The CMSX@-10 alloy is a third generation single crystal (SX) casting material which is used in demanding turbine engine blading applications. The flight engine certified alloy is characterized by it's 6 wt. % rhenium content, high additive refractory element level, and relatively low chromium employment. Based on published data, the alloy is thought to exhibit the highest creep strength and resistance to fatigue of any production Ni-base, cast SX superalloy.CMSX-10 alloy provides an approximate 30°C improved creep strength relative to second generation 3 wt. % containing SX alloys such as CMSX-4 and PWA 1484. Furthermore, it develops low cycle and high cycle fatigue (LCF and HCF) strengths as much as 2-3 times better than the best alternatives. Moreover, the alloy also develops an attractive blend of tensile and impact strengths, foundry performance, heat treatability and environmental properties characteristic. Most notably, the alloy provides surprisingly good hot corrosion resistance, despite its novel and relatively low chromium content (2-3 wt. %). Additionally, the alloy performs extremely well in both the aluminide and Pt -aluminide coated conditions.Although the CMSX-10 alloy was developed to fulfill a perceived need in the aero-turbine industry, the alloy's long-term high strength, particularly at temperatures ranging from 850-950°C has attracted significant industrial turbine interest. For this reason, longer term (currently to about 5000 hours) creep-rupture strength characterization is underway. Similarly, due to a continued need for materials with greater creep-strength, a higher strength CMSX-10 derivative, currently designated CMSX-1 O+, is under development.This narrative characterizes the CMSX-10 alloy SX component castability, heat treatability, mechanical strength, environmental properties and coating characteristics. Active long-term creeprupture programs are discussed, as well as preliminary results for a higher strength alloy, currently designated CMSX@-lO+.
TheCMSX® -lO alloy isa third-generation, single-crystal (SX), nickel-based casting alloy that is characterized by its 6 wt. % rhenium content, relatively high refractory element level (W + Ta + Re+ Mo), and lowleve! of chromium employment. Based on published data, the alloy's high-temperature creep-rupture resistance is greater than all other nickel-based alloys (approximately 30"C better than CMSX-4 and PWA 1484). Moreover, the alloy's composition is balanced to provide an attractive blend of SX component castability, heat treatability, impact strength, fatigue strength, and resistance to environmental degradation. Most notably, the alloy provides extremely good bare hot corrosion resistance, despite its novel and relatively low (2-3 wt.% ) chromium content.
Turbine inlet temperatures over the next few years will approach 1650°C (3000°F) at maximum power for the latest large commercial turbofan engines, resulting in high fuel efficiency and thrust levels approaching 445 KN (100,000 lbs.). High reliability and durability must be intrinsically designed into these turbine engines to meet operating economic targets and ETOPS certification requirements. This level of performance has been brought about by a combination of advances in air cooling for turbine blades and vanes, design technology for stresses and airflow, single crystal and directionally solidified casting process improvements, and the development and use of rhenium (Re) containing high γ′ volume fraction nickel-base superalloys with advanced coatings, including full-airfoil ceramic thermal barrier coatings. Re additions to cast airfoil superalloys not only improves creep and thermo-mechanical fatigue strength, but also environmental properties including coating performance. Re dramatically slows down diffusion in these alloys at high operating temperatures. A team approach has been used to develop a family of two nickel-base single crystal alloys (CMSX-4® containing 3 percent Re and CMSX®-10 containing 6 percent Re) and a directionally solidified, columnar grain nickel-base alloy (CM 186 LC® containing 3 percent Re) for a variety of turbine engine applications. A range of critical properties of these alloys is reviewed in relation to turbine component engineering performance through engine certification testing and service experience. Industrial turbines are now commencing to use this aero developed turbine technology in both small and large frame units in addition to aero-derivative industrial engines. These applications are demanding, with high reliability required for turbine airfoils out to 25,000 hours, with perhaps greater than 50 percent of the time spent at maximum power. Combined cycle efficiencies of large frame industrial engines are scheduled to reach 60 percent in the U. S. ATS programme. Application experience to a total 1.3 million engine hours and 28,000 hours individual blade set service for CMSX-4 first stage turbine blades is reviewed for a small frame industrial engine.
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