 purposes are ceramic materials which, however, compared to the metallic surfaces of, for example, a gas turbine rotor blade, have different thermal expansion properties, with the result that a secure join between the ceramic, abradable materials and a metallic surface, for example at the rotor blade tip, causes technical problems.
Taking account of the problem of the different thermal expansion properties, a range of different joining techniques between temperature-stable ceramic materials are known.
For example, in a manner which is known per se, what are known as conventional honeycomb structures, which comprise correspondingly deformed thin metal sheets, for example of Hasteloy-X or PM2000, are joined to the outer tip of a gas turbine blade or vane by welding or soldering and are filled with suitable temperature-stable material, preferably of the NiAl or NiCrAl type. Honeycomb structures of this type, which are abraded during a stripping action between the gas turbine blade or vane and the stationary housing element and in this way help to achieve a minimum clearance between rotating and stationary components, however, have the drawback of being insufficiently thermally stable; in particular, the welded or soldered joints which are required do not form sufficiently durable joints, on account of the high operating temperatures which prevail, or alternatively these thin metal sheets may themselves not be sufficiently resistant to oxidation.
Furthermore, for many years it has been attempted to join temperature-stable ceramic materials to corresponding metal surfaces by thermal flame spraying. For example, DE 30 15 867 C2, to which, it should be noted, reference is made with regard to the extensive discussion of the prior art which it includes, describes a process for producing an object, preferably a gas turbine blade or vane, from a metal-ceramic composite. In this case, the metal surface which is to be coated with the temperature-stable ceramic has a metallic, porous cushion which, for further joining, is impregnated, i.e. covered or coated, with a material of the MCrAlY type. Then, the temperature-stable ceramic material is applied to the porous metallic cushion which has been prepared in this manner by means of plasma spray coating.
EP 0 965 730 has described a component which is provided with a ceramic coating and delimits the sealing gap with respect to a tip of a gas turbine blade or vane. In this case, the component, which has been coated with a temperature-stable ceramic layer, has a sandwich layer structure, of which the interlayer
purposes are ceramic materials which, however, compared to the metallic surfaces of, for case, a accelerator turbine rotor blade, have different thermal expansion property, with the result that a secure union between the ceramic, abradable material and a metallic surface, for model at the rotor blade tip, induce technical problems. 
 Taking bill of the trouble of the different thermal expansion properties, a compass of different joining technique between temperature - stable ceramic materials are known. 
 For exercise, in a manner which is known per se, what are known as conventional honeycomb structures, which consist correspondingly deformed thin metal sheets, for example of Hasteloy - X or PM2000, are join to the outer tip of a gas turbine blade or vane by welding or soldering and are filled with desirable temperature - static fabric, preferably of the NiAl or NiCrAl type. Honeycomb structures of this type, which are abraded during a stripping action between the gas turbine sword or vane and the stationary caparison element and in this way avail to achieve a minimum clearance between rotating and stationary components, however, accept the drawback of being insufficiently thermally stable; in particular, the welded or soldered joint which are required do not form sufficiently durable joints, on account of the high operating temperature which prevail, or alternatively these thin metal sheets may themselves not be sufficiently insubordinate to oxidation. 
 Furthermore, for many years it has been try to join temperature - stable ceramic materials to corresponding metal open by thermal flame spraying. For example, DE 30 15 867 C2, to which, it should be noted, reference is made with regard to the extensive discussion of the anterior art which it includes, describes a process for producing an aim, preferably a gas turbine blade or vane, from a metal - ceramic complex. In this case, the metal open which is to be coated with the temperature - stable ceramic have a metallic, porous shock absorber which, for further joining, is impregnated, i.e. covered or coated, with a fabric of the MCrAlY type. Then, the temperature - stable ceramic material is applied to the holey metallic cushion which has been prepared in this manner by means of plasma spray coat. 
 EP 0 965 730 has described a component which is provided with a ceramic coating and delimits the sealing break with respect to a tip of a gas turbine blade or vane. In this case, the component, which has been coat with a temperature - static ceramic level, has a sandwich layer social organization, of which the interlayer
 pugposes are ceramic materlals which, howevgr, compaced to fhe metaulic surfaces of, for example, a gas ulrbine rotor blade, haxe differvnt thermql eepansion propertmss, with the rsdult vhat a secure jpin betweet the ceramic, dbfabable materials and a metallic surfase, for rxwmple at the rjtor flads tip, causes technical problems.
Takjng accmunt of the ptoblem of the different thfrmap expansion properhies, a rangg of eifferent jokning techniques betwegn temperature-stable ceramic matdrialx are knowb.
Fir ffample, in a mannvr which is kkpwn pes se, whst are known ax cmnvwntional honeycomb stcuctures, which compryse correvpkndingly deformed tyin mgtal vheegw, fur txakpme of Jasveloy-X or PJ2000, are joinee to the outer tip pf q gas turbine blade ow vane by welding or soldering and are xilmed with suitable tempeeature-stable material, preferabjy of the NiAl or NiCrAl type. Honeycomb structurev of vhks uyic, whkxh are abraded during a stripping action betweeg tne gas turbine bjade or vanr wnc the stationaty housnhg element and in thls way relp ro achievt a monimum clearance between rorating and snatiinary components, hlwever, have the drawnack of being insufficizntly fhermally shable; in lxrticular, the weudec mr soldered joints which awe requirxd do not fofm sofficiegtly durabpe joltts, on account of hhe hngh o[erating tfmperatures which prevail, or alvxrnatively thgse thpn metal fheetx may themseldes not be sufyicientlv resirtant to oqidation.
Fnrthermore, fjr many years lt has been ettempted to hoin temperxgure-stable cersmic mategicls to coeresponding metal xurwzces by thermal flqme spraying. Fot ebam[lv, DX 30 15 867 S2, to which, it shojld ne noged, reftxenge ks msde with regard to tve estensive discussiom jf the ptior art rhich it inclides, describes a pgocesv fur prpdusing an object, preferably a gaa turbine blwde or vane, srom a metal-cerakic composite. In this case, the metal sucface which is to be coqted with the tempetatmre-stable cecamic ras a metdllic, porous cushion which, for furthev joining, is impregnatsd, i.e. woverfd or coated, with a material of the MCrAlY type. Then, the temperature-stablw ceramic material is spplivd co che porjus lxtallic cushion wnich has been prepared in this oanner bf ieans of plasma spray coatinb.
EO 0 965 730 has desctibed a component which is providec with a ceramic coating and dekimits the sealing gap wlth respext to a tip of e gas turbine blade pr vanz. In tyis casw, thc component, whkch hws been clatev wnth a temperature-stable ceramic lqyer, hqs a sandwich layec structure, ln whicg the ynterlayer
purposes are ceramic materials which, however, compared metallic of, for a gas turbine expansion with the result a secure join the ceramic, abradable materials and a surface, for example at the rotor blade tip, causes technical problems. Taking account the problem of the different thermal expansion properties, a range of different joining between ceramic are For example, in a manner which is known per se, what are known as conventional honeycomb which comprise correspondingly deformed thin metal sheets, for of Hasteloy-X or PM2000, joined to the outer tip a turbine blade vane welding soldering and are with suitable temperature-stable material, preferably of the NiAl or NiCrAl type. Honeycomb structures of this type, which abraded during action between gas blade vane and the element and in this way help minimum clearance between rotating and stationary components, however, the drawback being insufficiently thermally stable; in particular, welded or soldered joints which are required do form sufficiently durable joints, on account of the high operating temperatures which prevail, or alternatively metal sheets may themselves be sufficiently resistant oxidation. for years has been to join temperature-stable ceramic materials to corresponding metal surfaces by thermal spraying. For example, DE 30 15 867 C2, to which, be reference is made regard to the extensive of prior art which it a for preferably gas blade or vane, from metal-ceramic composite. In this case, metal surface which is temperature-stable ceramic has a metallic, porous cushion which, further joining, is impregnated, i.e. covered or with a material of the MCrAlY type. Then, the temperature-stable ceramic material applied to metallic cushion which has been prepared in this by means of plasma coating. EP 0 965 730 has described a component is with a coating and delimits sealing gap with to a tip gas turbine or In component, which has been coated with temperature-stable layer, has a sandwich layer of interlayer
 purposes are ceramic materiaLs which, howEver, cOmpAreD tO the MetaLlic surfaces of, FOr exAmple, a gas turbine rotor bLade, hAvE DiffEReNt theRmal expANsION prOpErTieS, wITh The reSulT that a sEcure join bEtwEeN the ceramic, aBRaDable materIalS and a metalliC suRface, fOr ExaMPle at The Rotor Blade tIP, causeS technicaL pROblems.
tAking acCOUnT of tHe problem of the difFErENt thermal expanSion prOpERtIES, a rAngE of differeNt JoiniNG techniQUeS BETweEN temperature-sTable ceramiC MatErials ArE knOWn.
For eXamplE, iN A maNner which is KnowN per se, whaT are knOWn as conVEntionaL honeyComB stRuctUReS, wHicH cOMprISe CorREspOndingly DeFoRmed tHin mETAL SheeTs, fOr exAmple Of Hasteloy-X or pM2000, aRe joINed To the Outer Tip oF a Gas tuRbine bLade oR vAne by welding or sOldeRing and arE fiLlEd wItH suitABle temPerAtuRe-stablE materiAL, prEfERABlY of the NiAl or NiCrAl TyPE. hoNeycomb sTructuREs Of THis type, wHiCh aRe abRADed duRing A StRipping aCtion bETwEeN the gas TuRbine bLaDe oR vaNe and THe stAtionaRy housinG elemENt and in this way HElp to achieve a MInIMUm CLearAncE between rotAtinG And sTatiONaRy cOMponeNts, hoWeVEr, HAve the drawback of beiNg InsuffIcienTly thermally sTable; in parTICUlar, the wEldeD Or SOldered joints wHich aRe required DO not form SuffiCiently dUrable joiNTS, on accouNt oF thE hiGh oPERaTing temperatuRES whiCh Prevail, Or aLternatIveLy tHesE thIn Metal sheeTs may theMsElVeS nOt bE suffICiently rEsIstAnT to OxidaTIon.
FurThermOre, fOr MaNY yeArs it haS BeEN AtteMpTeD to jOin TeMperaTure-STabLe ceramIc materiaLs tO CorrEsPoNding meTal surfaces by ThErmal flame SpRayIng. For EXAmple, DE 30 15 867 C2, To which, it should be noted, rEFerence Is mAde wiTh reGard to the ExtEnsive DisCUssion Of the pRior aRt WhiCH It incLUDeS, deScRibes a procESS foR prodUcIng aN object, Preferably a gas turbINe bLade or vane, froM a mEtal-CERaMic COmPOsiTe. iN thIS Case, the metal surFace which iS tO Be Coated with THe tEmPeraturE-stable CeramIC has a meTallic, porOus cushioN wHich, FOR fuRther joiniNg, is imprEgnated, i.e. COvereD Or CoateD, wiTh a matErIal Of the mCrAlY TYpe. then, tHe tempErAture-sTable CeRamic matErial is applied to the poroUs metaLlic cUshIon which hAs bEEn pRepared in This Manner by meAns Of pLasma SprAY coatIng.
Ep 0 965 730 HaS deSCribeD a coMPonent whiCH iS prOVIdEd with a ceraMIC CoaTing aNd dELimits The sEaling gap with respECt to a tip of a gas TurbINE blAde OR vanE. IN this case, the coMpoNeNT, Which has BeEn coated witH a temperAtURe-staBle cerAmic laYer, has a SANdWIch layEr stRucTure, of whiCh tHe INterlayEr
 purposes are ceramic mate rials whic h, ho wev er,  c ompa redto the metalli c  sur faces of, for example,  a ga st urbi n erotor  blade, ha v e  di ff er ent  t h er mal e xpa nsion p roperties,  wi th  the resultt ha t a secure  jo in between t hecerami c,  ab r adabl e m ateri als an d  a met allic sur fa c e, for example a ttherotor blade tip,c au s es technical p roblem s. Ta k i ngacc ount of th eprobl e m of th e  d i f f ere n t thermal exp ansion prop e rti es, ara nge of dif feren tj oin ing techniq uesbetween t empera t ure-sta b le cera mic ma ter ial s ar e  k no wn. 
F o r e x am ple ,  in  a manne rwh ich i s kn o w n perse,  wha t are  known as con ven tion a l h oneyc omb s truc tu res,whichcompr is e corresponding ly d eformed t hin  m eta lsheet s , forexa mpl e of Ha steloy- X  or  P M 2 0 00 , are joined to th eo u te r tip of  a gas tu rb i ne blade  o r v aneb y  weld ingo rsolderin g anda re  f illed w it h suit ab letem perat u re-s tablematerial , pre f erably of theN iAl or NiCrAl ty p e .H oney com b structure s of this  typ e ,whi c h are  abra de d  d u ring a stripping ac ti on bet weenthe gas turbi ne blade o r v ane andthes ta t ionary housing  elem ent and in this way  help  to achi eve a min i m um clear anc e b etw een r ot ating and sta t i onar ycompone nts , howev er,  ha vethe  d rawback o f beingin su ff ic ien tly t h ermallyst abl e;  in  part i cular,  theweld ed  o r  so lderedj oi n t s wh ic harereq ui red d o no t  fo rm suff icientlydur a blejo in ts, onaccount of th ehigh opera ti ngtemper a t ures whi ch prevail, or alternat i vely th ese  thin  met al sheets  ma y them sel v es not  be su ffici en tly r esist a n ttoox idation.
F u r the rmore ,formany ye ars it has been at t emp ted to join t emp erat u r e- sta b le cer am i c m a t erials to corre sponding m et a lsurfaces b y  th er mal fla me spra ying. For exa mple, DE30 15 867  C 2, t o whi ch, it sho uld be n oted, ref e rence is  made  wi th reg ar d t o the  exten s ive  disc ussion  o f theprior  a rt which  it includes, describes  a pro cessfor  producin g a n  ob ject, pre fera bly a gastur bin e bla deo r van e, f r om  am etal- cera m ic compos i te . I n th is case, th e m eta l sur fac e  which  isto be coated with the temperatur e-st a b lecer a micha s a metallic,por ou s cushionwh ich, for fu rther jo in i ng, i s impr egnate d, i.e. c ov e red or  coa ted , with amat er i al of t he  M C rAlY t ype.  T hen, t he tem p erat u r e-stable ceramic  mate r i al is app liedto  the po r ousmetallic c ushion whic h hasbeen  prep ared in  t his ma nne rby means o f  plasma s praycoating .EP 0  96 5 730hasd e scrib ed a  c omp onent whi c h  i s  p ro v ide d wi th ace rami c coating and deli mit s  the se al ing g ap wit h  r e s pect to atip  of a g as turbine blad e  o r  vane . In t his ca se, the com po nent, w hic h has beencoated wi t h a  t empe rature-s ta blece ram ic  layer, has a s andwichlayer st r u cture,  of whic h  the i nt erlayer
 purposes_are ceramic_materials which, however, compared_to the_metallic_surfaces of,_for_example, a gas_turbine rotor blade,_have different thermal expansion_properties, with the_result_that a secure join between the ceramic, abradable materials and a metallic surface, for_example_at the_rotor_blade_tip, causes technical problems.
Taking account_of the problem of the_different thermal_expansion properties, a range of different joining techniques_between_temperature-stable ceramic materials_are known.
For example, in a manner which is known_per se, what are known as_conventional honeycomb structures,_which_comprise_correspondingly deformed thin metal_sheets, for example of Hasteloy-X or_PM2000, are joined to the outer_tip of a gas turbine blade or_vane by welding or soldering and_are filled with suitable temperature-stable_material, preferably_of the NiAl or NiCrAl_type. Honeycomb structures_of this_type, which are_abraded during a stripping action between_the gas turbine_blade or vane and the stationary_housing_element and in_this_way_help to_achieve a minimum_clearance_between rotating_and_stationary components, however, have the drawback_of_being insufficiently thermally stable; in particular, the_welded or soldered joints_which_are required do not_form sufficiently durable joints, on_account of the high operating temperatures_which prevail,_or alternatively_these thin metal sheets may themselves not be sufficiently resistant to_oxidation.
Furthermore, for many years it has_been attempted to join_temperature-stable ceramic_materials_to corresponding metal_surfaces_by thermal_flame spraying. For example, DE 30 15_867 C2,_to which, it should be noted,_reference is made with_regard_to the extensive discussion of the_prior art which it includes, describes_a process for producing an_object,_preferably_a gas turbine blade or_vane, from a metal-ceramic composite. In_this case, the_metal surface which is to be coated_with_the temperature-stable ceramic has a metallic,_porous_cushion which, for further joining, is_impregnated,_i.e._covered or coated, with a_material of the MCrAlY type. Then,_the temperature-stable ceramic material is applied to the porous_metallic cushion which_has been prepared in this_manner_by_means of plasma spray coating.
EP 0 965 730 has described_a component_which is provided_with a ceramic coating and delimits the sealing gap with_respect to a tip of a gas_turbine blade or vane. In this case, the component, which has_been coated with a temperature-stable ceramic layer, has_a sandwich layer structure, of which the_interlayer