CN102307679A - Engine wash system and method - Google Patents

Engine wash system and method Download PDF

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Publication number
CN102307679A
CN102307679A CN2009801448440A CN200980144844A CN102307679A CN 102307679 A CN102307679 A CN 102307679A CN 2009801448440 A CN2009801448440 A CN 2009801448440A CN 200980144844 A CN200980144844 A CN 200980144844A CN 102307679 A CN102307679 A CN 102307679A
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CN
China
Prior art keywords
gas
turbine unit
planes
engine
contained structure
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Pending
Application number
CN2009801448440A
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Chinese (zh)
Inventor
R·L·斯通
D·E·格伯
K·马苏达
D·G·布兰彻特
M·D·富林顿
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General Electric Co
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General Electric Co
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Filing date
Publication date
Priority claimed from US12/612,355 external-priority patent/US20110108062A1/en
Application filed by General Electric Co filed Critical General Electric Co
Publication of CN102307679A publication Critical patent/CN102307679A/en
Pending legal-status Critical Current

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    • 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
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics

Abstract

A system for washing a gas turbine engine, the gas turbine engine having an inlet and an exhaust, the exhaust having an inner surface and an outer surface. The system comprises: a containment structure for capturing gaseous, liquid, and solid material emerging from the engine; a filtration system for separating the gaseous, liquid, and solid material; and a retaining ring for securing the containment structure to said exhaust; wherein the retaining ring is adjustable in at least one of size and shape so as to sealingly engage the inner surface of the exhaust.

Description

Engine purging system and method
Technical field
The techniques described herein relate generally to gas-turbine unit, and relate more specifically to be used to clean the system and method for gas-turbine unit, and the method that is used for the Clean after every of definite gas-turbine unit.
Background technology
At least a known gas turbine assembly comprises the fan component that is installed in the core gas-turbine unit upper reaches.During operation, the portion of air of discharging from fan component flows to downstream and guides to the core gas-turbine unit, and therein, air stream further is compressed.Air compressed stream is directed in the burner then, mixes mutually with fuel, and produces hot combustion gas through lighting.Burning gases guide to turbine then, and this turbine obtains energy to compressor power being provided from burning gases, and produce useful work and advance aloft aircraft.Another part air of discharging from fan component is flowed through and is left engine by the fan flow nozzle.
In operation, particularly closely look like take-off and landing during operating period at aircraft, gas-turbine unit can be taken in various forms of foreign substances, like dust, dirt, insect etc.Even its size of these materials is enough little or very frangible and under situation about not damaging, get into and pass engine, but these materials can stay residue on in-engine inner surface.Pass the combustion by-products of engine and the oxidation of various members and also can on the engine inner surface, produce or stay residue.As time goes on, these residues can be accumulated, and engine performance is had side effects.
Developed various system and methods, utilizing cleaning solution " cleaning " or clean the inner surface of these gas-turbine units, thereby removed residue with restorability.Yet these systems much all use trouble, comprise the engine that makes many members and/or large-scale flexible structure surround cleaning.Many systems can't catch residue and cleaning solution fully after using, cause the pollution to outside environmental surfaces of loss that solution re-uses and residue and cleaning solution.
Therefore, still need a kind of improvement system and method that is used to clean gas-turbine unit, it improves catching residue and cleaning solution.
In addition, many gas-turbine unit operating personnel rely on and determine when based on mode of operation or the announcement suggestion of operation duration and to need cleaned engine.Other some are then carried out cleaning operation based on certain operation rhythm or frequency.Some that also have then rely on certain variation of level of engine performance.Yet, determine when that these methods of need cleaning can cause for optimum performance cleaning operation too much to carry out or carry out deficiency.
Therefore, still need a kind of improved method for optimum performance, when need to confirm engine to clean.
Summary of the invention
On the one hand, described a kind of system that is used to clean gas-turbine unit, this gas-turbine unit has inlet and discharger (exhaust), and this discharger has inner surface and outer surface.This system comprises: the contained structure that is used for catching the gaseous material, fluent material and the solid material that form from engine; Be used to separate the filtration system of gaseous material, fluent material and solid material; And be used for contained structure is fixed to the retaining ring on the said discharger; Wherein, at least one in the size and dimension of retaining ring is adjustable, so that engage the inner surface of discharger hermetically.
On the other hand, described a kind of method of cleaning gas-turbine unit, this method may further comprise the steps: gas-turbine unit is provided, and this engine has inlet and discharger, and this discharger has inner surface and outer surface; Be provided for cleaning the system of gas-turbine unit, this system comprises contained structure; Through retaining ring contained structure is fixed on this inner surface releasedly; Cleaning liquid is introduced in the inlet; And cleaning liquid is collected in the contained structure.
On the other hand; A kind of method of cleaning gas-turbine unit that determines when has been described; This method may further comprise the steps: measure the engine performance data of gas-turbine unit, this gas-turbine unit is a region operation group of planes (fleet) and starts group of planes family to operate the part of a group of planes; The average behavior data of a zoning operation group of planes; The average behavior data of a calculation engine crowd family operation group of planes; The engine performance data of gas-turbine unit is compared with the average data of a region operation group of planes; And indication needs to clean gas-turbine unit when comparison step shows that the gas-turbine unit performance descends.
On the other hand; A kind of optimal clean method of confirming in order to clean gas-turbine unit has at interval been described; This method may further comprise the steps: measure the engine performance data of gas-turbine unit, this gas-turbine unit is a region operation group of planes and a part of starting a group of planes family operation group of planes; Calculate the key engine Performance Characteristics of gas-turbine unit through the development& testing of the data that record and manufacturers of engines in the whole life cycle of gas-turbine unit; Calculating comes from the manufacturers of engines algorithm and to the average group of planes rate of change of the key performance characteristic of the simulation of the engine that do not clean and clean; Gas-turbine unit Performance Characteristics based on the manufacturers of engines of key is developed is calculated the average cleaning benefit retention time and is calculated its rate of change based on group of planes data and operation Consideration; Gather average block (block) the fuel combustion data of a specific region operation group of planes; Calculating clean influence by engine other have cost and measure, comprise the influence of maintenance cost with overhaul (or maintenance) interval; Fuel cost and the engine of gathering a specific region operation group of planes are washed to notebook data; And the financial cost interest analysis that is based upon the specific region operation group of planes of independently special course line customization comes the calculating optimum Clean after every.
Description of drawings
Fig. 1 is the side elevation view of exemplary gas-turbine unit and engine purging system;
Fig. 2 is the planar top view of gas-turbine engine shown in Fig. 1 and engine purging system;
Fig. 3 is the cross sectional elevation of engine purging system shown in Fig. 1 of 3-3 intercepting along the line, shows main mist collector; And
Fig. 4 is the decomposition view of the mist collector that is suitable in the engine purging system shown in Fig. 1 to Fig. 3, using.
The specific embodiment
Fig. 1 is the front view with exemplary gas turbine assembly 10 of longitudinal axis.Gas turbine assembly 10 comprises fan component and core gas-turbine unit.The core gas-turbine unit comprises high pressure compressor, burner and high-pressure turbine.In the exemplary embodiment, gas turbine assembly 10 also comprises low-pressure turbine, multistage booster compressor, and the separator of external booster substantially.
Fan component comprises from the radially export-oriented fan blade array that extends of rotor disk.Gas turbine assembly 10 has entrance side and discharger side.Fan component, booster and turbine through the first rotor axle be linked together, and compressor and turbine pass through second armature spindle be linked together.
In operation, air flows through fan component, and booster passes through guiding in the first of air stream.The compressed air of discharging from booster passes compressor through guiding, and therein, air stream further is compressed and is delivered to burner.The hot combustion product that comes from burner is used to drive turbine, and a turbine is used for coming drive fan assembly and booster through the mode of axle.The first of air stream is disposed to atmosphere together with combustion product via nozzle 15.In the operating condition scope of gas turbine assembly 10 between design operation condition and non-design operation condition is exercisable.
The second portion that the air of discharging from fan component flows passes by-pass conduit through guiding, walks around around the core gas-turbine unit so that come from the part air stream of fan component.More specifically, by-pass conduit extends between blower-casting or guard shield and the separator.Therefore; As indicated above; Booster passes through guiding in the first that comes from the air stream of fan component, and gets in the compressor then, and the second portion that comes from the air stream of fan component passes by-pass conduit through guiding and with usual practice such as aircraft thrust is provided.Gas turbine assembly 10 comprises that also the fan frame assemblies is to provide structure support and also to be used for fan component is connected to the core gas-turbine unit to fan component.
Also show engine purging system 20 among Fig. 1.Be shown exemplary water and clean the engine purging system 20 of trailer (WWT) unit form and comprise trailer 30 or other conveying arrangement that is fit to, coiled casing (boot) 40, annular holder 45, acquisition equipment 50 as drip a dish, gathering system 60, optional storage box 70, and the cleaning liquid spraying system (not shown) that can be commercial system.
Engine purging system 20 is designed in order to collect waste water the engine cleaning operation term of execution and from the engine exhaust particle of exhaust nozzle 15, gas turbine assembly 10 keeps being installed on the aircraft simultaneously.In the gas turbine engine, form the combination that is generally gaseous material, fluent material and solid material of (or appearance), like air, water or clean solution and granular materials from the gas turbine engine.
Coiled casing 40 is installed in the exhaust nozzle 15 through the retaining ring for annular holder 45 forms, and this annular holder 45 forms in order to engage the inner surface of exhaust nozzle 15 with structure for being designed to for this reason purpose and its size especially.Therefore annular holder 45 makes coiled casing can be fixed on the exhaust nozzle and any additional firmware or any specially designed characteristic need not arranged on gas turbine assembly 10.For sleeve pipe 40 is fixed on the nozzle 15, annular holder 45 its sizes are reduced to the diameter littler than exhaust nozzle 15, and insert sufficient distance in the nozzle 15, and for instance, for example the outlet apart from exhaust nozzle 15 has about 3 inches.Annular holder 45 is then through the expansion of any suitable mechanism, the hand-crank screw shown in the embodiment of Fig. 1, thus guarantee to center between coiled casing 40 and nozzle 15 inner surfaces their the contacting of circumference.This joint has been guaranteed initiatively sealed engagement, so that help to guarantee that the discharge air to leaving nozzle 15 has higher capture rate.Annular holder or retaining ring are except that size or replace size and be variable in shape, insert in the exhaust nozzle and engage with the nozzle inner surface then so that allow.
Gathering system 60 includes and helps to catch and collect the washing fluid removed from gas turbine assembly 10 and the characteristic of material.Shown in Fig. 1 to Fig. 3, gathering system 60 comprises being used as expands (or expansion) chamber so that leave the air of nozzle 15 and the water collection transition bin 62 of drop deceleration, and corresponding main mist collector 64 and secondary mist collector 66.Main mist collector 64 is designed in order to intercepting water or fluid mist from discharge air, and secondary mist collector 66 is designed to any mist or the droplet that pass main mist collector 64 in order to catch.Fig. 3 shows a kind of suitable structure as mist collector 64 and/or 66 in more detail, but a variety of other structure also is provably suitable.Mist collector can be single layer structure, or is sandwich construction as shown in Figure 3.
The physical details of engine purging system 20 comprises various size of component and shape, can be suitable for combining one or more particular configuration of gas turbine assembly 10 to use.In addition, washing fluid may be selected to be and is used for specific sanitary characteristics and atmospheric environment, like temperature.In some cases, can use the light water that comes from urban water supply or other source, and in other situation, can make the mixture of water and cleaning agent such as detergent.The mixture of water and alcohol can be used for the engine cleaning operation under the cryogenic conditions.If expectation, washing fluid also can heat.
Engine purging system 20 can be completely from accepting unit, its distribution and collect cleaning fluid, or can be collector unit, and it relies on separately and independent the outfit and/or the cleaning fluid distribution system of operation, like current commercially available those.Collection type unit generally include be used for from gathering system remove collected liquid suction pump, be used for removing the filter of granular materials and/or clean solution from water; And the sufficient reservoir vessel of capacity; For instance; For example 60 gallons, in order to remain on water consumption used in the representative engine cleaning procedure.Feed and distributing equipment be will comprise from accepting unit completely, heater or other pre-processing device comprised, and above-mentioned collection characteristic.
Other optional feature that can comprise is detergent filtration system, cold water reservoir vessel, the hot water tank with heater, detergent container, be used to spray the high-pressure pump of purpose, be used for manual selector valve, the pressure safety valve between water receptacle or detergent container, selected, and solution playpipe (being generally Shephard ' s cane (Xie Pode sugarcane) form).
Transition bin 62 by constituting such as stainless suitable material is caught water smoke from exhaust nozzle 15, and collects used rinse water or fluid.This bin is designed to make the air of discharging from nozzle 15 will expand to the bin and air velocity is reduced, thereby improves the possibility of catching water smoke and particle.This bin and/or gathering system can comprise and be used to rotate and/or slow down air stream and help the stator of fluid separation applications.Waste water enters downwards and drips in the dish 50, and one or more dish is used for catching and collecting any a spot of rinse water or the fluid that can spill from the various elements of gas turbine assembly 10 or engine purging system 20.
Pump such as self priming pump can be used for used rinse water or fluid are sent in the reservoir vessel, optionally via water filtering system.The filter that is fit to can be provided as in order to used rinse water or filtering flow to desired standard, comprises the granular materials of removing such as 1 micron specified size.The suitable one or more water receptacles of size can be provided as in order to the water that stores the warp filtration so that further use or eliminating subsequently.
Trailer 30 provides mechanism easily to be used to support, store and organize the various elements of engine purging system 20.Optionally, the lifting mechanism (not shown) can be provided as the part of engine purging system 20 and/or trailer 30.This kind lifting mechanism can be used for the element of engine purging system 20 is positioned at desired height, uses so that combine various aircraft and Gas Turbine Modules to construct.This kind lifting mechanism can be the part of engine purging system 20, or can be independent vehicle or mechanism, and can comprise hydraulic pump, electro-motor and relevant manifold, valve, pipeline and check valve, or can be mechanically actuated and supporting.The lifting mechanism that is fit to designs and is configured to the element in order to supporting engine purging system 20, and can comprise security feature, like locking piece, pull bar etc., in order to guarantee safety operation.Lifting mechanism or other machinery, pneumatic or hydraulic mechanism can be provided for adjusting the aligning of other element of bin, sleeve pipe or system, and can come the artificially operation through hand-crank or alternate manner, or can power be provided by electro-motor or other device.
Can be included in the engine purging system 20 or other element that binding engine purging system 20 uses comprises in order to generator that electric power is provided to system, in order to from the exhaust nozzle vacuum drawn with collect vacuum cleaner or other this kind suction generating device of any residual water, and in order to be connected to the earth connection on the suitable electrical earthing or grounding means at place, operation place.
In the preparation of operation, should consider the water cleaning procedure in aircraft operation handbook and/or the craft preservation handbook corresponding to various types of aircraft of carrying out the engine cleaning procedure thereon.Significant consideration is that gas-turbine unit should be with the operation of " dried motoring " pattern, and wherein, the core component of gas-turbine unit is rotated by engine primer having no fuel to be supplied under the situation of fuel system (fuel nozzle etc.).This is different from " wet motoring ", and (it is identical with " dried motoring "; But have fuel to be supplied to fuel system) and " ground idle running "; In ground idle running, gas turbine has started and has operated down at himself power, normally maintains ground operation with the slowest idle speed.
Before operation engine purging system; The suggestion following steps: the damage in the inspection shipment, remove and store cover cap, once more check damage or anomalous event, open lead to the door that stores capsule with the petrol tank of guaranteeing generator fill, the leakage of test liquid pressing system, and guarantee that cylinder is in suitable position and switch cuts out.Simultaneously, allow aircraft operation personnel about 5 minutes of controlling gas turbine under ground idle running, or the alternate manner of being recommended by the craft preservation handbook; Shutting engine down; And engine purging system trailer is positioned at the rear of engine centerline, and the artificially is near engine, up to the bin inlet away from about 3 feet of jet expansion.Guarantee the center line aligning of engine and bin, move trailer nearer lentamente, enter the mouth away from about 20 inches of exhaust nozzle pelvic outlet plane up to bin.Coiled casing can be fixed on the engine exhaust nozzle through the remainder of retaining ring and performed cleaning sequence then.
Benefit for the water cleaning program that increases gas-turbine unit to greatest extent; When cleaning the performance benefit that will provide desired; Should be at certain hour and carry out this cleaning process at a certain time interval, the cost and the time of balance cleaning process self simultaneously.
In order to determine when to the time that is fit to and the time interval that is fit to so that on given gas-turbine unit, carry out the engine cleaning operation; Can use following method; It comprises the steps: to measure the engine performance data of gas-turbine unit, and this gas-turbine unit is a region operation group of planes and a part of starting a group of planes family operation group of planes; Calculating is used for the average behavior data of a region operation group of planes; Calculating is used to start the average behavior data of a group of planes family operation group of planes; The engine performance data of said gas-turbine unit is compared with the average data of a region operation group of planes; And indication needs to clean gas-turbine unit when comparison step shows that the gas-turbine unit performance descends.
This group method that determines when cleaning can be through the further refinement of more detailed method, method as mentioned below.
Be used to confirm that reasonable time and the reasonable time this more detailed method at interval of on given gas-turbine unit, carrying out the engine cleaning operation may further comprise the steps: measure the engine performance data of gas-turbine unit, this gas-turbine unit is a region operation group of planes and a part of starting a group of planes family operation group of planes; Calculate the key engine Performance Characteristics in the whole engine life cycle through the data that record and the development& testing of manufacturers of engines; Calculating comes from the manufacturers of engines algorithm and to the average group of planes rate of change of the key performance characteristic of the simulation of the engine that do not clean and clean; Performance Characteristics based on the manufacturers of engines of key is developed is calculated the average cleaning benefit retention time and is calculated its rate of change based on group of planes data and operation Consideration; Gather the average block fuel combustion data of a specific region operation group of planes; Calculating clean influence by engine other have cost and measure, comprise influence to maintenance cost and time between overhaul; Fuel cost and the engine of gathering a specific region operation group of planes are washed to notebook data; And the financial cost interest analysis that is based upon the specific region operation group of planes of independently special course line customization comes the calculating optimum Clean after every.
These methods can be through additional Consideration, comes as required and refinement like type of aircraft, engine model with such as the flight characteristics of duration flight and distance.For example, these calculating can only be used about single type of aircraft, single engine model, or have the group of planes of identical duration flight and/or distance or handset crowd's data produce.
The contained structure of engine purging system can use like any suitable material of any suitable manufacturing approach cause known in the field with other element and process, and structure that is suitable for expecting and operating environment.Equally, any suitable liquid all can be used as washing fluid, comprises water, detergent and/or all kinds of solvents.The various size of component of this system, shape and layout can change into and adapt to any certain applications, or any specific Consideration, like storage area, rodability etc.
Although described the present invention according to various specific embodiments, those of ordinary skill in the art will recognize that the present invention can be utilized in the modification of carrying out in the spirit and scope of claim and implement.

Claims (20)

1. system that is used to clean gas-turbine unit, said gas-turbine unit has inlet and discharger, and said discharger has inner surface and outer surface, and said system comprises:
Be used for catching the contained structure of the gaseous material, fluent material and the solid material that form from said engine;
Be used to separate the filtration system of said gaseous material, fluent material and solid material; And
Be used for said contained structure is fixed to the retaining ring on the said discharger;
Wherein, at least one in the size and dimension of said retaining ring is adjustable, so that engage the said inner surface of said discharger hermetically.
2. system according to claim 1 is characterized in that said contained structure comprises expansion chamber.
3. system according to claim 1 is characterized in that, said system also comprises and is used for said contained structure is connected to the coiled casing on the said discharger.
4. system according to claim 1 is characterized in that, said discharger is an exhaust nozzle.
5. system according to claim 1 is characterized in that said system is installed on the trailer.
6. system according to claim 1 is characterized in that, said system comprises the flexible apron that is used to catch said gas-turbine unit below liquid.
7. system according to claim 1 is characterized in that, said system comprises the dish that drips that is used to catch liquid.
8. system according to claim 1 is characterized in that, said system comprises main mist collector and secondary mist collector.
9. system according to claim 1 is characterized in that, said retaining ring is an annular holder.
10. system that is used to clean gas-turbine unit, said gas-turbine unit has inlet and exhaust nozzle, and said exhaust nozzle has inner surface and outer surface, and said system comprises:
Be used for catching the contained structure of the gaseous material, fluent material and the solid material that form from said engine;
Be used for said contained structure is connected to the coiled casing on the said exhaust nozzle;
Be used to separate the filtration system of said gaseous material, fluent material and solid material; And
Be used for said contained structure is fixed to the retaining ring on the said exhaust nozzle;
Wherein, at least one in the size and dimension of said retaining ring is adjustable, so that engage the said inner surface of said exhaust nozzle hermetically.
11. a method of cleaning gas-turbine unit said method comprising the steps of:
Gas-turbine unit is provided, and said engine has inlet and discharger, and said discharger has inner surface and outer surface;
Be provided for cleaning the system of gas-turbine unit, said system comprises contained structure;
Through retaining ring said contained structure is fixed on the said inner surface releasedly;
Cleaning liquid is introduced in the said inlet; And
Said cleaning liquid is collected in the said contained structure.
12. method according to claim 11 is characterized in that, said contained structure comprises expansion chamber.
13. method according to claim 11 is characterized in that, said method also comprises and is used for said contained structure is connected to the coiled casing on the said discharger.
14. a method of cleaning gas-turbine unit said method comprising the steps of:
Gas-turbine unit is provided, and said engine has inlet and exhaust nozzle, and said exhaust nozzle has inner surface and outer surface;
Be provided for cleaning the system of gas-turbine unit, said system comprises the contained structure with expansion chamber;
Said contained structure is fixed on the said inner surface through the coiled casing of being fixed by retaining ring releasedly;
Cleaning liquid is introduced in the said inlet; And
Said cleaning liquid is collected in the said contained structure.
15. one kind determines when the method for cleaning gas-turbine unit, said method comprising the steps of:
Measure the engine performance data of gas-turbine unit, said gas-turbine unit is a region operation group of planes and a part of starting a group of planes family operation group of planes;
Calculate the average behavior data of a said region operation group of planes;
Calculate said average behavior data of starting a group of planes family operation group of planes;
The said engine performance data of said gas-turbine unit is compared with the said average data of a said region operation group of planes; And
The indication needs clean said gas-turbine unit when said comparison step shows that said gas-turbine unit performance reduces.
16. method according to claim 15 is characterized in that, said data are relevant with single gas-turbine unit model.
17. method according to claim 15 is characterized in that, a said region operation group of planes and the said aircraft that starts a group of planes family operation group of planes to comprise single type.
18. a definite optimal clean is cleaned the method for gas-turbine unit at interval, said method comprising the steps of:
Measure the engine performance data of gas-turbine unit, said gas-turbine unit is a region operation group of planes and a part of starting a group of planes family operation group of planes;
Calculate the key engine Performance Characteristics of said gas-turbine unit through the development& testing of the data that record and manufacturers of engines in the whole life cycle of said gas-turbine unit;
Calculating comes from the manufacturers of engines algorithm and to the average group of planes rate of change of the key performance characteristic of the simulation of the engine that do not clean and clean;
The Performance Characteristics of the said gas-turbine unit of developing based on the manufacturers of engines of key is calculated and is on average cleaned the benefit retention time and calculate its rate of change based on group of planes data and operation Consideration;
Gather the average block fuel combustion data of a said specific region operation group of planes;
Calculating clean influence by engine other have cost and measure, comprise influence to maintenance cost and time between overhaul;
Fuel cost and the engine of gathering a said specific region operation group of planes are washed to notebook data; And
The financial cost interest analysis that is based upon the said specific region operation group of planes of independently special course line customization comes the calculating optimum Clean after every.
19. method according to claim 18 is characterized in that, said data are relevant with single gas-turbine unit model.
20. method according to claim 18 is characterized in that, a said region operation group of planes and the said aircraft that starts a group of planes family operation group of planes to comprise single type.
CN2009801448440A 2008-11-06 2009-11-06 Engine wash system and method Pending CN102307679A (en)

Applications Claiming Priority (9)

Application Number Priority Date Filing Date Title
US11208008P 2008-11-06 2008-11-06
US61/112080 2008-11-06
US61236609A 2009-11-04 2009-11-04
US12/612,355 US20110108062A1 (en) 2008-11-06 2009-11-04 Method of washing a gas turbine engine
US12/612349 2009-11-04
US12/612355 2009-11-04
US12/612366 2009-11-04
US12/612,349 US20110083705A1 (en) 2008-11-06 2009-11-04 Engine wash system
PCT/US2009/063463 WO2010054132A2 (en) 2008-11-06 2009-11-06 Engine wash system and method

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AU (1) AU2009313497A1 (en)
CA (1) CA2742109A1 (en)
WO (1) WO2010054132A2 (en)

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AU2009313497A8 (en) 2011-11-17

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