Patent Application
20160304262
The invention relates to a shipment packaging for elongate components, in particular turbine blades or vanes.
Elongate components such as turbine blades or vanes are sent incorporated together with the rotor of the turbine.
During retrofitting, turbine blades or vanes are refurbished and sent back again to technical installations throughout the world. These may also be new turbine blades or vanes which replace old ones, or refurbished turbine blades or vanes.
The turbine blades or vanes have protective layers which should not be damaged during transportation.
Therefore, it is an object of the invention to solve the aforementioned problem.
The object is achieved by a shipment packaging as claimed in the claims.
The advantage consists in the flexibility of the reception of various types of components.
The dependent claims list further advantageous measures which can be combined with one another, as desired, in order to obtain further advantages.
The shipment packaging as claimed in the claims can be improved in each case alone or in any desired combination by:
In the figures:
The description and the drawing represent only exemplary embodiments of the invention.
The elongate components can be ring segments or combustion chamber components of gas turbines or preferably turbine blades or vanes 120, 130, in respect of which the invention is only explained in more detail by way of example.
The blades or vanes 120, 130 which are packaged and sent can be blades or vanes of gas turbines, steam turbines or aircraft turbines.
Similarly, the shipment packaging 1 is suitable for transportation within a plant or between suppliers and the plant.
The blades or vanes 120, 130 can be guide vanes or rotor blades from the first, second, third or fourth row of turbines or from all rows of a turbine.
In this case, a distinction is made between rotor blades and guide vanes, with the guide vanes 130 generally comprising an upper and a lower platform. The rotor blades 120 often comprise only a lower platform 403, however.
The outer packaging 4 preferably consists of HDPE and preferably comprises runners 6, in particular three runners 6, on the outside on the base. Base means bottom.
For identifying the shipment unit, the outer packaging 4 preferably likewise comprises a self-adhesive document pocket on the outside.
For the shipment packaging, there is an outer cover (not shown), which suitably covers the outer packaging 4 at the top. Outer cover means top.
The shipment packaging 1 preferably has a flame-retardant design.
At least one inner packaging 10′, 10″, 10′″, . . . , which is shown in
It is preferable that the inner packaging 10′, 10″, 10′″, . . . can be inserted into the outer packaging 4 in a plurality of layers, as shown in
The turbine components 120, 130 are arranged individually or as a pair in a compartment 25′, 25″, . . . of a plug-in divider 13′ (grid divider), but always in such a way that the components 120, 130 do not touch one another.
The plug-in dividers 13′, 13″, 13′″ preferably consist of PP trilaminate.
There are preferably no more than two components 120, 130 in each compartment 25′, 25″.
The blades or vanes 120, 130 are held, preferably fixed, standing in the compartment 25′, 25″ . . . .
At the base, the compartments 25′, 25″ preferably each comprise a receptacle 19, 22, into which the turbine component 120, 130 is introduced. The receptacle 19, 22 (
The receptacles 19, 22 (
In this example, the blades or vanes 120, 130 are fixed standing in a compartment 25′, 25″ by the receptacle 19, 22.
In each compartment 25′, 25″, there is preferably a receptacle 19 for turbine blades or vanes of the same type. However, various receptacles 19, 22 for various turbine blades or vanes 120, 130 may be present in a plug-in divider 13′.
A receptacle 19, 22 can receive two blades or vanes 120, 130, but can also be equipped only with one blade or vane 120, 130 (
The receptacle 19, 22 (
In the case of a rotor blade 120, the blade receptacle 19 has a depression 19′, which can preferably be formed in accordance with the blade root 400, preferably like a fir tree, and can preferably be pushed from the side into the blade receptacle 19. The blade receptacle 19 thus has a lateral opening 19″ and an upper opening 19′″.
The blade receptacle 19 (
The turbine component 120 (or a plurality thereof) is preferably firstly inserted into the receptacle 19 and then introduced together therewith into the compartment 25′, 25″ of the plug-in divider 13′.
In the case of guide vanes 130 having two platforms, the guide vane 130 is placed from above into an opening 22′ in the vane receptacle 22. The vane receptacle 22 thus preferably has only an upper opening 22′.
The blade or vane platforms 403 are preferably arranged within the receptacle 19, 22, i.e. the components 120, 130 do not protrude beyond the receptacles 19, 22. A plug-in divider cover 16 is preferably placed on the plug-in divider 13′ and preferably additionally fixes the turbine blade or vane 120, 130. The plug-in divider cover 16 is preferably only a plate. The fixing means 17 are preferably provided by a layer of a foam (see also
The inner packaging 10′ therefore comprises at least: a plug-in divider 13′, receptacles 19, 22 and various covers (
The fixing means 17 are formed by a plurality of cuboids or cubes 17′, 17″, which fit exactly into a compartment 25′, 25″, 25′″. Therefore, the plug-in divider cover 16 is preferably supported directly on the plug-in divider 13′, 13″, 13′″, and the fixing means 17′, 17″, . . . protrude into the compartments 25′, 25″, . . . .
In the plane, the plug-in divider 13″ likewise fills the internal space 7 of the outer packaging.
The rotor blade 120 is fixed so as to hang; it is preferably fixed by means of a suspending contoured plate 31. The suspending contoured plate 31 comprises an opening 32, through which the blade 120 is inserted first by way of the blade tip 415.
The suspending contoured plate 31 is preferably made in one piece and is preferably supported on the plug-in divider 13″, or is fixedly connected to the plug-in divider 13″.
The blade 120 is inserted through the suspending contoured plate 31 into the compartment 25′ of the plug-in divider 13″, the platform 403 being supported on the suspending contoured plate 31 or at least protruding beyond the latter 31.
The blade roots 400 protrude out of the contoured plate 31 and can be covered by a protective cover 18, onto which a further plug-in divider can be placed.
The protective cover 18 preferably does not comprise any fixing means.
Since the main blade or vane part 406 of the turbine blade or vane 120, 130 is twisted, the opening 32 in the suspending contoured plate 31 is accordingly wider than the cross section of the main blade or vane part 406, such that, upon insertion of the blade 120, it guides the main blade part 406 into a defined end position, and holds it there.
A receptacle 22′″″, which fixes the end of the turbine blade 120, is preferably present at the end of the compartment 25′. The receptacle 22′″″ is preferably foam-like.
The guide vanes 130 are fixed standing within a plug-in divider 13′″.
At the base of the compartment 25′, there is likewise a receptacle 22″, preferably made of a foam, into which the guide vane 130 is inserted from above. The receptacle 22″ comprises only an upper opening 22′″.
A contoured plate 37 is then placed onto the plug-in divider 13′″.
The contoured plate 37 preferably comprises at least one opening 39, which encloses the upper platform of the turbine blade 120 and thereby stabilizes the other end of the turbine vane 130 at the top.
Here, a protective cover (as in
The turbine components 120, 130 are arranged individually or as a pair in a compartment 25′, 25″ of the plug-in divider 13′, 13″, but always in such a way that the components do not touch one another.
The main rotor blade part 406 stands vertically in the compartment 25′, i.e. the receptacle 50 is adapted accordingly and has an obliquely running surface. Vertical means: the longitudinal axis of the turbine blade 130 stands vertically on the base in the plug-in divider 13′″.
Lying means that the longitudinal axis runs parallel to the base of the plug-in divider (
A lower receptacle 50 and an upper receptacle 53 are present in the compartment 25′ and encompass the turbine part 120 at the ends thereof, here the platforms 403.
The receptacle 53 is effectively a specially preformed fixing means 17′, 17″, . . . as per
Here, it is likewise possible for a plug-in divider cover 16 to be used.
The receptacles 50, 53 can be in the form of separate modules of the inner packaging 10′, 10″, . . . , or else can be arranged fixedly in the compartment 25′ or fastened to the plug-in divider cover 16 (53 on 16).
In
To this end, two lateral receptacles 41, 44 are present.
The lateral receptacles 41, 44 must not touch one another in the compartment 25′, 25″, . . . .
In a single plug-in divider 13′, . . . , components 120, 130 can be arranged lying (
The shipment packaging 1 can comprise a plurality of layers of plug-in dividers 13′, 13″, 13′″ with a plug-in divider cover 16, a protective cover 18 or contoured plates 31.
Similarly, by virtue of separated blocks 47′, 47″ on the side of an insert 49 which directly faces the outer cover, the pressure of the outer cover can preferably be passed onto the plug-in dividers 13′, 13″, . . . , so that the latter cannot move. The insert 49 is preferably used only once at the very top.
The outer cover is preferably tied to the outer packaging 4 by straps.
Technical documents and accompanying papers can be shipped at the same time between the blocks 47′, 47″, the blocks 47′, 47″ being arranged in such a way that they delimit an area for the documents and hold the documents in the plane.
The plug-in dividers 13′, 13″ are known in terms of structure and assembly from the prior art.
The extent of the plug-in dividers 13′, 13″, . . . in the plane is such that it fits flush into the internal space 7 of the outer packaging 4.
Here, use is made of reinforcements 60 for the plug-in dividers 13′, 13″, . . . of the plug-in dividers 13′, 13″, . . . already described above.
The reinforcements 60 preferably extend over the entire width or depth of the plug-in divider 13′ and, like the elements of the plug-in divider 13′, similarly have a plate-like form, but are not so high, so that they extend over the entire depth of the plug-in divider 13′.
The reinforcements 60 have appropriate indentations so that they can be pushed into corresponding indentations in the plug-in divider 13′, such that the topmost edge of the reinforcement 60 preferably terminates with the topmost edge of the plug-in divider 13′.
Therefore, the side walls of the compartments 25′, 25″, . . . can buckle to a lesser extent and are more rigid.
The turbomachine may be a gas turbine of an aircraft or of a power plant for generating electricity, a steam turbine or a compressor.
The blade or vane 120, 130 has, in succession along the longitudinal axis 121, a securing region 400, an adjoining blade or vane platform 403 and a main blade or vane part 406 and a blade or vane tip 415.
As a guide vane 130, the vane 130 may have a further platform (not shown) at its vane tip 415.
A blade or vane root 183, which is used to secure the rotor blades 120, 130 to a shaft or a disk (not shown), is formed in the securing region 400.
The blade or vane root 183 is designed, for example, in hammerhead form. Other configurations, such as a fir tree or dovetail root, are possible.
The blade or vane 120, 130 has a leading edge 409 and a trailing edge 412 for a medium which flows past the main blade or vane part 406.
In the case of conventional blades or vanes 120, 130, by way of example solid metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade or vane 120, 130.
Superalloys of this type are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949.
The blade or vane 120, 130 may in this case be produced by a casting process, by means of directional solidification, by a forging process, by a milling process or combinations thereof.
Workpieces with a single-crystal structure or structures are used as components for machines which, in operation, are exposed to high mechanical, thermal and/or chemical stresses.
Single-crystal workpieces of this type are produced, for example, by directional solidification from the melt. This involves casting processes in which the liquid metallic alloy solidifies to form the single-crystal structure, i.e. the single-crystal workpiece, or solidifies directionally.
In this case, dendritic crystals are oriented along the direction of heat flow and form either a columnar crystalline grain structure (i.e. grains which run over the entire length of the workpiece and are referred to here, in accordance with the language customarily used, as directionally solidified) or a single-crystal structure, i.e. the entire workpiece consists of one single crystal. In these processes, a transition to globular (polycrystalline) solidification needs to be avoided, since non-directional growth inevitably forms transverse and longitudinal grain boundaries, which negate the favorable properties of the directionally solidified or single-crystal component.
Where the text refers in general terms to directionally solidified microstructures, this is to be understood as meaning both single crystals, which do not have any grain boundaries or at most have small-angle grain boundaries, and columnar crystal structures, which do have grain boundaries running in the longitudinal direction but do not have any transverse grain boundaries. This second form of crystalline structures is also described as directionally solidified microstructures (directionally solidified structures).
Processes of this type are known from U.S. Pat. No. 6,024,792 and EP 0 892 090 A1.
The blades or vanes 120, 130 may likewise have coatings protecting against corrosion or oxidation e.g. (MCrAlX; M is at least one element selected from the group consisting of iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and/or silicon and/or at least one rare earth element, or hafnium (Hf)). Alloys of this type are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1.
The density is preferably 95% of the theoretical density.
A protective aluminum oxide layer (TGO=thermally grown oxide layer) is formed on the MCrAlX layer (as an intermediate layer or as the outermost layer).
The layer preferably has a composition Co-30Ni-28Cr-8Al-0.6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y. In addition to these cobalt-based protective coatings, it is also preferable to use nickel-based protective layers, such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1.5Re.
It is also possible for a thermal barrier coating, which is preferably the outermost layer, to be present on the MCrAlX, consisting for example of ZrO2, Y2O3—ZrO2, i.e. unstabilized, partially stabilized or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide.
The thermal barrier coating covers the entire MCrAlX layer.
Columnar grains are produced in the thermal barrier coating by suitable coating processes, such as for example electron beam physical vapor deposition (EB-PVD).
Other coating processes are possible, e.g. atmospheric plasma spraying (APS), LPPS, VPS or CVD. The thermal barrier coating may include grains that are porous or have micro-cracks or macro-cracks, in order to improve the resistance to thermal shocks. The thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
Refurbishment means that after they have been used, protective layers may have to be removed from components 120, 130 (e.g. by sand-blasting). Then, the corrosion and/or oxidation layers and products are removed. If appropriate, cracks in the component 120, 130 are also repaired. This is followed by recoating of the component 120, 130, after which the component 120, 130 can be reused.
The blade or vane 120, 130 may be hollow or solid in form. If the blade or vane 120, 130 is to be cooled, it is hollow and may also have film-cooling holes 418 (indicated by dashed lines).
This application is a divisional of U.S. Ser. No. 13/512,991 filed on May 31, 2012 which is the US National Stage of International Application No. PCT/EP2009/066343, filed Dec. 3, 2009 and claims the benefit thereof. All of the applications are incorporated by reference herein in their entirety.
| Number | Date | Country | |
|---|---|---|---|
| Parent | 13512991 | Aug 2012 | US |
| Child | 15190783 | US |
