High-Temperature Fatigue Properties of Single Crystal Superalloys in Air and HydrogenSource: Journal of Engineering for Gas Turbines and Power:;2004:;volume( 126 ):;issue: 003::page 590Author:N. K. Arakere
DOI: 10.1115/1.1501075Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Hot section components in high-performance aircraft and rocket engines are increasingly being made of single crystal nickel superalloys such as PWA1480, PWA1484, CMSX-4, and Rene N-4 as these materials provide superior creep, stress rupture, melt resistance, and thermomechanical fatigue capabilities over their polycrystalline counterparts. Fatigue failures in PWA1480 single crystal nickel-base superalloy turbine blades used in the space shuttle main engine fuel turbopump are discussed. During testing many turbine blades experienced stage II noncrystallographic fatigue cracks with multiple origins at the core leading edge radius and extending down the airfoil span along the core surface. The longer cracks transitioned from stage II fatigue to crystallographic stage I fatigue propagation, on octahedral planes. An investigation of crack depths on the population of blades as a function of secondary crystallographic orientation (β) revealed that for β=45+/−15 deg tip cracks arrested after some growth or did not initiate at all. Finite element analysis of stress response at the blade tip, as a function of primary and secondary crystal orientation, revealed that there are preferential β orientations for which crack growth is minimized at the blade tip. To assess blade fatigue life and durability extensive testing of uniaxial single crystal specimens with different orientations has been tested over a wide temperature range in air and hydrogen. A detailed analysis of the experimentally determined low cycle fatigue properties for PWA1480 and SC 7-14-6 single crystal materials as a function of specimen crystallographic orientation is presented at high temperature (75°F–1800°F) in high-pressure hydrogen and air. Fatigue failure parameters are investigated for low cycle fatigue data of single crystal material based on the shear stress amplitudes on the 24 octahedral and 6 cube slip systems for FCC single crystals. The max shear stress amplitude [Δτmax] on the slip planes reduces the scatter in the low cycle fatigue data and is found to be a good fatigue damage parameter, especially at elevated temperatures. The parameter Δτmax did not characterize the room temperature low cycle fatigue data in high-pressure hydrogen well because of the noncrystallographic eutectic failure mechanism activated by hydrogen at room temperature. Fatigue life equations are developed for various temperature ranges and environmental conditions based on power-law curve fits of the failure parameter with low cycle fatigue test data. These curve fits can be used for assessing blade fatigue life.
keyword(s): Temperature , Crystals , Nickel , Fuels , Superalloys , Stress , Turbine blades , High pressure (Physics) , Fracture (Materials) , Failure , Fatigue cracks , Hydrogen , Blades , High temperature , Engines , Shear (Mechanics) , Low cycle fatigue , Pumps , Cycles , Fatigue , Crystal structure , Airfoils , Failure mechanisms AND Fatigue properties ,
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contributor author | N. K. Arakere | |
date accessioned | 2017-05-09T00:12:59Z | |
date available | 2017-05-09T00:12:59Z | |
date copyright | July, 2004 | |
date issued | 2004 | |
identifier issn | 1528-8919 | |
identifier other | JETPEZ-26829#590_1.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl/handle/yetl/130007 | |
description abstract | Hot section components in high-performance aircraft and rocket engines are increasingly being made of single crystal nickel superalloys such as PWA1480, PWA1484, CMSX-4, and Rene N-4 as these materials provide superior creep, stress rupture, melt resistance, and thermomechanical fatigue capabilities over their polycrystalline counterparts. Fatigue failures in PWA1480 single crystal nickel-base superalloy turbine blades used in the space shuttle main engine fuel turbopump are discussed. During testing many turbine blades experienced stage II noncrystallographic fatigue cracks with multiple origins at the core leading edge radius and extending down the airfoil span along the core surface. The longer cracks transitioned from stage II fatigue to crystallographic stage I fatigue propagation, on octahedral planes. An investigation of crack depths on the population of blades as a function of secondary crystallographic orientation (β) revealed that for β=45+/−15 deg tip cracks arrested after some growth or did not initiate at all. Finite element analysis of stress response at the blade tip, as a function of primary and secondary crystal orientation, revealed that there are preferential β orientations for which crack growth is minimized at the blade tip. To assess blade fatigue life and durability extensive testing of uniaxial single crystal specimens with different orientations has been tested over a wide temperature range in air and hydrogen. A detailed analysis of the experimentally determined low cycle fatigue properties for PWA1480 and SC 7-14-6 single crystal materials as a function of specimen crystallographic orientation is presented at high temperature (75°F–1800°F) in high-pressure hydrogen and air. Fatigue failure parameters are investigated for low cycle fatigue data of single crystal material based on the shear stress amplitudes on the 24 octahedral and 6 cube slip systems for FCC single crystals. The max shear stress amplitude [Δτmax] on the slip planes reduces the scatter in the low cycle fatigue data and is found to be a good fatigue damage parameter, especially at elevated temperatures. The parameter Δτmax did not characterize the room temperature low cycle fatigue data in high-pressure hydrogen well because of the noncrystallographic eutectic failure mechanism activated by hydrogen at room temperature. Fatigue life equations are developed for various temperature ranges and environmental conditions based on power-law curve fits of the failure parameter with low cycle fatigue test data. These curve fits can be used for assessing blade fatigue life. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | High-Temperature Fatigue Properties of Single Crystal Superalloys in Air and Hydrogen | |
type | Journal Paper | |
journal volume | 126 | |
journal issue | 3 | |
journal title | Journal of Engineering for Gas Turbines and Power | |
identifier doi | 10.1115/1.1501075 | |
journal fristpage | 590 | |
journal lastpage | 603 | |
identifier eissn | 0742-4795 | |
keywords | Temperature | |
keywords | Crystals | |
keywords | Nickel | |
keywords | Fuels | |
keywords | Superalloys | |
keywords | Stress | |
keywords | Turbine blades | |
keywords | High pressure (Physics) | |
keywords | Fracture (Materials) | |
keywords | Failure | |
keywords | Fatigue cracks | |
keywords | Hydrogen | |
keywords | Blades | |
keywords | High temperature | |
keywords | Engines | |
keywords | Shear (Mechanics) | |
keywords | Low cycle fatigue | |
keywords | Pumps | |
keywords | Cycles | |
keywords | Fatigue | |
keywords | Crystal structure | |
keywords | Airfoils | |
keywords | Failure mechanisms AND Fatigue properties | |
tree | Journal of Engineering for Gas Turbines and Power:;2004:;volume( 126 ):;issue: 003 | |
contenttype | Fulltext |