Innovative Casting Methods for Single Crystal Turbine Blades

2021 ◽  
Vol 1032 ◽  
pp. 178-185
Author(s):  
Wan Qiu Ding
Keyword(s):  
Single Crystal ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Operation System ◽  
Gas Turbine Blades ◽  
Bridgman Process

This report outlines a succinct analysis of the contemporary casting methods in single-crystal turbine blades. Furthermore, this paper also provides an examination of the solidification procedure in mixed turbine blades. The couple cooling and heating operation system was advanced to obtain identical thermal positions for single crystal (SC) solidification in the blade group, thereby significantly diminishing the associated flaws in the contemporary Bridgman process. The chemistry science of Nickel based alloys planed for single crystal (SC) gas turbine blades has been notably improved upon, especially when considering the initial production of alloys. The second and third production within the total operation has been enhanced by the introduction of rhenium (Re). Surged density, grain flaws, and microstructural stableness have presented themselves as significant issues within this process. Additionally, it is imperative to minimize the concentrations of the different alloying components.

scholarly journals Single crystal casting of gas turbine blades using superior ceramic core

2020 ◽  
Vol 9 (3) ◽  
pp. 3348-3356
Author(s):  
Eun-Hee Kim ◽  
Hye Yeong Park ◽  
Cho-long Lee ◽  
Jong Bum Park ◽  
SeungCheol Yang ◽  
...  
Keyword(s):  
Single Crystal ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Ceramic Core ◽  
Gas Turbine Blades

Investigation of Crystallization Process of a Single Crystal Nickel-Based Alloy during the Laser Multilayer Cladding

2019 ◽  
Vol 822 ◽  
pp. 481-488
Author(s):  
R.S. Korsmik ◽  
Gleb A. Turichin ◽  
G.G. Zadykyan ◽  
Andrey Igorevich Zhitenev
Keyword(s):  
Single Crystal ◽  
Gas Turbine ◽  
Laser Cladding ◽  
Crystallization Process ◽  
Turbine Blades ◽  
Regression Equations ◽  
Microstructure Formation ◽  
Technological Parameters ◽  
Gas Turbine Blades ◽  
Nickel Based Alloy

The article shows the results of multilayer laser cladding of heat-resistant single crystal nickel-based alloy ZhS32-VI (CSMX-4 analogue). The influence of the main technological parameters on geometry and microstructure formation of deposited beads was investigated. Based on obtained dependencies, the regression equations are compiled for describing the shape of bead and the ratio of directional and equiaxial crystallized sections. The obtained dependencies of regime parameters nomination allow restoring the gas-turbine blades by the method of laser cladding.

Rejuvenation Heat Treatment of Single Crystal Gas Turbine Blades

2017 ◽  
Author(s):  
J. Kuipers ◽  
K. Wiens ◽  
B. Ruggiero
Keyword(s):  
Heat Treatment ◽  
Single Crystal ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Damage Mechanism ◽  
Operating Conditions ◽  
Gas Turbine Blades ◽  
Full Solution ◽  
Fatigue Endurance ◽  
Root Surfaces

Thermal degradation of precipitation-hardened nickel based superalloys has been demonstrated to be reversible through full solution rejuvenation heat treatment processing. The specific concern with full solution rejuvenation heat treatment of single crystal alloys is the formation of recrystallized grains on surfaces with residual stress. The threshold temperature for recrystallization and the effect of heat treatment temperature and time on recrystallization depth were evaluated on service run industrial gas turbine blades comprised of nickel based single crystal alloys René N5 and RR2000. Recrystallization of rejuvenated blades was observed on the root surfaces of blades which had been shot peened at original manufacture and/or during a prior repair. Blades which did not receive peening at manufacture were free of recrystallization in critical areas following full solution rejuvenation heat treatment. Given that gas turbine blade roots operate at relatively low temperatures compared to the airfoil, creep is not considered a life limiting damage mechanism for this region of the blade. Rather, high cycle fatigue is considered the primary damage mechanism of concern. As such, fatigue testing of shot peened and heat treated (recrystallized) René N5 specimens was carried out at 650°C at various stress levels in comparison with baseline (non-recrystallized) specimens to determine the extent to which recrystallization would limit fatigue endurance at blade root operating conditions. It was found that recrystallization did not reduce the fatigue endurance relative to baseline samples at the tested conditions. The findings indicate that repair including full solution rejuvenation heat treatment of previously peened blades comprised of René N5 alloy is feasible provided that recrystallization be limited to root surfaces.

Development of Ni based single crystal superalloys for power generation gas turbine blades

2007 ◽  
Vol 2 (1) ◽  
pp. 5-12 ◽  
Author(s):  
R. Hashizume ◽  
A. Yoshinari ◽  
T. Kiyono ◽  
Y. Murata ◽  
M. Morinaga
Keyword(s):  
Power Generation ◽  
Single Crystal ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Gas Turbine Blades

Advancement of Experimental Methods and Cailletaud Material Model for Life Prediction of Gas Turbine Blades Exposed to Combined Cycle Fatigue

2012 ◽  
Author(s):  
Marcus Thiele ◽  
Swen Weser ◽  
Uwe Gampe ◽  
Roland Parchem ◽  
Samuel Forest
Keyword(s):  
Single Crystal ◽  
Gas Turbine ◽  
Life Prediction ◽  
Kinematic Hardening ◽  
Turbine Blades ◽  
Material Model ◽  
Combined Cycle ◽  
Cycle Fatigue ◽  
Stress Strain ◽  
Gas Turbine Blades

The European project PREMECCY has been conducted to enhance predictive methods for combined cycle fatigue (CCF) of gas turbine blades, i.e. interaction of low cycle fatigue (LCF) and high cycle fatigue (HCF). While design of CCF feature tests, comprising specimen and test rig design, has already been reported, this paper presents experimental HCF/ CCF test results and progress in life prediction. Besides standard lab specimen tests for characterization of single crystal and conventional cast material, also advanced specimens representing critical rotor blade features were tested in a hot gas rig. Based on these experimental data an extended Cailletaud material model for stress-strain analysis has been calibrated and combined with a modified ONERA damage model for creep-fatigue interaction to estimate the lifetime of the advanced test specimens. The model extensions address the effect of ratcheting, which is typical for CMSX-4 at asymmetric cyclic loading at elevated temperature. Caused by limitations of the Armstrong-Frederick kinematic hardening rule regarding ratcheting, three models for improved ratcheting simulation of isotropic material were adopted to anisotropic material. In addition multiple Norton-flow rules for the viscous part of the model are combined with time recovery terms in the kinematic hardening evolution to represent the behaviour of single crystal material in high temperature environment at a wide range of strain rates. Hence, an improved model for stress-strain and lifetime prediction for single crystals has been developed.

scholarly journals Development of Ni-based Single Crystal Superalloys for Power-generation Gas-turbine Blades

2004 ◽  
Vol 90 (7) ◽  
pp. 518-525 ◽  
Author(s):  
Ryokichi HASHIZUME ◽  
Akira YOSHINARI ◽  
Yoshinori MURATA ◽  
Masahiko MORINAGA
Keyword(s):  
Power Generation ◽  
Single Crystal ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Gas Turbine Blades

scholarly journals Processing of a Single Crystal Casting for Heavy-Duty Gas Turbine Blades: Creep and Metal/Mould Reaction Behavior of Al2O3-SiO2 Shell Mould

1993 ◽  
Author(s):  
K. Iijima ◽  
A. Yoshinari ◽  
T. Ishida ◽  
T. Yasuda ◽  
H. Matsuzaki ◽  
...  
Keyword(s):  
Single Crystal ◽  
Gas Turbine ◽  
Turbine Blades ◽  
Average Particle Size ◽  
Average Particle ◽  
Heavy Duty ◽  
Creep Tests ◽  
Gas Turbine Blades ◽  
Sio2 Shell ◽  
Heavy Duty Gas Turbine

Al2O3-SiO2 moulds have been adopted successfully as shell moulds for a single crystal casting for jet engine blades. Heavy-duty gas turbine blades also have large dimensions and complex features comparable to those of jet engines. Then shell moulds should be subjected to similar severe service conditions when casting heavy-duty gas turbine blades. Creep behavior of 90mol%Al2O3+10mol%SiO2, which was manufactured through the lost wax process by using fused Al2O3 powder (average particle size, 15 μ m), was studied at temperatures of 1450 to 1550 °C. in four-point bending creep tests. Creep deflection rates were linearly proportional to stresses. The proposed creep mechanism was Al grain boundary diffusion at the interfacial regions between Al2O3 stucco powder. No severe metal/mould reaction appeared for the region adjacent to the interface between moulds and Ni base superalloys.

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