# Numerical Simulation of Creep Damage and Life Prediction of Superalloy Turbine Blade

Authors: Donghuan Liu; Haisheng Li; Yinghua Liu
Journal: Mathematical Problems in Engineering
 (2015)

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## Abstract

Creep caused failure is an important failure mode of the turbine blade. A numerical approach of life assessment of the superalloy turbine blade is proposed in the present paper based on the Lemaitre-Chaboche creep damage model. Material damage is introduced into each element based on the ANSYS APDL function, and the creep damage effect is considered through the modification of Young’s modulus. At last, the strength life and stiffness life of the blade can be obtained through the maximum damage and maximum creep strain criterion, respectively. The present method can not only consider the effect of creep damage, but also give the time histories of the element stresses, damage, and creep strain. The above life prediction results based on the proposed method are compared with theθ projection method, and the results suggest that the present life prediction method of turbine blade is feasible and turbine blade’s life in the present study is determined by creep fracture rather than creep deformation.


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## Body

## 1. Introduction

Creep failure is one of the most important failure modes of turbine blade. Creep is the progressive time-dependent inelastic deformation under mechanical load and high temperature. The creep process is accompanied by many different microstructural rearrangements including dislocation movement, aging of microstructure, and grain-boundary cavitation. Over the preceding decades, many numerical and experimental investigations have been performed to improve the knowledge of creep of structures under high temperature. Creep constitutive relationship, creep damage evolution equation, and creep life prediction method are three main topics.Hayhurst et al. presented a methodology for accurately calibrating constitutive parameters for a 1/2Cr–1/2Mo–1/4V ferritic steel. The accurate description achieved is attributed to the physical basis of the constitutive equations and particularly to the state variables that represents the coarsening of the carbide precipitates and the creep constrained cavity growth [1, 2]. Hore and Ghosh developed a simple method of estimating material parameters for Dyson-McLean model [3]. Constitutive equations for time independent plasticity and creep of 316 stainless steel at 550°C were given by Hayhurst et al. [4]. Ma et al. presented a method for determining the power law creep constants using the small punch (SP) creep test [5]. The biggest advantage of SP creep test is that it can be used to evaluate remaining creep life using very small specimens extracted from in-service components. Saad et al. developed a material constitutive model for the P91 and the P92 steels under cyclic loading and high temperature conditions [6]. Bolton proposed a characteristic-strain model of creep of analyzing long term-relaxed stresses and creep strains in engineering components under steady load [7]. Bolton independently examined the worked example presented in BSI document PD6605-1:1998, to illustrate the selection, validation, and extrapolation of a creep rupture model using statistical analysis [8]. Wilshire and Scharning presented a new approach to analysis of stress rupture data allowing rationalization, extrapolation, and interpretation of multibatch creep life measurements reported for ferritic 1Cr–0.5 Mo tube steel [9]. Holdsworth et al. reviewed results are of an ECCC work program to investigate procedures for the practical representation of mean creep behavior for well-specified alloys from large multisource, multicast strain-time datasets. Leinster proposed a method of creep rupture data extrapolation based on physical processes [10].Zhang et al. studied creep-fatigue interaction damage evolution of the nuclear engineering materials modified 9Cr–1Mo steel with continuum damage mechanics (CDM) theory [11]. Wilshire and Burt interpreted normal creep curves in terms of the deformation mechanisms controlling strain accumulation and the damage processes causing tertiary acceleration and eventual failure [12]. Hyde et al. used single-state variable and three-state variable creep damage constitutive models to investigate the material behavior of two P91 steels of differing strength [13]. Spindler determined the material properties of some creep and constant strain rate tests on a Type 347 weld metal, and then various creep damage models are used to predict the creep damage in some creep-fatigue tests on the same Type 347 weld metal [14, 15]. Guan et al. presented quantitative study of creep cavity area of HP40 furnace tubes [16]. Hyde et al. presented a novel modelling process for creep crack growth prediction of a 316 stainless steel using continuum damage mechanics, in conjunction with finite element (FE) analysis [17]. Smith et al. investigated the type IV creep cavity accumulation and failure in steel welds [18].Mackerle reviewed the finite element methods applied to creep and creep fracture/damage of engineering materials and structures from the theoretical as well as practical points of view [19]. Masuyama interrupted large-size cross-weld creep rupture testing at given creep life fractions until rupture to measure the hardness, microstructure, and potential drop in the heat affected zones of welds to clarify creep degradation in welds of Mod.9Cr-1Mo steel [20]. Ling et al. performed several small punch creep tests on Type 304 stainless steel at 650°C and presented a finite element model with modified Kachanov-Rabotnov creep damage constitutive equations [21]. Izaki et al. proposed a residual creep life assessment method for boiler pipes using small punch creep (SPC) test [22]. Massé and Lejeail numerically investigated the creep behaviour and damage mechanisms of modified 9Cr1Mo steel between 450°C and 650°C [23, 24]. Weber et al. developed a method for creep life prediction for pipe bends with Graham-Wallas creep law [25]. Oldham and Abou-Hanna presented a fast and effective method for creep-fatigue life prediction of 9Cr-1Mo (grade 91) for a temperature range of 500°C−550°C [26]. Oh et al. proposed a method to simulate creep failure using finite element damage analysis and the method was applied to simulate creep crack growth in six different types of cracked specimens of 316H at 550°C. The creep damage model is based on the creep ductility exhaustion concept, and incremental damage is defined by the ratio of incremental creep strain and multiaxial creep ductility [27, 28]. Yao et al. grouped the existing theories and creep design approaches into three categories, that is, the classical plastic theory (CPT) based approach, the cavity growth mechanism (CGM) based approach, and the continuum damage mechanics (CDM) based approach [29].Beside these, many efforts are devoted to the life prediction of turbine blade. Lewis and Beckwith reviewed the life prediction approaches of the turbine blade [30]. Abu et al. provided a life assessment tool for aero jet engine blades by integrating suitable models and software with the Neu/Sehitoglu damage model [31]. Marahleh et al. predicted the operating life of service-exposed blades used in industrial gas turbines [32]. Chen et al. proposed a power-exponent function model for the life prediction of turbine blades under creep-fatigue interaction [33, 34]. Rodríguez et al. developed artificial neural network (ANN) to predict the useful life (UL) of the blades [35]. Schönbauer et al. investigated the influence of corrosion pits on the endurable fatigue loading in different environments and at various stress ratios for 12% Cr steam turbine blade steel [36]. Tawancy and Al-Hadhrami compared the microstructural changes of unused and used blades in power generation [37].Although many researches have conducted on the creep performance of the turbine blade, previous works always perform the finite element calculation through complex creep and damage relations with user subroutine. In the present research, a simple and feasible approach is proposed to investigate the creep life of turbine blade.


## 2. Material Characterization

This section gives the thermophysical parameters, creep constitutions, and creep damage evolution relationship of the turbine blade material GH4169. GH4169 is a domestic high temperature alloy, known as Inconel 718 in USA.Thermal and mechanical properties such as thermal conductivity, specific heat, elastic modulus, Poisson’s ratio, and thermal expansion coefficient are presented in Tables1, 2, 3, 4, and 5 [38]. These parameters are temperature-dependent. Density of GH4169 is 8240 kg/m3 and is assumed to be a constant.Table 1
Thermal conductivity of GH4169 with different temperatures.
T/°C
100
200
300
400
500
600
700
800
900
1000
λ/(W/(m·°C))
14.7
15.9
17.8
18.3
19.6
21.2
22.8
23.6
27.6
30.4Table 2
Specific heat of GH4169 with different temperatures.
T/°C
300
400
500
600
700
800
900
1000
C/(J/(kg·°C))
481.4
493.9
514.8
539
573.4
615.3
657.2
707.4Table 3
Elastic modulus of GH4169 with different temperatures.
T/°C
25
400
500
650
750
E/GPa
205
175.5
168.5
142
130.5Table 4
Poisson’s ratio of GH4169 with different temperatures.
T/°C
25
300
400
500
600
650
750
μ
0.321
0.329
0.339
0.344
0.355
0.361
0.381Table 5
Thermal expansion coefficient of GH4169 with different temperatures.
T/°C
100
200
300
400
500
600
700
800
900
1000
α/(10−6C-1°)
11.8
13.0
13.5
14.1
14.4
14.8
15.4
17
18.4
18.7The most important and widely used constitutive equation to predict the secondary creep is Norton’s power law equation:(1)ε˙cr=C1σC2e-C3/T,where ε˙cr is the steady state creep strain rate, σ is stress (MPa), T is temperature (K), C1, C2, and C3 are material constant which should be determined based on creep test data, and they are C1=2.147×10-70.03, C2=10.171, and C3=50825.890, respectively [39].Creep caused damage is also considered in the present research, and the damage evolution relationship is given by the modified Lemaitre-Chaboche model [40]:(2)dDCdt=σAr1-DC-k,where DC is the creep damage, t is time (h), σ is stress (MPa), and k is given by(3)k=a0+a1σ-z+a2σ-z2,where r, A, a0, a1, a2, and z are material constant which should be determined based on creep test data and are shown in Table 6 [41].Table 6
Thermal expansion coefficient of GH4169 with different temperatures.
Parameter
r
A
z
a
0
a
1
a
2
Value
13.19
1209
733.25
13.2478
0.7865× 10−4
0.1924× 10−3It should be noted that as (2) is nonlinear, the computation of the damage is an iterative process.


## 3. Thermomechanical Analysis

In the present research,E3 (energy efficient engine) high pressure turbine blade is employed based on the airfoil profile published by NASA [42]. Geometry of the turbine blade is firstly created in CAD software and then imported into ANSYS, which is shown in Figure 1. The model details at top and bottom of the blade are ignored in the present research; at the same time, the bottom of the blade is extended to simulate the effect of the tongue and groove.Figure 1
Finite element discretization of the turbine blade.


### 3.1. Thermal Analysis

Thermal analysis should be conducted to obtain the temperature field of the turbine blade. 3D fluid thermal analysis is performed in the present analysis with FLUENT. The basic equations for fluid dynamics are as follows [43].(1) Continuity Equation. Continuity equation is also called the conservation of mass, which ensures that the total mass is conserved; in other words, the total mass of a fluid system is completely accounted for. In three dimensions, the continuity equation is(4)∂ρ∂t+∇·ρu=0,where ρ is the density, t is time, u is the velocity vector, and ∇ is the gradient operator.(2) Momentum Conservation Equation. The principal of conservation of linear momentum means the total force generated by the momentum transfer in each direction is balanced by the rate of change of momentum in each direction and is given by(5)ρ∂u∂t+u·∇u=∇·σ+ρf,where f is the body force vector and σ is the Cauchy stress tensor and is defined by(6)σ=μ∇u+∇uT-pI,where μ is the shear viscosity of fluid, superscript “T” means transpose, p is pressure, and I is the identity matrix.(3) Energy Conservation Equation. The energy balance can be obtained as heat entering the control volume by convection and heat entering the control volume by diffusion are equal to heat exiting the control volume by convection and heat exiting the control volume by diffusion and rate of change of energy within the control volume. Energy conservation equation is given by(7)ρCp∂T∂t+u·∇T=-∇·q+Q,where Cp is heat capacity, T is temperature, q is the heat flux vector, and Q is the internal heat generation.(4) Turbulent Flow Equation. Turbulent k-ε is widely used in engineering practice to study turbulent flow, and the turbulent kinetic k equation and turbulent dissipation ε equation are given, respectively, by(8)∂ρk∂t+∇·ρuk=∇·μ+μtσk∇k-ρε+μtPG,∂ρε∂t+∇·ρuε=∇·μ+μtσε∇ε-ρC2ε2k+μtC1εkPG,where turbulent viscosity coefficient μt and turbulent kinetic generation term PG satisfied(9)μt=ρCμk2ε,PG=2∂u∂x2+∂v∂y2+∂w∂z2+∂u∂y+∂v∂x2+∂u∂z+∂w∂x2+∂v∂z+∂w∂y2,where k is turbulent kinetic energy, ε is the turbulent dissipation rate, and μt, σk, σε, C1, C2, and Cμ are constant.The fluid heat transfer analysis is conducted with FLUENT after importing the finite element model from ANSYS.Convective heat transfer boundary is applied at the inner surface of the cooling channel of the turbine blade, and the convective heat transfer coefficient and wall temperature are assumed to be 400 W/m2K and 600 K, respectively. The inlet pressure is 1.324 MPa and the inlet temperature is 1633 K. Temperature field of the turbine blade is given in Figure 2.Figure 2
Temperature field of the turbine blade.It can be seen from Figure3 that the temperature is ranging from 770 K to 920 K, and the maximal temperature is about 920 K at the bottom of the leading edge. In general, when temperature is larger than 0.3 times of the melt point, creep will become important, and the melt point of GH4169 is about 1533 K, which means creep plays a very important role in the life prediction of the turbine blade.Figure 3
Equivalent stress field of the turbine blade under inertial force.


### 3.2. Mechanical Analysis

There are different sources of loads imposed on the turbine blade. Due to the rotation, the blade is subjected to inertial force which acts along the axial direction, and the angular velocity of the blade is 13223 rpm. Aerodynamic pressure is not considered in the present research. Temperature field obtained in the previous section is applied on the finite element node as body forces. The computation is conducted with ANSYS, and SOLID185 element with hexahedron mesh is used. There are 11026 meshes and 14630 nodes. Three load cases are calculated; only inertial force, only temperature, both inertial force and temperature, and the equivalent stress field of the turbine blade under these three conditions are shown in Figures3, 4, and 5, respectively.Figure 4
Equivalent stress field of the turbine blade under temperature.Figure 5
Equivalent stress field of the turbine blade under both inertial force and temperature.It can be seen from Figures3–5 that, under individual inertial force and temperature, the maximal equivalent stress of the turbine blade is 800 MPa and 140 MPa respectively, while with the consideration of both inertial force and temperature, the maximal equivalent stress is 850 MPa. It is found that inertial force is the primary source of the blade stress, and thermal stress is secondary. The main effect of the temperature is that of activation of the creep process.


## 3.1. Thermal Analysis

Thermal analysis should be conducted to obtain the temperature field of the turbine blade. 3D fluid thermal analysis is performed in the present analysis with FLUENT. The basic equations for fluid dynamics are as follows [43].(1) Continuity Equation. Continuity equation is also called the conservation of mass, which ensures that the total mass is conserved; in other words, the total mass of a fluid system is completely accounted for. In three dimensions, the continuity equation is(4)∂ρ∂t+∇·ρu=0,where ρ is the density, t is time, u is the velocity vector, and ∇ is the gradient operator.(2) Momentum Conservation Equation. The principal of conservation of linear momentum means the total force generated by the momentum transfer in each direction is balanced by the rate of change of momentum in each direction and is given by(5)ρ∂u∂t+u·∇u=∇·σ+ρf,where f is the body force vector and σ is the Cauchy stress tensor and is defined by(6)σ=μ∇u+∇uT-pI,where μ is the shear viscosity of fluid, superscript “T” means transpose, p is pressure, and I is the identity matrix.(3) Energy Conservation Equation. The energy balance can be obtained as heat entering the control volume by convection and heat entering the control volume by diffusion are equal to heat exiting the control volume by convection and heat exiting the control volume by diffusion and rate of change of energy within the control volume. Energy conservation equation is given by(7)ρCp∂T∂t+u·∇T=-∇·q+Q,where Cp is heat capacity, T is temperature, q is the heat flux vector, and Q is the internal heat generation.(4) Turbulent Flow Equation. Turbulent k-ε is widely used in engineering practice to study turbulent flow, and the turbulent kinetic k equation and turbulent dissipation ε equation are given, respectively, by(8)∂ρk∂t+∇·ρuk=∇·μ+μtσk∇k-ρε+μtPG,∂ρε∂t+∇·ρuε=∇·μ+μtσε∇ε-ρC2ε2k+μtC1εkPG,where turbulent viscosity coefficient μt and turbulent kinetic generation term PG satisfied(9)μt=ρCμk2ε,PG=2∂u∂x2+∂v∂y2+∂w∂z2+∂u∂y+∂v∂x2+∂u∂z+∂w∂x2+∂v∂z+∂w∂y2,where k is turbulent kinetic energy, ε is the turbulent dissipation rate, and μt, σk, σε, C1, C2, and Cμ are constant.The fluid heat transfer analysis is conducted with FLUENT after importing the finite element model from ANSYS.Convective heat transfer boundary is applied at the inner surface of the cooling channel of the turbine blade, and the convective heat transfer coefficient and wall temperature are assumed to be 400 W/m2K and 600 K, respectively. The inlet pressure is 1.324 MPa and the inlet temperature is 1633 K. Temperature field of the turbine blade is given in Figure 2.Figure 2
Temperature field of the turbine blade.It can be seen from Figure3 that the temperature is ranging from 770 K to 920 K, and the maximal temperature is about 920 K at the bottom of the leading edge. In general, when temperature is larger than 0.3 times of the melt point, creep will become important, and the melt point of GH4169 is about 1533 K, which means creep plays a very important role in the life prediction of the turbine blade.Figure 3
Equivalent stress field of the turbine blade under inertial force.


## 3.2. Mechanical Analysis

There are different sources of loads imposed on the turbine blade. Due to the rotation, the blade is subjected to inertial force which acts along the axial direction, and the angular velocity of the blade is 13223 rpm. Aerodynamic pressure is not considered in the present research. Temperature field obtained in the previous section is applied on the finite element node as body forces. The computation is conducted with ANSYS, and SOLID185 element with hexahedron mesh is used. There are 11026 meshes and 14630 nodes. Three load cases are calculated; only inertial force, only temperature, both inertial force and temperature, and the equivalent stress field of the turbine blade under these three conditions are shown in Figures3, 4, and 5, respectively.Figure 4
Equivalent stress field of the turbine blade under temperature.Figure 5
Equivalent stress field of the turbine blade under both inertial force and temperature.It can be seen from Figures3–5 that, under individual inertial force and temperature, the maximal equivalent stress of the turbine blade is 800 MPa and 140 MPa respectively, while with the consideration of both inertial force and temperature, the maximal equivalent stress is 850 MPa. It is found that inertial force is the primary source of the blade stress, and thermal stress is secondary. The main effect of the temperature is that of activation of the creep process.


## 4. Creep Life Prediction

### 4.1. Computational Flowchart

Equations (1) and (2) are implemented within ANSYS in the present research. With the development of the creep process, the stress is relaxed and becomes smaller, while creep damage becomes larger. As damage is affected by stress and temperature, which is quite different from element to element, creep in each element is different. In the present research, effect of damage to the blade is realized by changing Young’s modulus of the material:(10)E=E01-DC,where E is present Young’s modulus and E0 is original Young’s modulus. It is noted that even original Young’s modulus of each element is different as the temperature of each element is different.The computations are conducted by the following steps.Step 1.
Import CAD model of the turbine blade into ANSYS.Step 2.
Mesh the turbine blade and assign every element with different material number.Step 3.
Import finite element model into FLUENT and perform the fluid heat transfer computation to obtain the heat flux field of the outer surface of the turbine blade.Step 4.
Import the heat flux field of the outer surface of the turbine blade obtained in Step3 and apply boundary conditions at the surface of the cooling channel and then perform the heat transfer computation to obtain the temperature field of the turbine blade.Step 5.
Switch element type from thermal analysis to structural analysis and apply node temperature obtained in Step4 as body force and structural boundary conditions and inertial force. Initialize the damage of each element.Step 6.
Begin computation and give displacement, stress, and strain.Step 7.
Compute element damage with (2).Step 8.
Evaluate the safety of the turbine blade with failure criterion. If the turbine blade is failed, the present time will be the lifetime of the turbine blade. If not, modify Young’s modulus of each element with element damage obtained in Step7 and then turn to Step 6 to perform computation of the next time step.Two-creep failure criterion is considered in the present research, one is creep rupture when the maximum damage of the structure reaches a threshold value, and the other is creep deformation failure when the creep strain or creep deformation reaches a threshold value. In the present paper, lifetime based on these two failure modes is called strength lifetime and stiffness lifetime, respectively, since the gap between the rotor and stator is usually less than 1/1000 of the rotational radius of the blade to prevent or reduce the gas leakage through the blade tip-gap.Load and boundary conditions in creep analysis are the same as in the mechanical analysis, and during the whole computation these conditions are assumed to be constant.


### 4.2. Strength Lifetime

In the present research, threshold value of element damage is defined byDC=0.4, as the remaining creep time before complete failure occurs is very small compared to the total creep time. Time when the maximal element damage reaches 0.4 is defined as the strength lifetime of the turbine blade. It is found that the strength lifetime of the turbine blade in the present research is 441 h, with a maximal element damage of 0.415. After creep for 441 h, the equivalent stress and element damage of the turbine blade are shown in Figures 6 and 7, respectively. Figures 8 and 9 give the evolution of the maximal element damage and maximal equivalent stress.Figure 6
Equivalent stress of the turbine blade after creep 441 h.Figure 7
Element damage of the turbine blade after creep 441 h.Figure 8
Evolution of the maximal element damage.Figure 9
Evolution of the maximal equivalent stress.Compared with Figures5 and 6, it can be found that after creep for 441 h, the maximal equivalent stress decreases from 800 MPa to 558 MPa. It can be seen from Figure 7 that the maximal element damage locates at the area that maximal stress exists, this is, because the damage is primarily affected by the stress as shown in (2). The evolution of the maximal element damage shown in Figure 8 reveals that the maximal element damage increases linearly at the first and second creep stages and then at the third stage, damage increases rapidly until rupture. Figure 9 shows the relaxation of the maximal equivalent stress; it is very clear that stress decreases rapidly at the very beginning and after a very short time, stress begins the steady relaxation until the end of the creep when stress decreases rapidly to fracture.


### 4.3. Stiffness Lifetime

In the present research, threshold value of creep strain is defined byεcr=1% [44]. Figures 10 and 11 show the creep strain field of the turbine blade after creeps 433 h and 855 h, respectively.Figure 10
Creep strain of the turbine blade after creep 443 h.Figure 11
Creep strain of the turbine blade after creep 856 h.It can be seen from Figures10 and 11 that, after creep 443 h, the maximal creep strain of the turbine blade is 0.5997%, and it is smaller than the threshold value and the threshold value is reached at 856 h with the maximal creep strain 1.07%, which means the stiffness lifetime of the turbine blade is 856 h. Compared with the strength lifetime and stiffness lifetime, it is found that strength lifetime is much smaller than the stiffness lifetime which means that the turbine blade may be broken before too much deformation exists.


## 4.1. Computational Flowchart

Equations (1) and (2) are implemented within ANSYS in the present research. With the development of the creep process, the stress is relaxed and becomes smaller, while creep damage becomes larger. As damage is affected by stress and temperature, which is quite different from element to element, creep in each element is different. In the present research, effect of damage to the blade is realized by changing Young’s modulus of the material:(10)E=E01-DC,where E is present Young’s modulus and E0 is original Young’s modulus. It is noted that even original Young’s modulus of each element is different as the temperature of each element is different.The computations are conducted by the following steps.Step 1.
Import CAD model of the turbine blade into ANSYS.Step 2.
Mesh the turbine blade and assign every element with different material number.Step 3.
Import finite element model into FLUENT and perform the fluid heat transfer computation to obtain the heat flux field of the outer surface of the turbine blade.Step 4.
Import the heat flux field of the outer surface of the turbine blade obtained in Step3 and apply boundary conditions at the surface of the cooling channel and then perform the heat transfer computation to obtain the temperature field of the turbine blade.Step 5.
Switch element type from thermal analysis to structural analysis and apply node temperature obtained in Step4 as body force and structural boundary conditions and inertial force. Initialize the damage of each element.Step 6.
Begin computation and give displacement, stress, and strain.Step 7.
Compute element damage with (2).Step 8.
Evaluate the safety of the turbine blade with failure criterion. If the turbine blade is failed, the present time will be the lifetime of the turbine blade. If not, modify Young’s modulus of each element with element damage obtained in Step7 and then turn to Step 6 to perform computation of the next time step.Two-creep failure criterion is considered in the present research, one is creep rupture when the maximum damage of the structure reaches a threshold value, and the other is creep deformation failure when the creep strain or creep deformation reaches a threshold value. In the present paper, lifetime based on these two failure modes is called strength lifetime and stiffness lifetime, respectively, since the gap between the rotor and stator is usually less than 1/1000 of the rotational radius of the blade to prevent or reduce the gas leakage through the blade tip-gap.Load and boundary conditions in creep analysis are the same as in the mechanical analysis, and during the whole computation these conditions are assumed to be constant.


## 4.2. Strength Lifetime

In the present research, threshold value of element damage is defined byDC=0.4, as the remaining creep time before complete failure occurs is very small compared to the total creep time. Time when the maximal element damage reaches 0.4 is defined as the strength lifetime of the turbine blade. It is found that the strength lifetime of the turbine blade in the present research is 441 h, with a maximal element damage of 0.415. After creep for 441 h, the equivalent stress and element damage of the turbine blade are shown in Figures 6 and 7, respectively. Figures 8 and 9 give the evolution of the maximal element damage and maximal equivalent stress.Figure 6
Equivalent stress of the turbine blade after creep 441 h.Figure 7
Element damage of the turbine blade after creep 441 h.Figure 8
Evolution of the maximal element damage.Figure 9
Evolution of the maximal equivalent stress.Compared with Figures5 and 6, it can be found that after creep for 441 h, the maximal equivalent stress decreases from 800 MPa to 558 MPa. It can be seen from Figure 7 that the maximal element damage locates at the area that maximal stress exists, this is, because the damage is primarily affected by the stress as shown in (2). The evolution of the maximal element damage shown in Figure 8 reveals that the maximal element damage increases linearly at the first and second creep stages and then at the third stage, damage increases rapidly until rupture. Figure 9 shows the relaxation of the maximal equivalent stress; it is very clear that stress decreases rapidly at the very beginning and after a very short time, stress begins the steady relaxation until the end of the creep when stress decreases rapidly to fracture.


## 4.3. Stiffness Lifetime

In the present research, threshold value of creep strain is defined byεcr=1% [44]. Figures 10 and 11 show the creep strain field of the turbine blade after creeps 433 h and 855 h, respectively.Figure 10
Creep strain of the turbine blade after creep 443 h.Figure 11
Creep strain of the turbine blade after creep 856 h.It can be seen from Figures10 and 11 that, after creep 443 h, the maximal creep strain of the turbine blade is 0.5997%, and it is smaller than the threshold value and the threshold value is reached at 856 h with the maximal creep strain 1.07%, which means the stiffness lifetime of the turbine blade is 856 h. Compared with the strength lifetime and stiffness lifetime, it is found that strength lifetime is much smaller than the stiffness lifetime which means that the turbine blade may be broken before too much deformation exists.


## 5. Comparisons withθ Projection Method

θ projection method is a widely used method in the lifetime prediction of high temperature structures. It is proposed by UK’s National Physical Laboratory [45], and this method assumed that the creep strain can be given by(11)εc=ε0+θ11-e-θ2t+θ3eθ4t-1,where εc is the creep strain, ε0 is the initial strain before creep occurs, and t is time. θ1(1-e-θ2t) and θ3(eθ4t-1) represent the creep at the first stage and the third stage, respectively. θii=1,2,3,4 are experimentally determined constants, and they should satisfy(12)log⁡θi=ai+biT+ciσ+diσT,where T is temperature and σ is stress. ai, bi, ci, and di are material constant, once they are obtained and θi under any temperature and stress can be determined by (12), and the creep strain can be obtained by (11); then the creep lifetime of the structure will be obtained.Based on the experimental results of GH4169 [46], θii=1,2,3,4 are firstly determined and given in Table 7. Then ai, bi, ci, and di can be determined by data fitting with (12), and they are given in Table 8. Comparisons of experimental data [46] and fitting data are shown in Figures 12, 13, and 14, and 15.Table 7
Parameters ofθi with different temperature and stress.
Temperature/°C
Stress/MPa
θ
1
θ
2
θ
3
θ
4
600
740
0.010296
0.284201
2.093486
×
10
-
6
0.172685
650
750
0.013662
0.030494
2.421462
×
10
-
7
0.086381
660
700
0.016081
0.019141
6.367507
×
10
-
6
0.066379
670
700
0.007818
0.083223
1.419716
×
10
-
4
0.066127Table 8
Parameters ofai, bi, ci, and di with different θi.
Parameter
a
i
b
i
c
i
d
i
θ
1
425.933468
-
0.649289
-
0.581509
0.000883
θ
2
-
1040.439613
1.578947
1.423707
-
0.002164
θ
3
-
1836.649917
2.817091
2.489243
-
0.003832
θ
4
-
74.340425
0.110132
0.104673
-
0.000157Figure 12
Comparisons of experimental data [46] and fitting data under 873 K and 740 MPa.Figure 13
Comparisons of experimental data [46] and fitting data under 923 K and 750 MPa.Figure 14
Comparisons of experimental data [46] and fitting data under 933 K and 700 MPa.Figure 15
Comparisons of experimental data [46] and fitting data under 943 K and 700 MPa.It is found that the fitting data compare very well with the experimental results, so theθ projection method can be used to predict the creep lifetime of the GH4169 turbine blade. As shown in Section 3, the temperature and stress of the hot point of the turbine blade are 804 K and 699 MPa, respectively; substituting these two values in (12), θii=1,2,3,4 can be obtained. Then substituting θii=1,2,3,4 into (11) and assigns εc=1%, ε0=0, we can obtain the lifetime of the turbine blade with the θ projection method, which is 729.5 h, and this value compared well with the stiffness lifetime (856 h) by direct simulation. This comparison also shows the feasibility of the present numerical approach.


## 6. Conclusions

A numerical approach of lifetime prediction of the turbine blade with creep damage is proposed in the present paper and then applied to the lifetime prediction of high pressure turbine blade. The present approach can directly give the evolution of element stress, creep deformation, and element damage, which is very useful in the life prediction of high temperature structures. Lifetime of the turbine blade with two different creep failure criterions, as well as theθ projection method, is given. Numerical results show that the present numerical approach based on creep damage for lifetime prediction of high temperature structure is feasible and reliable and provides a technical support for high temperature structure safety evaluation and design. With the creep failure criterion of creep rupture and creep deformation failure, the lifetime of the turbine blade is 441 h and 856 h, respectively, and lifetime with θ projection method also based on creep deformation criterion is 729.5 h. The difference of the lifetime with different failure criterion shows different failure mechanism, and it is found that turbine blade failure is mainly caused by creep rupture; in other words, the blade may be broken before the creep deformation reaches its limitation.The present paper provides an alternative method to predict high temperature structure lifetime with creep damage, and future work should consider the effect of the interaction of creep and fatigue. Meanwhile, the present paper just shows the application of the present method in GH4169 and the application of the present method in other superalloys is also interesting.



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*Source: 732502-2015-05-19.xml*