Describe a metal fatigue failure.  (b) What two distinct types of surface areas are usually recognized on a fatigue failure surface? (c) Where do fatigue failures usually originate on a metal section

3. Linear elastic fracture mechanics (LEFM) predicts there will be an infinite stress at the tip of a crack. Why is this not the case? What happens microstructurally in metals, polymers and ceramics that prevents this?

Need answer correctly

6. In a plot of the variation of stress with time in a fatigue test, what does the double arrow line indicate? (a) Fatigue limit.. (b) Range of stress. (c) Mean stress. (d) Stress amplitude. Time I +

An aircraft component is fabricated from an aluminum alloy that has a plane strain fracture toughness of 37 MPa/m. It has been determined that fracture results at a stress of 249 MPa when the maximum (or critical) internal crack length is 2.16 mm. a) Determine the value of Yora for this same component and alloy at a stress level of 323 MPa when the maximum internal crack length is 1.08 mm. i MPa /m b) Under these circumstances will the component fail?

What is the cause of the fracture of a brittle material?

Under what circumstance could a fatigue crack become nonpropagating, even though the component experiences the same stress cyclic levels?

Research or journal about Failure of Materials Due to Creep and Fatigue. Please include the reference, Range of year from 2000 to 2022!

Estimate the theoretical fracture strength of a brittle material if it is known that fracture occurs by the propagation of an elliptically shaped surface cra of length 0.5 mm and having a tip radius of curvature of 0.005 mm, when a stress of 1040MPa is applied. Your answer must be in GPa. Write your answer to 1 decimal place. Answer: V 30 (0) 00 a W 4340 steel alloy. Determine the ductile to brittle transition

(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