fig1 shows a plasma spray nozzle 1 in longitudinal section . the plasma spray nozzle 1 has , on its inside , an elongate inner channel 4 with a longitudinal axis 22 , in which 4 a plasma is generated and into which 4 powder is injected through at least one hole 7 . the inner channel 4 is formed so that it is longer than the divergent region 16 , and in particular comprises 60 %, more particularly 75 %, of the total length . there is a divergent part 16 at the end 19 of the plasma spray nozzle 1 , so that the inner cross section of the inner channel 4 increases toward the exit or end 19 . the outer diameter of the end 28 of the nozzle 1 , which lies opposite the divergent part 16 , is preferably more than the outer diameter at the end 19 of the divergent region 16 . this means that the mass per axial length is greater at the end 28 . the powder injection is carried out internally , i . e . before the divergent region 16 . it may take place through one hole 7 ( fig3 ) or through several holes 7 ′, 7 ″, 7 ′″ ( fig2 ). the distance between the at least one hole 7 , 7 ′, 7 ″, 7 ′″ and the end 19 of the nozzle 1 is preferably at least 60 %, in particular at least 70 %, more particularly 80 % of the total length l of the nozzle 1 . at the start of the divergent part 16 , there is preferably a shoulder 25 ( fig1 , 4 ) which guides the electric arc of the plasma toward the inner channel 4 . the shoulder 25 constitutes a non - constant or discontinuous transition 25 to the divergent region 16 . there is preferably an edge at the transition 25 from the inner channel 4 with a constant cross section to the divergent region 16 . the shoulder 25 preferably extends perpendicularly to the longitudinal axis 22 of the inner channel 4 . it is also possible for there to be no shoulder 25 ( fig5 ). cooling fins 10 are preferably provided externally along the flow direction for the plasma spray nozzle 1 , that is to say parallel to the longitudinal axis 22 of the nozzle 1 or of the channel 4 ( fig4 ). the outer diameter of these 10 may exceed the outer diameter at the end 19 of the divergent region 16 . a sealing ring 13 is preferably arranged between the cooling fins 10 ( fig4 ). the powder is delivered into the channel 4 of the plasma spray nozzle 1 not through one , but in particular through two holes , particularly through three holes 7 , 7 ′, 7 ″, which are preferably distributed uniformly around the circumference of the inner channel 4 . owing to this arrangement of triple injection , the injection of the powder can be controlled accurately in relation to the jet , and the pass spacing , i . e . the spacing between runs over the component to be coated , can be at least doubled , the spray spot being kept constant in the same position so that the coating time is reduced significantly . except for the inner channel 4 and the powder injection holes 7 , 7 ′, 7 ″, 7 ′″, the nozzle 1 is formed solidly . the at least one hole 7 has a taper 8 at the end , i . e . close to where it enters the inner channel 4 , in order to inject into the plasma jet in a controlled way . fig7 shows a perspective view of a rotor blade 120 or guide vane 130 of a turbomachine , which extends along a longitudinal axis 121 . the turbomachine may be a gas turbine of an aircraft or of a power plant for electricity generation , a steam turbine or a compressor . the blade 120 , 130 comprises , successively along the longitudinal axis 121 , a fastening zone 400 , a blade platform 403 adjacent thereto as well as a blade surface 406 and a blade tip 415 . as a guide vane 130 , the vane 130 may have a further platform ( not shown ) at its vane tip 415 . a blade root 183 which is used to fasten the rotor blades 120 , 130 on a shaft or a disk ( not shown ) is formed in the fastening zone 400 . the blade root 183 is configured , for example , as a hammerhead . other configurations such as a firtree or dovetail root are possible . the blade 120 , 130 comprises a leading edge 409 and a trailing edge 412 for a medium which flows past the blade surface 406 . in conventional blades 120 , 130 , for example solid metallic materials , in particular superalloys , are used in all regions 400 , 403 , 406 of the blade 120 , 130 . such superalloys 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 120 , 130 may in this case be manufactured by a casting method , also by means of directional solidification , by a forging method , by a machining method or combinations thereof . workpieces with a single - crystal structure or single - crystal structures are used as components for machines which are exposed to heavy mechanical , thermal and / or chemical loads during operation . such single - crystal workpieces are manufactured , for example , by directional solidification from the melts . these are casting methods in which the liquid metal alloy is solidified to form a single - crystal structure , i . e . to form the single - crystal workpiece , or is directionally solidified . dendritic crystals are in this case aligned along the heat flux and form either a rod crystalline grain structure ( columnar , i . e . grains which extend over the entire length of the workpiece and in this case , according to general terminology usage , are referred to as directionally solidified ) or a single - crystal structure , i . e . the entire workpiece consists of a single crystal . it is necessary to avoid the transition to globulitic ( polycrystalline ) solidification in these methods , since nondirectional growth will necessarily form transverse and longitudinal grain boundaries which negate the beneficial properties of the directionally solidified or single - crystal component . when directionally solidified structures are referred to in general , this is intended to mean both single crystals which have no grain boundaries or at most small - angle grain boundaries , and also rod crystal structures which , although they do have grain boundaries extending in the longitudinal direction , do not have any transverse grain boundaries . these latter crystalline structures are also referred to as directionally solidified structures . such methods are known from u . s . pat . no . 6 , 024 , 792 and ep 0 892 090 a1 . the blades 120 , 130 may also have coatings against corrosion or oxidation , for example mcralx ( m is at least one element from the group 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 )). such alloys are known from ep 0 486 489 b1 , ep 0 786 017 b1 , ep 0 412 397 b1 or ep 1 306 454 a1 . a protective aluminum oxide layer ( tgo = thermally grown oxide layer ) is formed on the mcralx coating ( as an interlayer or as the outermost coat ). the coating composition preferably comprises co - 30ni - 28cr - 8al - 0 . 6y - 0 . 7si or co - 28ni - 24cr - 10al - 0 . 6y . besides these cobalt - based protective coatings , it is also preferable to use nickel - based protective coatings 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 . on the mcralx , there may furthermore be a thermal barrier coating , which is preferably the outermost coat and consists for example of zro 2 , y 2 o 3 — zro 2 , i . e . it is not stabilized or is partially or fully stabilized by yttrium oxide and / or calcium oxide and / or magnesium oxide . rod - shaped grains are produced in the thermal barrier coating by suitable coating methods , for example electron beam deposition ( eb - pvd ). other coating methods may be envisaged , for example atmospheric plasma spraying ( aps ), lpps , vps or cdv . the thermal barrier coating may comprise porous , micro - or macro - cracked grains for better thermal shock resistance . the thermal barrier coating is thus preferably more porous than the mcralx coating . refurbishment means that components 120 , 130 may need to be stripped of protective coatings ( for example by sandblasting ) after their use . the corrosion and / or oxidation layers or products are then removed . optionally , cracks in the component 120 , 130 are also repaired . the component 120 , 130 is then recoated and the component 120 , 130 is used again . the blade 120 , 130 may be designed to be hollow or solid . if the blade 120 , 130 is intended to be cooled , it will be hollow and optionally also comprise film cooling holes 418 ( indicated by dashes ).