the present invention is directed to gamma prime nickel - base superalloys , and particular those suitable for components produced by a hot working ( e . g ., forging ) operation to have a polycrystalline microstructure . a particular example represented in fig1 is a high pressure turbine disk 10 for a gas turbine engine . the invention will be discussed in reference to processing of a high - pressure turbine disk for a gas turbine engine , though those skilled in the art will appreciate that the teachings and benefits of this invention are also applicable to compressor disks and blisks of gas turbine engines , as well as numerous other components that are subjected to stresses at high temperatures and therefore require a high temperature dwell capability . disks of the type shown in fig1 are typically produced by isothermally forging a fine - grained billet formed by powder metallurgy ( pm ), a cast and wrought processing , or a spraycast or nucleated casting type technique . in a preferred embodiment utilizing a powder metallurgy process , the billet can be formed by consolidating a superalloy powder , such as by hot isostatic pressing ( hip ) or extrusion consolidation . the billet is typically forged at a temperature at or near the recrystallization temperature of the alloy but less than the gamma prime solvus temperature of the alloy , and under superplastic forming conditions . after forging , a supersolvus ( solution ) heat treatment is performed , during which grain growth occurs . the supersolvus heat treatment is performed at a temperature above the gamma prime solvus temperature ( but below the incipient melting temperature ) of the superalloy to recrystallize the worked grain structure and dissolve ( solution ) the gamma prime precipitates in the superalloy . following the supersolvus heat treatment , the component is cooled at an appropriate rate to re - precipitate gamma prime within the gamma matrix or at grain boundaries , so as to achieve the particular mechanical properties desired . the component may also undergo aging using known techniques . superalloy compositions of this invention were developed through the use of a proprietary analytical prediction process directed at identifying alloying constituents and levels capable of exhibiting better high temperature dwell capabilities than existing nickel - base superalloys . more particularly , the analysis and predictions made use of proprietary research involving the definition of elemental transfer functions for tensile , creep , hold time ( dwell ) crack growth rate , density , and other important or desired mechanical properties for turbine disks produced in the manner described above . through simultaneously solving of these transfer functions , evaluations of compositions were performed to identify those compositions that appear to have the desired mechanical property characteristics for meeting advanced turbine engine needs , including creep and hold time fatigue crack growth rate ( htfcgr ). the analytical investigations also made use of commercially - available software packages along with proprietary databases to predict phase volume fractions based on composition , allowing for the further definition of compositions that approach or in some cases slightly exceed undesirable equilibrium phase stability boundaries . finally , solution temperatures and preferred amounts of gamma prime and carbides were defined to identify compositions with desirable combinations of mechanical properties , phase compositions and gamma prime volume fractions , while avoiding undesirable phases that could reduce in - service capability if equilibrium phases sufficiently form due to in - service environment characteristics . in the investigations , regression equations or transfer functions were developed based on selected data obtained from historical disk alloy development work . the investigations also relied on qualitative and quantitative data of the aforementioned nickel - base superalloys r88dt and r104 . particular criteria utilized to identify potential alloy compositions included the desire for a volume percentage of gamma prime (( ni , co ) 3 ( al , ti , nb , ta )) greater than that of r88dt , with the intent to promote strength at temperatures of 1400 ° f . ( about 760 ° c .) and higher over extended periods of time . a gamma prime solvus temperature of not more than 2200 ° f . ( about 1200 ° c .) was also identified as desirable for ease of manufacture during heat treatment and quench . in addition , certain compositional parameters were identified as starting points for the compositions , including the inclusion of hafnium for high temperature strength , chromium levels of 10 weight percent or more for corrosion resistance , aluminum levels greater than the nominal r88dt level to maintain gamma prime ( ni 3 ( al , ti , nb , ta )) stability , and cobalt levels of greater than 18 weight percent to aid in minimizing stacking fault energy ( desirable for good cyclic behavior ) and controlling the gamma prime solvus temperature . the regression equations and prior experience further indicated that relatively high levels of refractory elements were desirable to improve high temperature properties , and selective balancing of titanium , tungsten , niobium and molybdenum levels were employed to optimize creep and hold time fatigue crack growth behavior . finally , regression factors relating to specific mechanical properties were utilized to narrowly identify potential alloy compositions that might be capable of exhibiting superior high temperature hold time ( dwell ) behavior , and would not be otherwise identifiable without extensive experimentation with a very large number of alloys . such properties included ultimate tensile strength ( uts ) at 1200 ° f . ( about 650 ° c . ), yield strength ( ys ), elongation ( el ), reduction of area ( ra ), creep ( time to 0 . 2 % creep at 1200 ° f . and 115 ksi ( about 650 ° c . at about 790 mpa ), hold time ( dwell ) fatigue crack growth rate ( htfcgr ; da / dt ) at 1300 ° f . ( about 700 ° c .) and a maximum stress intensity of 25 ksi √ in ( about 27 . 5 mpa √ m ), fatigue crack growth rate ( fcgr ), gamma prime volume percent ( gamma ′ %) and gamma prime solvus temperature ( solvus ), all of which were evaluated on a regression basis . units for these properties reported herein are ksi for uts and ys , percent for el , ra and gamma prime volume percent , hours for creep , in / sec for crack growth rates ( htfcgr and fcgr ), and ° f . for gamma prime solvus temperature . thermodynamic calculations were also performed to assess alloy characteristics such as phase volume fraction , stability and solvii for gamma prime , carbides , borides and topologically close packed ( tcp ) phases . the process described above was performed iteratively utilizing expert opinion and guidance to define preferred compositions for manufacture and evaluation . from this process , a first series of alloy compositions were defined ( by weight percent ) as set forth in the table of fig2 . also included in the table is r88dt for reference . regression - based property predictions for the alloys of fig2 are contained in the table of fig3 , and fig4 contains a graph of the hold time fatigue crack growth rate ( htfcgr ) and creep data from fig3 . from the visual depiction of fig4 , it can be seen that alloys me42 , me43 , me44 , me46 , me48 , me49 , and me492 were analytically predicted to exhibit the best combinations of creep and hold time crack growth rate characteristics , with creep exceeding 7000 hours and htfcgr of about 1 × 10 − 7 in / s ( about 1 × 10 − 6 mm / s ) or less , and therefore offering a notable improvement of the regression - based predictions for r88dt , r104 , and other current alloys plotted in fig4 . those alloys predicted to have improved dwell fatigue and creep over rene 88dt were further evaluated by thermodynamic calculations to assess alloy characteristics such as phase volume fraction , stability , and solvii . from this analysis , it was predicted that alloys me43 , me44 , me48 and me492 might be prone to potentially undesirable levels of detrimental topologically close - packed ( tcp ) phases , such as sigma phase ( generally ( fe , mo ) x ( ni , co ) y , where x and y = 1 to 7 ) and / or eta phase ( ni 3 ti ). although the thermodynamic calculations of tcp phases were believed to have some uncertainty , the desire to avoid undesirable levels of formation of tcp phases provided the basis for defining a second series of alloy compositions , designated as alloys hl - 06 through hl - 15 , whose compositions ( in weight percent ) are summarized in the table of fig5 . the second series included a designed experiment - based series of alloys ( hl - 06 , - 07 , - 08 , - 09 and - 10 ) and a more exploratory - based series of alloys ( hl - 11 , - 12 , - 13 , - 14 and - 15 ). the designed experiment - based series was largely based on the goal of providing a relatively high tantalum content while balancing ti / al and mo / w + mo ratios . four of the five exploratory alloys were formulated to investigate the effect of high tantalum levels , while the fifth ( hl - 15 ) was formulated to have a lower tantalum level but a much higher molybdenum level to investigate the affect of offsetting molybdenum for tungsten . regression - based property predictions for the second series of alloys are summarized in the table of fig6 , and fig7 contains a graph of the htfcgr and creep data from fig6 . from the visual depiction of fig7 , it can be seen that alloys hl - 07 , hl - 08 and hl - 09 were analytically predicted to exhibit the best combinations of creep and hold time crack growth rate characteristics , with creep exceeding 7000 hours and htfcgr of about 3 × 10 7 in / s ( about 7 . 6 × 10 6 mm / s ) or less , and therefore offering a notable improvement of the regression - based predictions for r88dt , r104 , and other current alloys plotted in fig7 . the alloys were also assessed for alloy characteristics such as phase volume fraction , stability and solvii , and none were predicted to have potentially undesirable levels of formation of tcp phases . on the basis of the above predictions , nine alloys ( alloys a through i ) were prepared with compositions based on the ten alloys of the second series . the actual chemistries ( in weight percent ) of the prepared alloys are summarized in the table of fig8 . from these alloys , two distinguishable alloy types were identified based in part on their different tantalum and molybdenum contents . the first alloy type , encompassing alloys a through h , is summarized in table ii below and characterized in part by relatively high tantalum levels . the second alloy type , encompassing alloy i , is summarized in table iii below and characterized by a relatively high molybdenum content . also summarized in table ii are alloying ranges for the compositions of alloys a and e , which are believed to have particularly promising properties based on actual performance in a htfcgr ( da / dt ) test conducted at about 1400 ° f . and using a three hundred second hold time ( dwell ) and a maximum stress intensity of 20 ksi √ in ( about 22 mpa √ m ). the crack growth rates of alloys a through i and their crack growth rates relative to ri 04 are summarized in table i below . a table provided in fig9 summarizes other properties of alloys a through i relative to r104 . ultimate tensile strength ( uts ) yield strength , ( 0 . 02 % ys and 0 . 2 % ys ), elongation ( el ), and reduction of area ( ra ) were evaluated at 1400 ° f . ( about 760 ° c . ), while time to 0 . 2 % creep ( 0 . 2 % creep ) and rupture ( rupture time ) were evaluated at 1400 ° f . and 100 ksi ( about 760 ° c . at about 690 mpa ). it should be noted that the creep and rupture behavior of alloys a , e and i were significantly higher than those of r104 , which itself is considered to exhibit very good creep and rupture behavior . fig1 provides a graph plotting the rupture data of fig9 versus the htfcgr data of table i . from the visual depiction of fig1 , it can be seen that alloys a , e and i exhibited the best combinations of hold time crack growth rate and rupture , and indicate a notable improvement over r104 . the titanium : aluminum weight ratio is believed to be important for the alloys of tables ii and iii on the basis that higher titanium levels are generally beneficial for most mechanical properties , though higher aluminum levels promote alloy stability necessary for use at high temperatures . in addition , the molybdenum : molybdenum + tungsten weight ratio is also believed to be important for the alloys of table ii as this ratio indicates the refractory content for high temperature response and balances the refractory content of the gamma and the gamma prime phases . as such , these ratios are also included in tables ii and iii where applicable . in addition to the elements listed in tables ii and iii , it is believed that minor amounts of other alloying constituents could be present without resulting in undesirable properties . such constituents and their amounts ( by weight ) include up to 2 . 5 % rhenium , up to 2 % vanadium , up to 2 % iron , and up to 0 . 1 % magnesium . though the alloy compositions identified in fig2 , 5 and 8 and the alloys and alloying ranges identified in tables ii and iii were initially based on analytical predictions , the extensive analysis and resources relied on to make the predictions and identify these alloy compositions provide a strong indication for the potential of these alloys , and particularly the alloy compositions of tables ii and iii , to achieve significant improvements in creep and hold time fatigue crack growth rate characteristics desirable for turbine disks of gas turbine engines . while the invention has been described in terms of particular embodiments , including particular compositions and properties of nickel - base superalloys , the scope of the invention is not so limited . instead , the scope of the invention is to be limited only by the following claims .