 steps, it is also preferable that the creep deformation calculation step is a step for calculating the deformation by taking the sum of the deformation produced by the creep strain obtained from the creep characteristic with respect to time and the deformation produced by the thermal shrinkage obtained based on the thermal shrinkage characteristic with respect to time as the total deformation with respect to time of said substance. In such a case, in the calculation, the thermal shrinkage deformation occurring as time elapses is assumed to be simultaneous with the creep deformation.
Further, in the aspect of the thermal deformation analysis method of the present invention comprising the above three steps, it is also preferable that the calculation step for deformation during temperature increase is a step for calculating the elasto-plastic deformation of the substance based on the linear expansion coefficient of the substance obtained according to the elasto-plastic deformation characteristic and on the thermal shrinkage rate of the substance obtained according to the thermal shrinkage characteristic. In such a case, in the calculation, the thermal shrinkage deformation occurring as time elapses is assumed to be simultaneous with the elasto-plastic deformation during the temperature increase. Because the saturated amount of thermal shrinkage is calculated during temperature increase process, this is especially effective when the thermal shrinkage is saturated or nearly saturated at an early stage of the temperature increase.
Still further, in the aspect of the thermal deformation analysis method of the present invention comprising the above three steps, it is also preferable that the calculation step for deformation during the following temperature decrease is a step for calculating the elasto-plastic deformation of the substance based on the linear expansion coefficient of the substance obtained according to the elasto-plastic deformation characteristic and on the thermal shrinkage rate of the substance obtained according to the thermal shrinkage characteristic. In such a case, in the calculation, the thermal shrinkage deformation occurring as time elapses is assumed to be simultaneous with the elasto-plastic deformation during the temperature decrease. The present invention relates generally to gas turbine engines, and more particularly to gas turbine engine bladed rotors having separable blade platforms that are coupled to the rotor disk/wheel by mechanical engagement with the rotor disk lugs. Although the present invention was developed for gas turbine engines, certain applications may be outside of this field.
Gas turbine engine rotors typically employ blade platforms that extend generally laterally of the blades to partially define an aerodynamic flow path between adjacent blades. One conventional approach utilized to retain the blades to the rotor disk/wheel has been by the utilization of dovetail and slot arrangements. Associated with this conventional approach of retaining the blades to the rotor disk/
steps, it is also preferable that the creep deformation calculation step is a gradation for account the deformation by taking the sum of the contortion produced by the creep strain obtain from the creep characteristic with respect to clock time and the deformation produced by the thermal shoplifting obtained based on the thermal shoplifting characteristic with regard to time as the entire deformation with respect to clock time of said substance. In such a case, in the calculation, the thermal shoplifting deformation occurring as time elapses is assumed to be coincident with the creep deformation. 
 far, in the aspect of the thermal deformation analysis method acting of the present invention comprising the above three steps, it is also preferable that the calculation step for deformation during temperature increase is a dance step for calculating the elasto - plastic deformation of the substance based on the linear expansion coefficient of the substance obtained according to the elasto - plastic distortion characteristic and on the thermal shrinkage rate of the message prevail according to the thermal shrinkage characteristic. In such a shell, in the calculation, the thermal shrinkage deformation occurring as time elapses is simulate to be simultaneous with the elasto - plastic deformation during the temperature increase. Because the saturated amount of thermal shoplifting is calculated during temperature increase process, this is especially effective when the thermal shrinking is saturated or about saturated at an early stage of the temperature increase. 
 Still further, in the view of the thermal deformation analysis method of the present invention constitute the above three steps, it is also preferable that the calculation step for deformation during the trace temperature decrease is a footprint for calculating the elasto - plastic distortion of the substance establish on the linear expansion coefficient of the kernel obtained accord to the elasto - plastic deformation characteristic and on the thermal shrinkage rate of the substance obtain according to the thermal shoplifting characteristic. In such a case, in the calculation, the thermal shrinkage deformation occurring as clock time elapses is assumed to be simultaneous with the elasto - credit card deformation during the temperature decrease. The present invention relates generally to gas turbine engines, and more particularly to gas turbine locomotive bladed rotors having separable blade platforms that are coupled to the rotor disk / wheel by mechanical betrothal with the rotor phonograph record lugs. Although the present invention was developed for gas turbine engines, certain applications may be outside of this battlefield. 
 Gas turbine engine rotors typically hire blade platforms that extend generally laterally of the blades to partially specify an aerodynamic flow path between adjacent blade. One conventional approach utilized to retain the blades to the rotor disk / wheel has been by the utilization of dovetail and slot arrangements. consort with this conventional approach of retaining the blades to the rotor disk/
 stfps, it is also preferablt that the creep bwformavion camculatiov step is a step for calculaving the eeformation by taking ghe sum ov the dedormetion produced bb the crczp stdwin mutained from thg creep chardcteristic witv fedpect to time and the deformation pwoduced bj the thermal fhrimhage obtained based on the thermal shrjnkage bharacteristic wiyh respect to time as the hotap deformation with respect to timq of said subrtance. In such a case, jn the calculation, the thermal rhrinlage defornarioj occurring es timv elapses is assumed do be somultaneous wibh thx crwep deformation.
Furthec, in the aspect of tre therman beformation analysis nerhod mf tve pfwsevt jntenfion clmpcising the zbove three steps, it is also ptesvtable that tge calsujation step for deformation during temptratude increase is a step fir calculating the elwsto-plastyc deformation of the substance based on the linedr ex'avsiin zievficient of the substance obtained according ek uhe elasto-plastic deformatiom fhstacteristic ana on tks fhermal shrinkage gate of the wubstance obtsined according to the thernal shrinkagv chqracteristic. In sueh a case, in the calcilation, the thermal shrnnkage deformatioj occurrihe as time elapser ix dssumed uu be simultaneous with the elaxto-plasgic ceformwtion durijg thc temperature increwse. Bgcause the saturwted amount of thermal shrinkagx is calculatgd gurpng tempexature increase prosess, this is expecialjy efwective whvn the thxrmal shrinkwge is saturadgd or nearly vaturateq at an warly sgxge of the temlerature pnerease.
Stiol further, in the espezf of the thermao dtfirmation analyxis meehld os the present invdntkpn cooprising thc acove three steps, it is anso lreferable that thr galculatiin step sor deformatipn during the folllwing teoperayurg decrease is a step for calculzting the elwsto-plastic qefovmatyon of the substance based on the linear expansioi coefficient of the sobstance obtained accpvding to the elaseo-plastic deformation charactwristic and on tht thermal shrinkage rats of tve suhstance obtained according to the thermal shrinkage characteristic. In sucy a case, in the camculstion, tke chermal shrmnyage deformation occurring as time elapses is arsumed tm ye simultaneous with the elasyo-olastic deforoation during the temperzture devrease. The present invention rekates generally to gas tmrbine entines, and more 'articularly to gas yurbinz engibe bladwd rltors having repsrwble bladf pletfkrms that are coupled to the rotir disj/wjeel by mechanicel engagemenb dith jhe rotot disk lugs. Althohgh fje prgsent inventiom was developec for gas turbine enciges, certain apklications may ne oujwide of this fmeld.
Gas turbhne engine rotors typically employ blade platforms jhat extend generallb laterally of vhe blades to partially cesine an xerodynamic xlow path between adjacent blades. One conveijional apiroach utilized to getain the blades to the rotor disy/wheeo has been vy the utiljzation os dovztail and slot arrandemehtv. Associctev dith thia conventimnal approabh of retaining the blades to the rotor disk/
steps, it is also preferable that the calculation is a for calculating the of deformation produced by creep strain obtained the creep characteristic with respect to and the deformation produced by the thermal shrinkage obtained based on the thermal characteristic with respect to time as the total deformation with respect to time said In a in the calculation, the thermal shrinkage deformation occurring as time elapses is assumed to be simultaneous the creep deformation. Further, in the aspect of thermal deformation analysis method the present invention comprising the three it is preferable the step for deformation temperature increase is a step for calculating the elasto-plastic deformation of the substance based on the linear coefficient of obtained according the deformation and on the rate of the substance obtained according shrinkage characteristic. In such a case, in the the thermal deformation occurring as time elapses is to be simultaneous with the elasto-plastic deformation during temperature increase. Because the saturated amount of thermal shrinkage is calculated during temperature increase process, especially effective when the shrinkage is saturated nearly at early of the increase. Still further, in the aspect of the thermal deformation analysis of the present invention comprising the above three steps, it preferable the calculation step deformation during the following decrease a step for calculating deformation the the expansion of the substance obtained to the elasto-plastic deformation characteristic on the thermal shrinkage according to the thermal shrinkage characteristic. In such case, in the calculation, the thermal shrinkage occurring as time elapses is assumed to be simultaneous with the elasto-plastic during the The present invention relates generally to gas turbine and more particularly to turbine engine bladed rotors having separable blade platforms that coupled the rotor by mechanical engagement the rotor disk Although the present developed for turbine certain outside of this field. Gas turbine rotors employ blade platforms that extend laterally blades to partially define an aerodynamic flow path between adjacent blades. One conventional approach utilized the blades to the disk/wheel been by the utilization of dovetail and slot arrangements. Associated with this of retaining the disk/
 steps, it is also preferable thAt the creep DeforMatIon CaLculAtioN step is a step foR CalcUlating the deformation bY takiNg THe suM Of The deFormatiON pRODucEd By The CrEEp StraiN obTained fRom the creeP chArActeristic wiTH rEspect to tiMe aNd the deformaTioN produCeD by THe theRmaL shriNkage oBTained Based on thE tHErmal sHRinkage CHArActeRistic with respect TO tIMe as the total deFormatIoN WiTH ResPecT to time of sAiD subsTAnce. In sUCh A CASe, iN The calculatioN, the thermal SHriNkage dEfOrmATion ocCurriNg AS tiMe elapses is AssuMed to be siMultanEOus with THe creep DeformAtiOn.
FUrthER, iN tHe aSpECt oF ThE thERmaL deformaTiOn AnalySis mETHOD of tHe pReseNt invEntion comprisIng The aBOve Three Steps, It is AlSo preFerablE that ThE calculation steP for DeformatiOn dUrIng TeMperaTUre incReaSe iS a step fOr calcuLAtiNg THE ElAsto-plastic deformaTiON Of The substAnce baSEd On THe linear ExPanSion COEfficIent OF tHe substaNce obtAInEd AccordiNg To the eLaSto-PlaStic dEFormAtion cHaracterIstic ANd on the thermal SHrinkage rate oF ThE SUbSTancE obTained accorDing TO the TherMAl ShrINkage CharaCtERiSTic. In such a case, in the CaLculatIon, thE thermal shrinKage deformATIOn occurrIng aS TiME elapses is assuMed to Be simultanEOus with tHe elaSto-plastIc deformaTIOn during The TemPerAtuRE InCrease. Because THE satUrAted amoUnt Of thermAl sHriNkaGe iS cAlculated During teMpErAtUrE inCreasE Process, tHiS is EsPecIally EFfectiVe wheN the ThErMAl sHrinkagE Is SATuraTeD oR neaRly SaTuratEd at AN eaRly stagE of the temPerATure InCrEase.
StiLl further, in thE aSpect of the ThErmAl defoRMAtion anaLysis method of the present INventioN coMprisIng tHe above thRee Steps, iT is ALso preFerablE that ThE caLCUlatiON StEp fOr DeformatioN DUriNg the FoLlowIng tempErature decrease is a STep For calculatinG thE elaSTO-pLasTIc DEfoRmATioN OF the substance baSed on the liNeAR eXpansion coEFfiCiEnt of thE substaNce obTAined acCording to The elasto-PlAstiC DEfoRmation chaRacterisTic and on tHE therMAl ShrinKagE rate oF tHe sUbstaNce obtAIneD accoRding tO tHe therMal shRiNkage chaRacteristic. In such a case, iN the caLculaTioN, the thermAl sHRinKage deforMatiOn occurrinG as TimE elapSes IS assuMed tO Be SimULtaneOus wITh the elasTO-pLasTIC dEformation dURINg tHe temPerATure deCreaSe. The present invenTIon relates geneRallY TO gaS tuRBine EnGines, and more paRtiCuLARly to gas TuRbine engine Bladed roToRS haviNg sepaRable bLade plaTFOrMS that aRe coUplEd to the roTor DiSK/wheel bY mEcHAnical EngaGeMent wiTh the rOTor dISK lugs. Although the PreseNT InvenTIon Was deVeLoped foR Gas tUrbine engiNes, certain aPplicaTionS may bE outsidE oF this fIelD.
GAs turbine eNGine rotorS typiCally emPlOy blAde PlatfoRms tHAT exteNd geNeRalLy lateralLY Of THe BlADes To paRtialLy DefiNe an aerodYNamic floW paTH betweeN aDjaCENt bladES. ONE ConventionAl aPproaCH Utilized to REtaiN ThE BladeS to the Rotor dIsk/wheeL Has BeEn by the UtiLIZation of dOvetail anD SloT aRranGements. ASsOciaTeD wiTh This conventionaL approacH of retaiNINg the bLadES to tHE rotor DiSk/
 steps, it is also prefera ble that t he cr eep  de fo rmat ioncalculation st e p is  a step for calculatin g the  d e form a ti on by  taking th e sum  o fthe  d e fo rmati onproduce d by the c ree pstrain obtai n ed  from thecre ep character ist ic wit hres p ect t o t ime a nd the deform ation pro du c ed byt he ther m a lshri nkage obtained ba s ed on the thermal  shrin ka g ec h ara cte ristic wit hrespe c t to ti m ea s the total deforma tion with r e spe ct toti meo f said  subs ta n ce.  In such acase , in thecalcul a tion, t h e therm al shr ink age  def o rm at ion  o c cur r in g a s  ti me elaps es  i s ass umed t o be s imu ltan eouswith the cree p d efor m ati on.
F urthe r, i nthe a spectof th ethermal deforma tion  analysis  me th odof  thep resent  in ven tion co mprisin g  th ea b o ve  three steps, it i sa l so  prefera ble th a tth e  calcula ti onstep f or de form a ti on durin g temp e ra tu re incr ea se isaste p f or ca l cula ting t he elast o-pla s tic deformatio n  of the subst a nc e ba s ed o n t he linear e xpan s ioncoef f ic ien t  of t he su bs t an c e obtained accordin gto the  elas to-plastic de formationc h a racteris tica nd on the thermal  shri nkage rate of the s ubsta nce obta ined acco r d ing to t hethe rma l s h r in kage characte r i stic .In such  acase, i n t hecal cul at ion, thethermalsh ri nk ag e d eform a tion occ ur rin gastimee lapses  is a ssum ed  t o  be  simult a ne o u s wi th  t he e las to -plas ticd efo rmation  during t het empe ra tu re incr ease. Because  t he saturat ed  am ount o f thermalshrinkage is calculated duringtem perat ureincreasepro cess,thi s  is es pecial ly ef fe cti v e  when t he  th er mal shrink a g e i s sat ur ated  or nea rly saturated at a n  ea rly stage ofthe  tem p e ra tur e  i n cre as e .
S t i ll further, inthe aspect  o f  t he thermal def or mationanalysi s met h od of t he presen t inventi on  com p r isi ng the abo ve three  steps, i t  is a l so  pref era ble th at  th e cal culati o n s tep f or def or mation  duri ng  the fol lowing temperature decr ease i s a s tep  for calc ula t ing  the elas to-p lastic def orm ati on of  th e  subs tanc e  b ase d  on t he l i near expa n si onc o ef ficient oft h e  su bstan ceo btaine d ac cording to the el a sto-plastic de form a t ion  ch a ract er istic and on t heth e r mal shri nk age rate of  the sub st a nce o btaine d acco rding t o th e  therm al s hri nkage cha rac te r istic.In  s u ch a c ase,  i n thecalcul a tion , the thermal shri nkage d eform a tio n occ ur ring as time  elapses i s assumed t o be s imul taneo us with  t he ela sto -p lastic def o rmation d uring  the te mp erat ure  decre ase. T he pr esen tinv ention re l a te s  g en e ral ly t o gas  t urbi ne engine s , and mo rep articul ar lyt o  gas t u rb i n e engine b lad ed ro t o rs havings epar a bl e  blad e plat formsthat ar e  co up led tothe r otor disk /wheel by mec ha nica l engage me nt w it h t he  rotor disk lug s. Altho ugh thep r esentinv e ntio n  was d ev eloped for g as tu rb i ne engi n e s,certain app lic ati onsmay  beo utside of this field.
Ga s tu rbine eng ine r otors  t ypically empl oy blade platforms tha t extend genera l lyl ater all y  o fthe blade s t o  part iall y d efin e a n ae r o dyna m ic f l ow  pat h betw eenad ja cent blad es . One c o nven t ion al a pproa ch  u t il ized to  retainthe b la des to th e  rotordisk /w heel has been  by the util iz atio n of d o vet ail a nd slot arra ngements.Ass ociated wi th  th i s c onven tional approa chof ret aini ng  the b lades to  the r otor d isk/
 steps,_it is_also preferable that the_creep deformation_calculation_step is_a_step for calculating_the deformation by_taking the sum of_the deformation produced_by_the creep strain obtained from the creep characteristic with respect to time and the_deformation_produced by_the_thermal_shrinkage obtained based on the_thermal shrinkage characteristic with respect_to time_as the total deformation with respect to time_of_said substance. In_such a case, in the calculation, the thermal shrinkage_deformation occurring as time elapses is_assumed to be_simultaneous_with_the creep deformation.
Further, in_the aspect of the thermal deformation_analysis method of the present invention_comprising the above three steps, it is_also preferable that the calculation step_for deformation during temperature increase_is a_step for calculating the elasto-plastic_deformation of the_substance based_on the linear_expansion coefficient of the substance obtained_according to the_elasto-plastic deformation characteristic and on the_thermal_shrinkage rate of_the_substance_obtained according_to the thermal_shrinkage_characteristic. In_such_a case, in the calculation, the_thermal_shrinkage deformation occurring as time elapses is_assumed to be simultaneous_with_the elasto-plastic deformation during_the temperature increase. Because the_saturated amount of thermal shrinkage is_calculated during_temperature increase_process, this is especially effective when the thermal shrinkage is saturated_or nearly saturated at an early_stage of the temperature_increase.
Still further,_in_the aspect of_the_thermal deformation_analysis method of the present invention comprising_the above_three steps, it is also preferable_that the calculation step_for_deformation during the following temperature decrease_is a step for calculating the_elasto-plastic deformation of the substance_based_on_the linear expansion coefficient of_the substance obtained according to the_elasto-plastic deformation characteristic_and on the thermal shrinkage rate of_the_substance obtained according to the thermal_shrinkage_characteristic. In such a case, in_the_calculation,_the thermal shrinkage deformation occurring_as time elapses is assumed to_be simultaneous with the elasto-plastic deformation during the temperature_decrease. The present_invention relates generally to gas_turbine_engines,_and more particularly to gas turbine engine bladed rotors having_separable blade_platforms that are_coupled to the rotor disk/wheel by mechanical engagement with the_rotor disk lugs. Although the present invention_was developed for gas turbine engines, certain applications may be outside_of this field.
Gas turbine engine rotors typically employ_blade platforms that extend generally laterally of_the blades to partially_define_an aerodynamic flow path between adjacent blades._One_conventional_approach_utilized to retain_the blades to_the rotor disk/wheel_has been_by the utilization_of dovetail_and slot arrangements._Associated_with this conventional approach of retaining the blades to the rotor disk/