CMSX®-486: A New Grain Boundary Strengthened Single Crystal Superalloy

2002 ◽  
Author(s):  
Ken Harris ◽  
Jacqueline B. Wahl
Keyword(s):  
Grain Boundary ◽  
Single Crystal ◽  
Engine Performance ◽  
Single Crystal Superalloy ◽  
Manufacturing Cost ◽  
Application Development ◽  
Turbine Engine ◽  
Component Design ◽  
Casting Yield ◽  
Rupture Properties

Modern turbine engine performance and life cycle requirements demand single crystal superalloy turbine airfoil and seal components. Complex SX vane segments can result in severe manufacturing cost challenges. This has resulted in the development of an improved creep-rapture strength SX superalloy designated CMSX®-486. This alloy is grain boundary strengthened through optimised additions of boron, carbon, hafnium and zirconium and is designed for use as-cast, to maximise complex casting yield through the use of generous grain specifications and without solution heat treatment recrystallisation problems. The paper in particular gives comprehensive low and high angle boundary creep-rupture properties of CMSX-486, enabling grain specifications to be developed depending upon component design requirements. The alloy has now entered its turbine application development phase.

CMSX-486® Single Crystal Alloy: Production Experience and Development of an Improved Version

2006 ◽  
Author(s):  
Jacqueline B. Wahl ◽  
Ken Harris
Keyword(s):  
Single Crystal ◽  
Rupture Strength ◽  
Engine Performance ◽  
Manufacturing Cost ◽  
Creep Rupture Strength ◽  
Turbine Engine ◽  
Production Experience ◽  
Casting Yield ◽  
Oxidation Resistant ◽  
Manufacturing Yield

Modern turbine engine performance and life cycle requirements demand single crystal (SX) superalloy turbine airfoil and seal components. However, complex SX components, such as vane segments, can result in severe manufacturing cost challenges due to low manufacturing yield. These requirements led to the development of CMSX-486® alloy, a grain boundary strengthened SX superalloy with improved creep-rupture strength over SX CM 186 LC® alloy. CMSX-486 alloy has excellent casting yield achieved through generous grain inspection criteria and is used as-cast, which minimizes post-cast processing costs and eliminates the risk of recrystallization during solution heat treatment. CMSX-486 alloy has attained production status and further improvements to the alloy are under evaluation. This paper will review the unique properties which make this alloy of serious interest, with particular attention to ongoing production experience. Discussion will also include direction and results of an improved oxidation resistant version of CMSX-486 alloy which is currently under development.

The influence of grain boundary angle on the hot cracking of single crystal superalloy DD6

2016 ◽  
Vol 676 ◽  
pp. 181-186 ◽  
Author(s):  
P. Rong ◽  
N. Wang ◽  
L. Wang ◽  
R.N. Yang ◽  
W.J. Yao
Keyword(s):  
Grain Boundary ◽  
Single Crystal ◽  
Hot Cracking ◽  
Single Crystal Superalloy

Improvement of grain boundary tolerance by minor additions of Hf and B in a second generation single crystal superalloy

2019 ◽  
Vol 176 ◽  
pp. 109-122 ◽  
Author(s):  
Y.S. Zhao ◽  
J. Zhang ◽  
Y.S. Luo ◽  
B. Zhang ◽  
G. Sha ◽  
...  
Keyword(s):  
Grain Boundary ◽  
Single Crystal ◽  
Second Generation ◽  
Single Crystal Superalloy

CMSX-486® Alloy Update

2009 ◽  
Author(s):  
Jacqueline Wahl ◽  
Ken Harris
Keyword(s):  
Fatigue Testing ◽  
Rupture Strength ◽  
Low Cycle Fatigue ◽  
Engine Performance ◽  
Manufacturing Cost ◽  
Type I ◽  
Homogeneous Microstructure ◽  
Turbine Engine ◽  
Electron Microscopy Analysis ◽  
Residual Sulfur

Modern turbine engine performance and life cycle requirements demand single crystal (SX) superalloy turbine airfoil and seal components. However, complex SX components, such as vane segments, can result in severe manufacturing cost challenges due to low manufacturing yield. As presented at TURBO EXPO 2002 and 2006, these requirements led to the development of CMSX-486® alloy, a grain boundary strengthened SX superalloy with improved creep-rupture strength over SX CM 186 LC® alloy. This paper will review the unique properties that make this alloy desirable, with particular attention to ongoing developments. Significant market interest has resulted in additional property evaluation, including strain-controlled low cycle fatigue testing which has produced fatigue lives similar to HIP’ed and solutioned CMSX-4® SX alloy at 1038°C. This was surprising considering the non-homogeneous microstructure of CMSX-486 alloy, which is used in the as-cast + double aged heat treat condition. Also, burner rig dynamic, cyclic oxidation and Type I hot corrosion results will be presented for CMSX-486 (SLS) [La+Y] alloy in comparison to CMSX-4, CMSX-4(SLS)[La+Y] and CMSX-486 alloys. Scanning electron microscopy analysis shows residual sulfur and phosphorus in CMSX-486 (SLS) [La+Y] are tied up as Y and La carbo-sulfides and phosphides.

The Evolution of Thermal Barrier Coatings in Gas Turbine Engine Applications

1994 ◽  
Vol 116 (1) ◽  
pp. 250-257 ◽  
Author(s):  
S. M. Meier ◽  
D. K. Gupta
Keyword(s):  
Thermal Barrier Coatings ◽  
Turbine Blades ◽  
Engine Performance ◽  
Design System ◽  
Thermal Barrier ◽  
Barrier Coatings ◽  
Turbine Engine ◽  
Component Design ◽  
Integral Element ◽  
Plasma Sprayed

Thermal barrier coatings (TBCs) have been used for almost three decades to extend the life of combustors and augmentors and, more recently, stationary turbine components. Plasma-sprayed yttria-stabilized zirconia TBC currently is bill-of-material on many commercial jet engine parts. A more durable electron beam-physical vapor deposited (EB-PVD) ceramic coating recently has been developed for more demanding rotating as well as stationary turbine components. This ceramic EB-PVD is bill-of-material on turbine blades and vanes in current high thrust engine models and is being considered for newer developmental engines as well. To take maximum advantage of potential TBC benefits, the thermal effect of the TBC ceramic layer must become an integral element of the hot section component design system. To do this with acceptable reliability requires a suitable analytical life prediction model calibrated to engine experience. The latest efforts in thermal barrier coatings are directed toward correlating such models to measured engine performance.

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