Extensive Industrial Gas Turbine Experience With Second Generation Single Crystal Alloy Turbine Blades

Brentnall, W. D.; Aurrecoechea, José M.; Rimlinger, C.; Harris, Ken; Erickson, G. L.; Wahl, Jacqueline B.

doi:10.1115/97-gt-427

Cited by 4 publications

(4 citation statements)

References 2 publications

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“…CMSX-4 alloy has been successfully used in numerous aero and industrial gas turbine applications since 1991. These applications, such as high pressure turbine blades and seals, have demonstrated an impressive combination of high temperature strength, good phase stability and oxidation, hot corrosion and coating performance in extensive engine service [11,12,13]. Close to five million pounds (650 heats) of CMSX-4 alloy have been manufactured to date.…”

Section: Cmsx-4 (Sls)[la + Y] Alloymentioning

confidence: 99%

Improved Single Crystal Superalloys, CMSX-4 (SLS)[La+Y] and CMSX-486

Harris¹,

Wahl²

2004

Superalloys 2004 (Tenth International Symposium)

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Single crystal superalloys and casting technology offer a combination of attractive properties for advanced gas turbine engine components. The alloys are designed to produce superior properties for a challenging combination of requirements: high temperature creep-strength, fatigue resistance, oxidation resistance, coating performance and retention of performance in thin-walled configurations. Application of this technology to new components has only been restricted by the competing criteria of affordability for first time introduction.The development of improved single crystal superalloys, CMSX-4 (SLS) [La+Y] and CMSX-486 provide an appealing combination of enhanced performance and production affordability for demanding, high temperature applications in advanced gas turbine engines.

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Section: Cmsx-4 (Sls)[la + Y] Alloymentioning

confidence: 99%

Improved Single Crystal Superalloys, CMSX-4 (SLS)[La+Y] and CMSX-486

Harris¹,

Wahl²

2004

Superalloys 2004 (Tenth International Symposium)

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“…Only very limited distress has been noted in the CMSX-4 airfoils after testing and the engine results indicate that the relative improvement for CMSX-4 is perhaps greater than originally anticipated. This has been particularly true for the multi-airfoil segmented 2nd vane (Burkholder, et al, 1995); (Figs. 13-17 incl.)…”

Section: Allison Engine Test Resultsmentioning

confidence: 83%

“…Solara Turbines, Inc. has reported that six years of field experience for CMSX-4 first stage blades in the MARS 100 industrial turbine has been excellent Total running time for the 132 engines in the field is 1.25 million hrs, with the blades and Pal coatings in good condition when examined at engine overall after 26,000 -28,000 Firs service. The MARS 100 engines tend to spend at least 50% of their miming time at maximum power with natural gas or liquid natural gas (LNG) as the predominant fuel (Harris, et al, 1992, Kubarych and Autrecoechea, 1993, Brentnall, et al, 1997. Figure 29 shows a photomicrograph from a MARS 100 first stage CM5X-4 turbine blade after over 25,000 service hours.…”

Section: : Other Engine Experiencementioning

confidence: 99%

“…The CastcoolTh Lamilloy® technology combines film leading and trailing edge airfoil cooling, with the dual-wall Lamilloy cooling in the rest of the airfoil in a one piece single crystal casting, further improving the cost of manufacture. The fine detail and complexity of these components bring manufacturing considerations to the forefront (Harris et al, 1990, Burkholder et al, 1995. (Fig.…”

Section: Introductionmentioning

confidence: 99%

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Development and Turbine Engine Performance of Three Advanced Rhenium Containing Superalloys for Single Crystal and Directionally Solidified Blades and Vanes

Broomfield

Ford

Bhangu

et al. 1997

Volume 4: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

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Turbine inlet temperatures over the next few years will approach 1650°C (3000°F) at maximum power for the latest large commercial turbo fan 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 improve 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% Re and CMSX®−10 containing 6% Re) and a directionally solidified, columnar grain nickel-base alloy (CM 186 LC® containing 3% 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% of the time spent at maximum power. Combined cycle efficiencies of large frame industrial engines is scheduled to reach 60% 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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Development and Turbine Engine Performance of Three Advanced Rhenium Containing Superalloys for Single Crystal and Directionally Solidified Blades and Vanes

Broomfield

Ford

Bhangu

et al. 1998

Journal of Engineering for Gas Turbines and Power

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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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Extensive Industrial Gas Turbine Experience With Second Generation Single Crystal Alloy Turbine Blades

Cited by 4 publications

References 2 publications

Improved Single Crystal Superalloys, CMSX-4 (SLS)[La+Y] and CMSX-486

Improved Single Crystal Superalloys, CMSX-4 (SLS)[La+Y] and CMSX-486

Development and Turbine Engine Performance of Three Advanced Rhenium Containing Superalloys for Single Crystal and Directionally Solidified Blades and Vanes

Development and Turbine Engine Performance of Three Advanced Rhenium Containing Superalloys for Single Crystal and Directionally Solidified Blades and Vanes

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