liquid (see FIG. DE 10 2012 002 275 Al) is already achieved increased cleaning effect. The cleaning effect is still further increased by the Temperaturdiffe ⁇ rence is increased between the cleaning medium and the cleaning area by the foregoing heating at least of the cleaning region of the turbine blade, which contributes to breaking and chipping of impurities.
- the device according to the invention is designed for the use of cleaning medium comprising solid carbon dioxide and in particular enables the cleaning of the turbine show ⁇ feln a turbine stage, while the jet engine remains at the flight ⁇ tool (on-wing).
- the heating takes place in the inventive method in time before cleaning by compressed gas jets.
- the two method steps can be carried out immediately one after the other, but not overlapping. But it is also possible that between the two steps a break of a maximum of 10 s, preferably a maximum of 5 s is vorgese ⁇ hen.
- the turbine blade itself is heated and not (only) the dirt to be removed.
- the device liquid carbon dioxide is supplied as a precursor of the cleaning medium ⁇ leads.
- the liquid carbon dioxide then solidifies from ⁇ exits the outlet opening at least partially, and forms a solid component in the form of carbon dioxide flakes. If liquid carbon dioxide comes into contact with ambient air in which it exits, for example, from a nozzle arranged at the outlet opening, a part readily assumes the form of gas. Another part of the carbon dioxide gets stuck in the form of flakes. This is because that binds a lot of heat from the liquid passing into the gaseous state of the carbon dioxide which is withdrawn from the rest of the still liquid part, whereby the temperature thereof to the solidification point of the Koh ⁇ lendioxids decreases.
- the device supplied to the cleaning medium directly solid carbon dioxide - also called dry ice - which geför ⁇ by a propellant gas is changed.
- the solid carbon dioxide can be provided in the form of pel ⁇ lets, which are sprayed with the aid of the propellant gas, such as. Air or CO 2, from the outlet opening.
- Pellets can be produced in a so-called pelletizer from liquid CO 2 and are well storable. It may be vorgese ⁇ hen that prefabricated pellets already be transported by means of the propellant gas to the outlet opening.
- the pellets be formed immediately prior to use of liquid carbon dioxide to subsequent ⁇ lixd conveyed with the fuel gas to the outlet opening to the ⁇ . In both cases, the solid carbon dioxide escapes from the outlet opening and enters the engine to be cleaned.
- the outlet opening must be suitably designed for a corresponding cleaning medium comprising solid carbon dioxide as a solid component.
- the jet pressure during the compressed gas jet is between 6 and 16 bar, preferably between 8 and 12 bar, more preferably between 9 and 10 bar.
- the cleaning range of the turbine blades is preferably at a temperature of 50 to 450 ° C, more preferably at a Tem ⁇ temperature of 120 to 300 ° C, more preferably to a Tempe ⁇ rature of 180 to 230 ° C.
- the cleaning medium based on carbon dioxide pellets from the cleaning medium be ⁇ inhaltete dry ice amount is preferably 50 to 200 kg / h, more preferably from 70 to 200 kg / h, more preferably 180 to 200 kg / h.
- the jet time per cleaning area of a single turbine blade is preferably 0.5 to 20 seconds, more preferably 1 to 10 seconds, more preferably 2 to 4 seconds.
- the turbine blades of the jet engine can be cleaned one at a time, for which purpose the turbine stage is clocked rotated stepwise so that always a Rei ⁇ nists Society an engine blade is located in the pressure gas jet which is moved in a clock at least once over the entire cleaning area.
- a stochastic cleaning of all engine blades takes place together, for which purpose the turbine stage continuously rotated and the compressed gas jet is moved continuously back and forth in a direction perpendicular to the axis of rotation of the turbine stage, so that after a determinable period of the compressed gas jet was passed at least once over each cleaning area of each turbine blade of the turbine stage.
- the gas can be introduced to the turbine blades via a device comparable to the cleaning lance . It is also possible to use this directly the cleaning lance , in which case to ⁇ next warm or hot gas flows through the cleaning lance, before the cleaning medium is supplied. In this case, the hot or hot gas can flow through the same channel in the Rei ⁇ n Trentslanze, then flows through the starsme ⁇ medium.
- the cleaning lance can also have a separate hot gas duct designed for this purpose. If laser radiation or inductive heating is provided for heating the turbine blades, the light guides or electrical lines required for this purpose can be guided directly along the cleaning lance. Hot gas duct, light guide and / or the electrical lines are designed so that a turbine blade arranged in the region of the outlet opening of the cleaning lance turbine blade can be heated.
- the method according to the invention can be carried out on a dismantled and possibly partially dismantled jet engine, it is preferred if the method is carried out on a jet engine (on-wing) located on the aircraft.
- a jet engine on-wing located on the aircraft.
- the costly disassembly and / or (partial) decomposition of the engine can be omitted.
- the cleaning lance is preferably designed for insertion into a beam ⁇ engine by a Boroskopö réelle, an opening for receiving a spark plug or an opening for a fuel ⁇ inspritzdüse of the engine, and have preferably ⁇ , a fastening device with which the cleaning lance on the outside of the Jet engine opposite the insertion opening can be attached.
- Corresponding openings are present on the jet engine, in particular in the region of the combustion chamber housing, and can be used to introduce the cleaning lance after removing a cover or the components respectively arranged in the openings for the operation of the engine, such as spark plugs or injection nozzles.
- the fixing device may in particular provided on the outside of the engine connecting components, in which basically covers and / or components as those mentioned above, attached, together ⁇ men massage to secure the cleaning lance opposite the insertion ⁇ opening.
- the cleaning lance preferably comprises a rigid core tube, whereby the cleaning lance itself is rigid. But there are also other versions of a rigid cleaning lance possible.
- the fastening device preferably comprises a guide mechanism with which the cleaning lance is after Fixed To ⁇ supply of the fastening device on the jet engine at least in the direction of the opening through which the cleaning lance ge ⁇ leads, can be moved.
- a corresponding movability is common advantageous for the above-described stepwise purification of the individual turbine blade as well as for the stochastic cleaning ⁇ account all engine blades.
- the guide mechanism further allows movement of the cleaning lance in the direction of the engine axis and / or a Pivoting about an axis perpendicular to the engine axis.
- the guide mechanism at least for the movement of the cleaning lance in the direction of the opening through which the cleaning lance is guided, one, via a Steuereinrich ⁇ controllable drive.
- the engine stage can then be rotated by the engine-side starter or a separate, preferably the cleaning device associated drive ⁇ unit in rotation and the control device performs the cleaning lance or its outlet opening so that after a certain period of Compressed gas jet was passed at least once over each cleaning area of each turbine blade of the turbine stage.
- the cleaning device comprises a drive unit for rotation of the turbine stage with the to-clean ⁇ constricting turbine blades
- the control means is adapted for driving the controllable drive of the guide mechanism and the drive unit for rotation of the turbine stage of the turbine blades of the jet engine one after another be cleaned by the turbine stage is cyclically rotated clockwise, so that there is always the cleaning area of an engine blade in the compressed gas jet, which is moved in one cycle at least once over the entire cleaning area.
- the outlet opening of the cleaning lance may have a deflection device with which the compressed gas jet is deflected relative to the axis of the cleaning lance.
- the Umlenkvor ⁇ direction may include a curved pipe section or a baffle plate.
- the deflection device may be formed integrally with the cleaning lance. However, it is also possible that the deflection device than on the cleaning lance ⁇ plug cap or as part of a protective coating of the cleaning ⁇ supply lance, which protects the components of the engine before BeCdi ⁇ conditions by the cleaning lance form. In the ⁇ sem case, the deflection device can relatively easily modify and / or replace.
- a Laval nozzle is integrated, which is preferably arranged near the outlet opening ⁇ .
- the Laval nozzle already existing solid carbon dioxide particles can be further accelerated ⁇ nigt in the cleaning medium, whereby the cleaning effect is increased.
- the La ⁇ val nozzle can be adapted to a possible curvature of the cleaning lance and thus also bent or curved out of ⁇ out.
- an optic is seen on the cleaning lance through which at least the cleaning area of a turbine blade can be seen. If a corresponding optics provided, - in particular in an on-wing purification - for the assessment at least of the cleaning region not geson ⁇ engineered endoscope longer required.
- the cleaning lance and / or the protective coating of the cleaning lance ⁇ may be formed to at least in partial regions that they are elastically deformable at ambient temperature, said elastic preferably decreases during the supply of the cleaning medium.
- the same can be achieved by GE ⁇
- One suitable material which at ambient temperature has the desired elasticity, but at lower Tem ⁇ temperatures that inevitably result in supply of the cleaning medium due to the solid or at least liquid carbon dioxide contained therein, but stiffened.
- the introduction of the cleaning lance can be simplified in the engine.
- stiffening the elastic areas of the cleaning lance and / or the protective cover when the cleaning medium is supplied ie, the elasticity decreases
- vibrations and vibrations in the cleaning lance can nevertheless be kept low during the cleaning process.
- the apparatus for cleaning turbine blades of a turbine stage of a jet engine further includes preference ⁇ as a dry-ice reservoir or a dry-ice generator for Kohlenstoffdioxidpellets for the cleaning medium.
- FIG. 1 shows a schematic representation of a first embodiment of a device according to the invention for cleaning turbine blades of a turbine stage of a jet engine; a detailed view of the outlet opening of the cleaning lance of the device of Figure 1; a schematic representation of a detail of the cleaning lance of the device of Figure 1; a detailed view of the fastening device of the cleaning device of Figure 1;
- FIG. 5 shows a schematic representation of the cleaning of a turbine blade with the cleaning device from FIG. 1;
- Figure 6a-d variants for the design of the cleaning lance
- FIG. 1 shows a schematic representation of a device 1 according to Inventive ⁇ for cleaning turbine blades 80 of a turbine stage 81 of a turbofan engine 82 is shown.
- the jet engine 82 also shown only schematically, is attached directly to the aircraft (not shown). The following statements therefore relate in particular to on-wing cleaning.
- the device 1 for cleaning turbine blades 80 environmentally summarizes a cleaning lance 2 with a pressurized gas to the jets with a cleaning medium comprising solid carbon dioxide from ⁇ formed outlet opening 3 at one end 4 (see FIG. 2).
- a supply port 5 is arranged for the supply of cleaning medium.
- the cleaning lance 2 is inserted through an original for an ignition ⁇ candle provided lateral opening 83 in the housing 84 of the combustion chamber 85, wherein it is so performed one end 4 through the Turbinenleitschaufein 86, that the exit ⁇ opening 3 of the cleaning lance 2 to the turbine blades 80 of the first high-pressure turbine stage 81 is aligned.
- the cleaning lance 1 is attached via a fastening device 7 to the housing 84 of the combustion chamber 85 (see also Figure 4).
- the fastening device 7 engages in the thread 87, which is provided for the attachment of the spark plug, a.
- a drive profile 8 preferably a hexagonal profile with a standard key width, provided.
- the fastening device 7 comprises a guide mechanism, not shown, with which the cleaning lance can be moved by fastening the fastening device 7 on the jet engine 82 in the direction indicated by the double arrow 90 direction of the opening 83, through which the cleaning lance 2 is guided by a controllable electric drive , whereby also the outlet opening 3 can be moved accordingly.
- the cleaning lance 2 comprises a core tube 10 which is provided with egg ⁇ nem protective coating 11 to protect ⁇ damage the components of the engine 82 in contact with the cleaning lance 2 before Be (see FIG. 2).
- a Laval nozzle 12 in the region of the end 4 to the outlet opening 3 is provided to the interior of the cleaning lance 2 is a Laval nozzle 12, which is in Darge ⁇ exemplary embodiment illustrated in a curved portion of the core tube 10 is arranged and thus also curved out ⁇ leads (see FIG. 3 ).
- the device 1 for cleaning turbine blades 80 further comprises a drive unit 13 for rotation of the
- Engine 82 and thus also the turbine stage 81 with the turbine blades 80 to be cleaned.
- the drive unit 13 is connected via an engine-side transmission 14 directly to the engine axis, at the u.a. the turbine stage 81 in question is attached.
- Both the drive unit 13 for rotation of the turbine stage 81 and the fastening device 7 with the electric drive arranged therein for moving the cleaning lance 6 are coupled to a control device 15 and are controlled by this.
- Control lines are indicated in Figure 1 as dashed arrows.
- the device 1 further comprises a controlled by the control device 15 dry ice jet generator 16, based on solid carbon dioxide pellets from the dry ice reservoir 17 and the compressed air compressor 18 made available compressed air, a cleaning medium comprising solid Kohlendi ⁇ oxide can form.
- the air compressor 18 is also connected to a heater 19, which is also controlled by the controller 15 and which can heat the compressed air to hot gas when needed.
- the hot gas can be applied directly by the cleaning lance 2 on the drive ⁇ bucket 80.
- it is pos ⁇ lich to provide a separate hot gas lance (not shown), with which the hot gas in the position of the turbine blade 80 in which the subsequent cleaning is carried out, is applied.
- hot gas is applied via a hot gas lance (not shown) to a turbine blade 80 in a deviating position and the turbine blade 80 is then moved by rotation of the turbine stage ⁇ 81 via the drive motor 13 in the cleaning position.
- the turbine blade 80 by Druckgasterah ⁇ len with a cleaning medium generated by the dry ice jet generator 16 comprising solid carbon dioxide and air as
- FIG. 5 shows by way of example the situation during the cleaning of the turbine blades 80 with the compressed gas jet.
- the end 4 of the cleaning lance 2 with the outlet opening 3 between the Turbinenleitschaufein 86 is passed, so that the bordered by the in Fig. 5 by dashed lines 70 compressed gas ⁇ jet basically unhindered can hit the turbine blades 80.
- the cleaning portion 71 of the turbine blade 80 - - depending drawn in Figure 5 ⁇ pressurized gas jet angle directly achievable from the pressure gas jet vane surface may be affected by shadowing benachbar ⁇ ter turbine blades 80 ⁇ .
- In the cleaning portion 71 ending cooling air ducts 91 can also be ge ⁇ purified.
- the drawn in Figure 5 distance A Zvi ⁇ rule of the outlet opening 3 and the planar Turbinenworkneingangs- is at least 10 mm.
- control device 15 is designed to move the cleaning lance 2 via the fastening device 7 in such a way that the entire cleaning region 71 of the turbine blade 80 that can be reached by the compressed gas jet is cleaned of the compressed gas jet.
- the cleaning lance 2 in the direction 90 of the opening 83, through which the cleaning lance is guided 2 is a ⁇ moves at least once over the entire blade length.
- the Steue ⁇ approximately device 15 controls the drive motor 13 such that the turbine stage is further rotated by a turbine blade 80 81, so the adjacent to the previously purified turbine blade 80 turbine blade 80 with its cleaning region 71 in the Compressed gas jet is located.
- the turbine stage 81 is thus getak ⁇ tet rotated stepwise so that always a rotatesbe ⁇ rich 71 of a engine blade 80 is located in the pressure gas jet which is moved in a clock at least once over the entire cleaning area 71st
- the actual cleaning region 71 of the turbine blade 80 is, inter alia, significantly dependent on the compressed gas jet angle. In this case that (up to max. 90 °) a better cleaning of the pre ⁇ derkante of the turbine blades 80 can be achieved at a higher pressure gas jet angle applies in principle.
- FIGS. 6 ad show different variants of corresponding deflection devices 21.
- the deflection device 21 is also inbil ⁇ det as part of the protective coating 11 of the cleaning lance 2 which projects over the core tube 10 and is bent. Also in the variant according to FIG. 6 b, the coating 11 protrudes beyond the core tube 10. However, the coating 11 is in this case only bevelled such that the force resulting from ⁇ opening 3 ⁇ ver ⁇ runs parallel to the turbine stage input level.
- the core tube 10 to be ⁇ nem one end an impingement plate 22 on which the Umlenkvor ⁇ direction is formed 21st
- the end of the core tube 10 is bent over in order to form the deflection device 21.
- a protective cover 11 may also be provided in the embodiment variants according to FIGS. 6c and d.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Cleaning In General (AREA)
- Cleaning By Liquid Or Steam (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102016206246.8A DE102016206246A1 (en) | 2016-04-14 | 2016-04-14 | Method and device for cleaning turbine blades |
PCT/EP2017/058914 WO2017178581A1 (en) | 2016-04-14 | 2017-04-13 | Method and device for cleaning turbine blades |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3443203A1 true EP3443203A1 (en) | 2019-02-20 |
Family
ID=58547534
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17717423.2A Withdrawn EP3443203A1 (en) | 2016-04-14 | 2017-04-13 | Method and device for cleaning turbine blades |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP3443203A1 (en) |
DE (1) | DE102016206246A1 (en) |
WO (1) | WO2017178581A1 (en) |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110948401B (en) * | 2019-11-19 | 2021-06-01 | 中国航发沈阳黎明航空发动机有限责任公司 | Adjustable protection device applied to blade finishing |
US11572800B2 (en) | 2020-02-14 | 2023-02-07 | Raytheon Technologies Corporation | Borescope port engine fluid wash |
CN111644988A (en) * | 2020-06-30 | 2020-09-11 | 盐城迪尔特抛丸设备有限公司 | Shot blasting machine and application method thereof |
CN113102379A (en) * | 2021-04-12 | 2021-07-13 | 王志强 | Can clean camera lens formula unmanned aerial vehicle |
CN113843197B (en) * | 2021-09-18 | 2022-08-05 | 佛山大德激光设备有限公司 | Turbine blade cleaning system and cleaning method thereof |
CN114082710B (en) * | 2022-01-20 | 2022-05-31 | 中国民航大学 | Cleaning and lubricating system for fan blades of aircraft engine |
CN115254819A (en) * | 2022-07-14 | 2022-11-01 | 中国民用航空飞行学院 | Rotary turbine blade cleaning tool based on hydrodynamics |
CN115676301B (en) * | 2022-11-09 | 2023-10-10 | 华能国际电力股份有限公司井冈山电厂 | Blending combustion conveying device and method for improving blending combustion fluidity of sludge in power plant |
CN117644478B (en) * | 2024-01-30 | 2024-05-17 | 西安格美金属材料有限公司 | Performance improvement method for aircraft multi-stage supercharged jet engine |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102010045869A1 (en) * | 2010-08-03 | 2012-02-23 | Mtu Aero Engines Gmbh | Cleaning a turbo machine stage |
DE102012002275A1 (en) * | 2012-02-06 | 2013-08-08 | Rolls-Royce Deutschland Ltd & Co Kg | Apparatus and method for processing high-pressure turbine blades of a gas turbine |
DE102012213590B4 (en) * | 2012-08-01 | 2014-04-03 | Lufthansa Technik Ag | Apparatus and method for cleaning a jet engine |
DE102012021964A1 (en) * | 2012-11-08 | 2014-05-22 | Linde Aktiengesellschaft | Method and apparatus for removing contamination from a surface |
DE102013002636A1 (en) * | 2013-02-18 | 2014-08-21 | Jürgen von der Ohe | Device for jet cleaning of unit, particularly of gas turbine jet engines of airplane, has jet nozzle with introduction stop, which limits depth of insertion of jet nozzle into opening, where twist element is arranged to introduction stop |
US9267393B2 (en) * | 2013-03-04 | 2016-02-23 | General Electric Company | Dry ice cleaning apparatus for gas turbine compressor |
-
2016
- 2016-04-14 DE DE102016206246.8A patent/DE102016206246A1/en not_active Ceased
-
2017
- 2017-04-13 EP EP17717423.2A patent/EP3443203A1/en not_active Withdrawn
- 2017-04-13 WO PCT/EP2017/058914 patent/WO2017178581A1/en active Application Filing
Also Published As
Publication number | Publication date |
---|---|
WO2017178581A1 (en) | 2017-10-19 |
DE102016206246A1 (en) | 2017-10-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP3443203A1 (en) | Method and device for cleaning turbine blades | |
EP2280872B1 (en) | Method and device for cleaning a jet engine using solid carbon dioxide | |
EP1993744B1 (en) | Device and method for cleaning the core engine of a jet engine | |
EP0781897A2 (en) | Method and device for the wet cleaning of the nozzle ring of a turbocharger | |
DE10116452B4 (en) | Gas turbine and repair process for this | |
WO2009129788A2 (en) | Method for cleaning an aircraft engine | |
EP3833492B1 (en) | Device, process and arrangement for cleaning of the core engine of a jet engine | |
EP2565391B1 (en) | Cleaning device of a exhaust gas turbine and corresponding exhaust gas turbine, power turbine and exhaust gas turbocharger | |
WO2020030516A1 (en) | Method, device and arrangement for cleaning the core engine of a jet engine | |
EP2136052A1 (en) | Turboprop engine comprising a device for creating a cooling air flow | |
WO2019076875A1 (en) | Device for cleaning turbine blades of a jet engine | |
WO2012130443A2 (en) | Cleaning lance and method for cleaning driving mechanisms | |
EP3074181B1 (en) | Method for cleaning a jet engine | |
EP1117913B1 (en) | Fuel preheating in a gas turbine | |
EP1618285B1 (en) | Method of assembly/disassembly of aviation engines | |
DE102004060884A1 (en) | Method for removing of combustion residues from wall of chamber carrying combustion gases involves contacting of combustion residues with first cleaning medium, and contacting of pre-treated residues with second cleaning medium | |
WO2005088103A1 (en) | Device and method for heating a gas flow | |
DE202009016059U1 (en) | Device for generating electricity | |
EP3387236B1 (en) | Gas turbine comprising a wet compression device for introducing a surfactant liquid mixture | |
DE102012213590B4 (en) | Apparatus and method for cleaning a jet engine | |
EP2194233A2 (en) | Flow splitter for a fan engine | |
DE102016214076A1 (en) | Intercooler | |
EP2730344A1 (en) | Method and apparatus for removing a contaminant from a surface | |
EP3113901A1 (en) | Method for repairing an airfoil, and cooling collar | |
EP0648919A2 (en) | Process and system for executing of gas production for operating a gas turbine in a combined power plant |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: UNKNOWN |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE INTERNATIONAL PUBLICATION HAS BEEN MADE |
|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
17P | Request for examination filed |
Effective date: 20181106 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE |
|
DAV | Request for validation of the european patent (deleted) | ||
DAX | Request for extension of the european patent (deleted) | ||
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: EXAMINATION IS IN PROGRESS |
|
17Q | First examination report despatched |
Effective date: 20210909 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20220120 |