Foundations of Materials Science and Engineering
6th Edition
ISBN: 9781259696558
Author: SMITH
Publisher: MCG
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Chapter 7.10, Problem 39AAP
To determine
The time to stress rupture.
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Animated Figure 9.41 is a plot of the logarithm stress versus the Larson-Miller parameter for an S-590 alloy. A component made of this alloy is subjected to a stress of 600 MPa. At what temperature will the rupture lifetime be 200 h?
Question 1
You are working on a design team at a small orthopaedic firm. You have been asked to select a cobalt-
chrome-molybdenum (CoCr) material that will not experience plastic deformation under a specific mechanical test, as follows...
A tensile stress is applied along the long axis of a solid cylindrical rod that has a diameter of 10 mm. An applied load of some
magnitude F produces a 7x10³ mm change in diameter (see figure below, original shape is blue, elongated shape is unshaded).
Q1F: How would the "new alloy" material (with different properties as shown below) behave, assuming it has the same initial
diameter (10mm) and applied load (F) in the tensile test? That is, would it experience plastic deformation (yield) under the
conditions of this problem?
(ii)
The turbine blade root is found to contain a surface fatigue
crack of 3.3 mm during a routine maintenance inspection. The
major stop-start load cycle is experienced twice per day with
a minimum stress of 34 MPa and a maximum stress of 195
MPa. The turbine blade has a KIC of 75 MPa√m. Fatigue
crack growth rate data for this alloy is given by: the Paris law
constant, A = 4.5 x 10-11 and the Paris law exponent, m =
3.8. How many more stop-starts would you recommend be
used? Explain your reasoning. You can assume the shape
factor Q = 1.2, K is in MPaNm and a (crack length) is in m
Chapter 7 Solutions
Foundations of Materials Science and Engineering
Ch. 7.10 - What are the characteristics of the surface of a...Ch. 7.10 - Prob. 2KCPCh. 7.10 - Prob. 3KCPCh. 7.10 - Prob. 4KCPCh. 7.10 - Prob. 5KCPCh. 7.10 - Prob. 6KCPCh. 7.10 - Prob. 7KCPCh. 7.10 - Prob. 8KCPCh. 7.10 - Prob. 9KCPCh. 7.10 - How does the carbon content of a plain-carbon...
Ch. 7.10 - Describe a metal fatigue failure.Ch. 7.10 - What two distinct types of surface areas are...Ch. 7.10 - Prob. 13KCPCh. 7.10 - Prob. 14KCPCh. 7.10 - Prob. 15KCPCh. 7.10 - Describe the four basic structural changes that...Ch. 7.10 - Describe the four major factors that affect the...Ch. 7.10 - Prob. 18KCPCh. 7.10 - Prob. 19KCPCh. 7.10 - Prob. 20KCPCh. 7.10 - Prob. 21KCPCh. 7.10 - Determine the critical crack length for a through...Ch. 7.10 - Determine the critical crack length for a through...Ch. 7.10 - The critical stress intensity (KIC) for a material...Ch. 7.10 - What is the largest size (in mm) of internal...Ch. 7.10 - A Ti-6Al-4V alloy plate contains an internal...Ch. 7.10 - Using the equation KIC=fa, plot the fracture...Ch. 7.10 - (a) Determine the critical crack length (mm) for a...Ch. 7.10 - A fatigue test is made with a maximum stress of 25...Ch. 7.10 - A fatigue test is made with a mean stress of...Ch. 7.10 - A large, flat plate is subjected to...Ch. 7.10 - Prob. 32AAPCh. 7.10 - Refer to Problem 7.31: Compute the final critical...Ch. 7.10 - Prob. 34AAPCh. 7.10 - Prob. 35AAPCh. 7.10 - Equiaxed MAR-M 247 alloy (Fig. 7.31) is used to...Ch. 7.10 - Prob. 37AAPCh. 7.10 - If DS CM 247 LC alloy (middle graph of Fig. 7.31)...Ch. 7.10 - Prob. 39AAPCh. 7.10 - Prob. 40AAPCh. 7.10 - Prob. 41SEPCh. 7.10 - Prob. 42SEPCh. 7.10 - A Charpy V-notch specimen is tested by the...Ch. 7.10 - Prob. 44SEPCh. 7.10 - Prob. 45SEPCh. 7.10 - Prob. 46SEPCh. 7.10 - Prob. 47SEPCh. 7.10 - Prob. 48SEPCh. 7.10 - Prob. 49SEPCh. 7.10 - Prob. 50SEPCh. 7.10 - While driving your car, a small pebble hits your...Ch. 7.10 - Prob. 52SEPCh. 7.10 - Prob. 53SEPCh. 7.10 - Prob. 54SEPCh. 7.10 - Prob. 56SEPCh. 7.10 - Prob. 57SEPCh. 7.10 - Prob. 58SEPCh. 7.10 - Prob. 59SEPCh. 7.10 - The components in Figure P7.60 are high-strength...
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- Specify a copper alloy that requires at least 50% elongation and at least 300 MPa tensile strength.arrow_forward7- Calculate the tensile strength of steel: ou = 700 * c% + 340 N Ø mm ( for hypo eutectoid steel) %3Darrow_forward1. Determine working stresses for the two alloys that have the stress–strain behaviors shown in Figures 6.22.arrow_forward
- Question: (a) Make an S–N plot (stress amplitude versus logarithm cycles to failure) using these data. (b) What is the fatigue limit for this alloy? (c) Determine fatigue lifetimes at stress amplitudes of 415 MPa (60,000 psi) and 275 MPa (40,000 psi). (d) Estimate fatigue strengths at 2 × 104 and 6 × 105 cycles. The Figure to answer these questions is provided below.arrow_forwardUsing the Animated Figure: S-N Plot for Brass for a brass alloy determine the following: (a) the fatigue strength at 3x 10 cycles. MPa (b) the fatigue life for 165 MPa. cyclesarrow_forwardO The following engineering stress-strain data were obtained for a 0.2% C plain-carbon steel. (i) Plot the engineering stress-strain curve. (ii) Determine the ultimate tensile strength of the alloy. (iii) Determine the percent elongation at fracture. Engineering Engineering Engineering Engineering Stress Strain Stress Strain (ksi) (in./in.) (ksi) (in./in.) 76 0.08 30 0.001 75 0.10 55 0.002 73 0.12 60 0.005 69 0.14 68 0.010 65 0.16 72 0.020 56 0.18 74 0.040 51 0.19 75 0.060 (Fracture)arrow_forward
- A low-nickel steel in the heat-treated condition had an 'engineering' tensile strength of 708 N/mm2. The reduction in area of cross-section at the fracture was 44%. What was the true tensile strength of the steel?arrow_forwardLet's assume that the stress-strain elongation curve of a high-strength steel is given by this equation. o = 1.4*10º"ɛ 3 2.9*10*ɛ ² + 2.1*10°z Calculate the yield limit value of this steel. Oa (kgf/cm³) (For Yield Strength, use a straight line from the starting point and Calculate wwwwwww ww w m by moving the line parallel to the given curve)arrow_forwardCurrent Attempt in Progress (a) Estimate the activation energy for creep (i.e., Qc in Equation 8.22) for the S-590 alloy having the steady-state creep behavior shown in animated Figure 8.33. Use data taken at a stress level of 300 MPa (43,500 psi) and temperatures of 650°C and 730°C. Assume that the stress exponent n is independent of temperature. (b) Estimate ė, at 600°C (873 K) and 300 MPa. Part 1 Excellent! What is Qc in J/mol? Qc = 480000 J/molarrow_forward
- Question-7. Steady-state creep data taken for an alloy at a stress level of 160 MPa are given below. The stress exponent n for the alloy is 6.8. R is 8.3145 J/mol-K. Compute the steady-state creep rate at 1000 °C and a stress level of 68 MPa. Es (h-1) 6.8 × 10-5 T (°C) 800 8.6 x 10-3 900arrow_forward8.24 The fatigue data for a steel alloy are given as follows: Stress Amplitude [MPa (ksi)] 470 (68.0) Cycles to Failure 10 440 (63.4) 3 x 104 390 (56.2) 105 350 (51.0) 3 x 10 310 (45.3) 106 290 (42.2) 3 x 106 290 (42.2) 107 290 (42.2) 108 (a) Make an S-N plot (stress amplitude versus logarithm of cycles to failure) using these data.arrow_forwardPlease annotate the attached to highlight the different phases of the stress/strain graph for 0.15% carbon steel. From the attached graph, calculate the following: 1-modulus of elasticity 2-tensile strength 3-the ductility in % of elongation 4- yield strength at a strain offset of 0.002arrow_forward
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