# Finite Element Modeling of Mode I Failure of the Single Contoured Cantilever CFRP-Reinforced Concrete Beam

Authors: T. Nicholas; D. Boyajian; S. E. Chen; A. Zhou
Journal: Journal of Structures
 (2013)

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## Abstract

The single contour cantilever beam (SCCB) test method has been developed with the intent to capture Mode I opening failures of CFRP-reinforced concrete beams. Recent development in the method explores possible shifting damage into the concrete substrate by using the International Concrete Repair Institute (ICRI) Surface Profile Level Three (SP3) as the desired CFRP bonded interface to concrete. To validate and explain the interface fracture behavior, finite element analysis using special cohesive elements has been performed. The cohesive element allows separation of the concrete substrate from the CFRP. This paper presents the simulation of laboratory test results, where failure in the substrates has been successfully reproduced. The simulation results indicate that finite element method using cohesive elements can successfully replicate Mode I critical strain energy release rate and the peak capacity of the laboratory tests and may have the potential to simulate actual applications.


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## Body

## 1. Introduction

Several laboratory methodologies have been developed over the past few years to measure Mode I critical strain energy release rate involving composite wrapped concrete beams. Failures of representative methodologies designed to isolate Mode I opening failure of a fracture interface include the modified double cantilever beam (DCB) method [1], the peel test method [2], the membrane peeling method [3], and the single contour cantilever beam (SCCB)  method  [4]. All the above methods are variations of each other with different strengths and weaknesses, depending on the application. However, the SCCB method exclusively ensures that the failure will always be the first mode. A second advantage of the SCCB method is the elimination of compliance measurements.The SCCB method was first developed by Boyajian [5] and has been utilized to determine the critical strain energy release rates at the bonding interface between concrete and carbon fiber-reinforced polymer (CFRP) [4, 6, 7].  Figure 1 shows the schematics of the SCCB test including the test specimen that consists of concrete base plate, CFRP bonded layer, the wood contour, and the experimental setup that includes a steel strap for pulling on the wood contour. Figure 2(a) shows the actual test setup within a MTS test apparatus with arrow indicating the direction of pull load. With the SCCB test, the high tensile capacity LVL is loaded with a normal force, P, inducing Mode I failure behavior of the CFRP to concrete interface and thus avoiding the arm break-off failure. The starter crack is created by debonding the CFRP from the concrete substrate for the first fifty millimeters of the bond length. This is achieved by pretreating the starter crack location with a substrate with tape or wax paper. The starter crack can be seen in Figure 2(c) as the white shaded area on the substrate.Figure 1
Schematic of single contoured cantilever beam test.The SCCB test: (a) experimental setup (arrow indicating load direction); (b) different concrete surfaces (SP1, mould, and SP3); (c) interface  surface  of failed specimens: FRAC1031_T1 and FRAC1031_T2.
(a)
SCCB test setup
(b)
Concrete surfaces (left to right): SP1, mould, and SP3
(c)
Failed specimen showing exposed substrateThe current study focused on using the International Concrete Repair Institute Surface Preparation 3 (ICRI SP3) [8] method to ensure failure within the substrate. In order to achieve the necessary surface profile, the ICRI standards allow for shot blasting, sand blasting, or pressurized water to be used. After numerous trials, the surface preparation method that produced the most consistent results was pressurized water from a 34.47 MPa pressure washer. Additionally, a set of surface profile tabs were obtained to assist in classifying the surface. The surface profile tabs are raised surface, rubber square swatches which illustrate each of the ICRI surface profiles. The common method for classifying the surface is to check the target surface tab (SP 3), as well as, the tab above (SP 4) and the tab below (SP 2). Figure 2(b) shows the different surface areas: SP1, mould, and SP3. Study of failure in the substrates is important as it may lead to premature failure and brittle failures [9]. Figure 2(c) shows the failed specimens clearly indicating failure within concrete substrate.This paper reports finite element (FE) simulation of a series of SCCB tests conducted with concrete specimens prepared with SP3 surfaces, which was not previously attempted. In order to develop realistic FE models, a damage evolution approach has been adopted. The results presented shows that the approach effectively predicts the critical strain energy release rate of the bonded interface. The model also compares well with the laboratory test results.


## 2. Mode 1 Fracture

Fracture behavior can normally be characterized as beginning with crack initiation and intensifying through crack propagation. At the onset of crack initiation, the crack propagation behavior becomes a function of the displacement of the failed interface surfaces [10–12]. Irwin [13] defined three failure modes to describe how the surfaces are displaced by Mode I, Mode II, and Mode III failures. Mode I describes a failure of the interface bond that occurs normal to the failed surface, often referred to as the opening mode. While most fractures can be described by one of the failure modes, the mixing of mode failures, such as  Mode I-Mode  II, is also a possibility. The ability of an engineering material to resist these failure modes is frequently referred to as fracture toughness. The commonly accepted method for representing fracture toughness is the critical release strain energy, GC, as defined by the Irwin-Kies equation [13, 14]:
(1)GC=(PC22b)(dCda),
where  GC is the critical strain energy release rate (J/m2), PC  is the critical load (N), b  is the width of the specimen (mm), and dC/da is the rate of compliance (C) with respect to crack length (a) (N−1).


## 3. Analytical Modeling of Fracture and the Cohesive Elements

As it pertains to the current study, finite element modeling of the SCCB can be divided into two categories: compliance of the SCCB wood contour and fracture. As there exist a number of methods to model crack propagation, it is important to select an efficient and accurate representation of the failure behavior. While the SCCB has not specifically been modeled for fracture, a number of past studies have focused on the fracture of the double cantilever beam and the peel test.  Most recently,  Nicholas  [15], Huang and Lyons [16], and Diehl [17] proposed methodologies for modeling the DCB, a modified DCB, and a peel test, respectively. For each study, the model was used to determine the total energy required to propagate the crack tip. The total energy required to fracture concrete can be taken as
(2)Gf=1B*(W-a)∫Pdδ,
where Gf is the specific fracture energy (J/m2), B is the specimen thickness (mm), W is the fracture width (mm), a is the initial crack length (mm), P is the point load (N), and δ is the displacement perpendicular to crack length (mm).Huang and Lyons [16] employed the J-integral algorithm in ABAQUS to model the crack propagation of a modified DCB as well as to calculate the critical strain energy release rate. The methodology produced good results compared to the basic energy equation and laboratory results. However, according to  Nicholas   [15], the cohesive element is an efficient approach to modeling fracture, as well, when the crack propagation is known a priori.Diehl [17] proposed utilizing an ABAQUS cohesive element to model the bonded region between elastic and inelastic materials, namely, a thin film. In the study, a penalty-based approach to debonding was proposed. In the penalty approach or damage evolution, as the elements ultimate stress capacity (traction (MPa), tULT) is achieved, the element is deleted from the model and does not provide further resistance to load. This damage process is illustrated in Figure 3, where the ultimate nominal stress serves as the elastic limit and the area under the curve provides the critical fracture energy, Gc.  This “unzipping” behavior closely resembles the behavior of the SCCB during crack propagation. Therefore, the cohesive element was used to model the bond interface in the current study.Figure 3
Damage evolution curve for ABAQUS cohesive element (t (MPa), δ (mm)) [18].ABAQUS assumes that traction separation is linear elastic prior to undergoing complete damage evolution. The elastic behavior is represented by a constitutive matrix in terms of nominal stress and strain. While ABAQUS provides a three-dimensional model, torsional effects will not be presented here because only a two-dimensional model was employed. It should be noted that, while a mixed mode process may be present (normal and shear), the SCCB test inherently provides a Mode I failure which is predominantly normal to the interface.Given that the nominal stress can be written as [18]
(3)tULT={tn0},
where t is the total separation stress and tn is the normal separation stress and strain can be written as
(4)ε={εn},
where ε is the total separation strain   and  εn=(δn/To) is the  normal separation strain, and To is the original thickness of the element, the elastic behavior can then be written as follows:
(5)tULT={tn0}=[Kn]{Δn}=Kε,
where  Kn is the stiffness that relates to the nominal stress  (N/m3). The subscripts for the stiffness matrix represent again the normal separation (n).Following the initial elastic response, damage is initiated provided that one of the user defined  criteria  is met. The damage initiation criteria can be defined in ABAQUS utilizing stress, strain, or quadratic function. The current work utilized a maximum stress criterion as follows [18]:
(6)max{〈tn〉tn0}=1,
where 〈tn〉 is the normal stress state and  tn0 is the peak normal stress.Once the damage criterion is achieved, the material undergoes a softening process or loss of stiffness that perpetuates the damage evolution. ABAQUS [18] represents damage evolution by introducing the damage variable, D, which ranges in magnitude from 0 to 1. The effect of the damage variable is given by
(7)tn0={(1-D)tndtnd,
where  tnd is the predicted normal stress (undamaged) and D is the damage variable.


## 4. Laboratory SCCB Tests

A series of SCCB tests was carried out [7]. The single cantilever contoured beam (SCCB) used for this study is comprised of a substrate material (reinforced concrete), a fiber-reinforced polymer layer, and a wood contour as illustrated in Figure 2. This study utilized the previously calibrated contour developed by Lawrence and Boyajian  [7]  with a rise of 95 mm.As previously stated, the bonding substrate for the system is a reinforced concrete beam as illustrated in Figure2. The target ranges for the concrete compressive strength were 27.58±1.73 MPa, 34.50±1.73 MPa, and 41.40±1.73 MPa among batches for consistency and comparison to previous work. The  only derivation  in testing protocol from previous studies was the mix design.  The previous studies  ([6, 7])  utilized approximately 1 : 1 : 1 and 1 : 2 : 4 ratios as the mix designs so as to increase the workability of the concrete into the mold and produce a consistent concrete surface. For the current work, the mix design was found using ACI 301 (2005) mix specifications which produced the more commonly used 1 : 3 : 5 mix design. While the issues of workability and a constant concrete surface are still true for the current study, they were addressed by employing a vibration table to fill voids and work the concrete into the mold. Additionally, a slump of 89 mm was used to further aid in workability. The only additive used in the mix design was an air entrainment agent which was added to achieve 6.5 percent ±1 percent average air content.  The addition of an air entrainment agent was necessary due to future durability testing.The testing regimen used by the entire study (compressive strengthf′c of substrate effects on GC) required a total of nine concrete beam specimens. For each batching, the concrete was tested for slump, air entrainment, and compressive strength. The batch was considered successful if it met the mix design requirements previously defined. The average compressive strengths among the batches were 28.96 MPa (SD = 2.34 MPa), 36.89 MPa (SD = 0.10 MPa), and 40.85 MPa (SD = 0.10 MPa) with all batches meeting the compressive strength standards.


### 4.1. Fiber-Reinforced Polymer System

The fiber-reinforced polymer used in the study consists of two parts: the carbon fibers and epoxy. The system selected for the study was Sikadur 301 two-part epoxy and SikaWrap Hex 103C carbon fiber due to the system’s increasing popularity in industry. The higher demand for the Sika 301 epoxy is a result of a lower cost for material and the lack of a primer coat, which in turn allows for faster construction times. The material properties for the system are listed in Table1.Table 1
Fiber-reinforced polymer properties (Sika).
SikaWrap Hex 103C
Sikadur 301
Tensile strength
3.793 GPa
52.0 MPa
Tensile modulus
234.5 GPa
2.000 GPa
Elongation
1.5%
3.5% at break


### 4.2. Microllam Laminated Veneer Lumber

The contour material used in the study is a wood product, 1.9E Microllam LVL (laminated veneer lumber). The material was selected to serve as the contoured member of the SCCB specimen due to the ease by which it could be shaped as required by the compliance results (refer back to Figure2). The material properties are listed in Table 2.Table 2
1.9E Microllam LVL properties.
Grade
G Shear modulus of elasticity
E Modulus of elasticity
E
min Adjusted modulus of elasticity
F
b Flexural stress
1.9E
819 MPa
13 GPa
6.6 GPa
18 MPaIn employing the SCCB testing methodology [5], the success of determining the critical strain energy release rate is directly related to the accuracy of compliance. As first presented in the Irwin-Kies equation, compliance, C, is represented by a ratio of displacement to load increment. In the absence of a contoured cantilever, the compliance of the uncontoured beam changes as the crack location, a, propagates along the structural member. As a result, calculating the critical strain release energy can only be achieved by continuously measuring the crack location during the experiment which is a difficult task. As a means to avoid the arduous measuring of crack tip location, a contoured shape is utilized that causes the compliance to change linearly in conjunction with crack propagation along the interface [5]. This linear relationship removes the dependence of load, P, and strain energy release rate, GI, from the crack tip location, a.In determining the optimized contour dimensions and in an effort to simplify the procedure, the dimensions of the contour are prescribed prior to analysis, except forhf (the height of the contour given in Figure 1 as 95 mm) which will be iterated in a finite element model (FE) to achieve several approximated contour shapes. The crack tip location begins at 51 mm (starter crack) loaded with 448 N and the corresponding contour deformation at the load location is recorded. The process is repeated for crack tip locations at 51 mm intervals up to 357 mm of specimen length. The resulting compliance, C (calculated as u/P), is plotted as a function of crack tip location, a.  The slope of the linear relationship provides the compliance gradient, dC/da. Subsequently, for each hf that yields acceptable compliance gradients, an experimental calibration must be performed to assist in the final optimization of the contour.This study utilized the previously calibrated contour developed by Lawrence and Boyajian  [7]  which had an hf=95 mm. The contour was modeled in ANSYS in an effort to check the compliance gradient. The resulting gradient used for the fracture studies was dC/da=1.49×10-5 N−1 which compares well with Boyajian [5].From the experimental study, three representative specimens (closest toGIC averages) of the nine pull test results are presented in Table 3, where GC and PC for the three different tests are presented along with the averaged values. Figure 2(c) shows the typical failed specimens, where failure plane showed exposed aggregates embedded in the substrates. The failure plane for all tests fell within the concrete matrix and lied within the substrate. Figure 4 shows the critical load versus crack opening displacement from the test results.Table 3
Representative experimental and analytical results.
Specimen
Critical load,Pc
G
I
c (initiation)
F
′
c
FRAC1031_T1
1494 N
384 J/m2
37 MPa
FRAC1031_T2
1245 N
267 J/m2
37 MPa
FRAC27_T3
1045 N
183 J/m2
29 MPa
Average
1261 N
278 J/m2
34 MPa
Finite element
1392 N
307 J/m2
37 MPaFigure 4
Critical strain energy curves for representative specimens.


## 4.1. Fiber-Reinforced Polymer System

The fiber-reinforced polymer used in the study consists of two parts: the carbon fibers and epoxy. The system selected for the study was Sikadur 301 two-part epoxy and SikaWrap Hex 103C carbon fiber due to the system’s increasing popularity in industry. The higher demand for the Sika 301 epoxy is a result of a lower cost for material and the lack of a primer coat, which in turn allows for faster construction times. The material properties for the system are listed in Table1.Table 1
Fiber-reinforced polymer properties (Sika).
SikaWrap Hex 103C
Sikadur 301
Tensile strength
3.793 GPa
52.0 MPa
Tensile modulus
234.5 GPa
2.000 GPa
Elongation
1.5%
3.5% at break


## 4.2. Microllam Laminated Veneer Lumber

The contour material used in the study is a wood product, 1.9E Microllam LVL (laminated veneer lumber). The material was selected to serve as the contoured member of the SCCB specimen due to the ease by which it could be shaped as required by the compliance results (refer back to Figure2). The material properties are listed in Table 2.Table 2
1.9E Microllam LVL properties.
Grade
G Shear modulus of elasticity
E Modulus of elasticity
E
min Adjusted modulus of elasticity
F
b Flexural stress
1.9E
819 MPa
13 GPa
6.6 GPa
18 MPaIn employing the SCCB testing methodology [5], the success of determining the critical strain energy release rate is directly related to the accuracy of compliance. As first presented in the Irwin-Kies equation, compliance, C, is represented by a ratio of displacement to load increment. In the absence of a contoured cantilever, the compliance of the uncontoured beam changes as the crack location, a, propagates along the structural member. As a result, calculating the critical strain release energy can only be achieved by continuously measuring the crack location during the experiment which is a difficult task. As a means to avoid the arduous measuring of crack tip location, a contoured shape is utilized that causes the compliance to change linearly in conjunction with crack propagation along the interface [5]. This linear relationship removes the dependence of load, P, and strain energy release rate, GI, from the crack tip location, a.In determining the optimized contour dimensions and in an effort to simplify the procedure, the dimensions of the contour are prescribed prior to analysis, except forhf (the height of the contour given in Figure 1 as 95 mm) which will be iterated in a finite element model (FE) to achieve several approximated contour shapes. The crack tip location begins at 51 mm (starter crack) loaded with 448 N and the corresponding contour deformation at the load location is recorded. The process is repeated for crack tip locations at 51 mm intervals up to 357 mm of specimen length. The resulting compliance, C (calculated as u/P), is plotted as a function of crack tip location, a.  The slope of the linear relationship provides the compliance gradient, dC/da. Subsequently, for each hf that yields acceptable compliance gradients, an experimental calibration must be performed to assist in the final optimization of the contour.This study utilized the previously calibrated contour developed by Lawrence and Boyajian  [7]  which had an hf=95 mm. The contour was modeled in ANSYS in an effort to check the compliance gradient. The resulting gradient used for the fracture studies was dC/da=1.49×10-5 N−1 which compares well with Boyajian [5].From the experimental study, three representative specimens (closest toGIC averages) of the nine pull test results are presented in Table 3, where GC and PC for the three different tests are presented along with the averaged values. Figure 2(c) shows the typical failed specimens, where failure plane showed exposed aggregates embedded in the substrates. The failure plane for all tests fell within the concrete matrix and lied within the substrate. Figure 4 shows the critical load versus crack opening displacement from the test results.Table 3
Representative experimental and analytical results.
Specimen
Critical load,Pc
G
I
c (initiation)
F
′
c
FRAC1031_T1
1494 N
384 J/m2
37 MPa
FRAC1031_T2
1245 N
267 J/m2
37 MPa
FRAC27_T3
1045 N
183 J/m2
29 MPa
Average
1261 N
278 J/m2
34 MPa
Finite element
1392 N
307 J/m2
37 MPaFigure 4
Critical strain energy curves for representative specimens.


## 5. SCCB Analytical Model

The SCCB was modeled using 2D plain strain plate quad elements in ABAQUS and represents the LVL contour, the concrete substrate, and the CFRP layer (see Table4). For FRP laminates, typically orthotropic layer elements are used [1]; however, for the 2D model, nondirectional element is used.Table 4
Summary of FE material input values.
Material
Young’smodulus
Poisson’sratio
Fractureenergy
Concrete
30 GPa
0.18
N/A
LVL contour
13 GPa
0.30
N/A
Cohesive
102 GPa
N/A
134 J/m2
CFRP
235 GPa
0.15
N/AThe interface region was geometrically inputted to represent a mixed layer of concrete and epoxy due to the deep intrusion of crack propagation into the substrate. This interfacial zone was considered to be the cohesive layer and was modeled using ABAQUS cohesive element, COH2D4. The material properties required to model the cohesive element areGc, K, nominal stress (traction), t, and separation, δ. The system was subjected to a 1.78 mm deflection of the contour tip, which corresponds to the laboratory results for the crack opening displacement (COD) at the critical load, Pc.Figure5 shows the FE model. Due to the deviation in concrete properties, averaged material properties from laboratory tests are used for the cohesive element: Gc=133.97 J/m2; K=102.45 N/m3 and nominal stress, 15.51 MPa. Table 3 provides a material summary for the SCCB model. The one area of concern in utilizing the cohesive element, as Duan et al. [19] pointed out, is the element size. Duan et al. [19] and others [12, 20] have proposed various analytical processes for determining cohesive element size and Diehl [17] proposed an element size of one-fifth of the model. The size of the cohesive element was 1/10 the size of the CFRP layer with an aspect ratio of 1 to 5. A close-up view of the final model is shown in Figure 6. It should be noted that the stress distribution at the location of the crack tip in Figures 5 and 7 ranged from 0 MPa to 48.46 MPa.Figure 5
Finite element model of the SCCB utilizing cohesive element.Figure 6
The finite element SCCB model.Figure 7
Close-up rendering of the damage evolution of the cohesive element.


## 6. Results and Discussion

Figure7 shows the stress distribution at critical load; significant crack propagation has penetrated into the interface. Over 50 cohesive elements have been removed (delamination) immediately after the critical load was achieved. Also illustrated in Figure 5, the stress distribution in the wood layer displayed typical Bernoulli bending behavior with compressive stresses of the cantilever at the top and the tensile stresses at the bottom. However, during the first fracture sequence of the SCCB, the interface was represented by a region of discontinuity as it pertains to the stress. The discontinuity is a result of the different material properties between the cohesive element, the concrete, and the FRP. The maximum stress in the FRP material is 48.46 MPa, which occurs at the crack tip, indicating that the composite wrap is being stressed.Figure8 shows the stiffness degradation within the interface (cohesive elements) and behind the crack. The analytical model produced reasonably close results compared to the laboratory results (Figure 8). Figure 8 is a rendering of the numerical model results as a function of all fractured specimens represented by the smeared gray area, indicating the experimental deviations. It should be noted that the laboratory results actually represent various compressive strengths of concrete, ranging from 29.0 MPa to 41.4 MPa. This will somewhat affect the specific fracture energy of the concrete as well as the effective stiffness of the cohesive layer.Figure 8
Finite element results compared to the companion laboratory results (straight line indicating nonseparation model with no CMZ).The critical load,Pc, was determined to be 1392 N at a crack opening displacement of 1.78 mm. The averaged critical load from the laboratory results was 1261 N at a crack opening displacement of 1.70 mm, yielding a percent difference of approximately 9 percent and 4.5 percent, respectively. The critical strain energy release rate from the finite element analysis was then calculated as 307 J/m2, which also corresponded well with the averaged critical strain energy release rate of 278 J/m2, yielding a percent difference of 9.4 percent. While the numerical results are acceptable as the percent differences are within the laboratory specimen percent differences, the behavior of the modeled fracture varied somewhat from the laboratory results. The fracture produced in the model is more representative of stable crack propagation rather than the moderately unstable fracture pattern produced in the laboratory experiments.Result from FE model with no cohesive material zone (CMZ) is also investigated, which shows significantly larger critical ultimate stress (straight line in Figure9). Furthermore, there is a slight, but negligible, difference in stiffness between the two models. Figure 10 shows the stress concentration in the nonseparation model, where the peak stress at initial fracture point is 71.6 MPa. Since the model is not allowed to crack, the FRP composite does not demonstrate realistic stress distribution as indicated in Figure 6. It is also of interest to note that high stress concentration exists within the concrete elements during loading (Figure 5), accurately portrayed possible penetrating into the substrate.Figure 9
Stiffness degradation along the cohesive zone (crack propagation) including the stiffness degradation behind the crack.Figure 10
Stress distribution in the nonseparation model.


## 7. Conclusions

The preceding work documents the effectiveness of modeling the delamination of CFRP that has been bonded to concrete utilizing the Abaqus defined cohesive element. The model does accurately predict the critical load,Pc, as well as the crack opening displacement, COD. Furthermore, without the use of the cohesive element, the stress distribution at the crack initiation cannot be modeled properly. The significance of the numerical modeling is the accurate portrayal of the debonding process of SCCB test method with SP3 surface: as was the case with the experiment results, the model bears out the deep penetration into the concrete substrate.Comparing to the nonseparation model (without cohesive element), the peak stress is significantly higher than the actual experimental results and the FRP material does not appear to resist the pull loading.There are a few areas need to be addressed to fully define the SCCB analytically.(1)
As multiple materials are contributing to the strength of the bond, it would be intuitive that each of these materials could be represented by multiple cohesive layers.(2)
One area of concern is the added concrete material to the contour during fracture. The addition of this material could impact the compliance.(3)
The nonhomogeneity of the wood and concrete caused some concern when comparing the numerical results to the laboratory results.(4)
Modeling the cohesive zone as a zero thickness element should be investigated for stiffness effects.



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*Source: 138617-2013-12-22.xml*