Fatigue-crack growth in two aluminum alloys and crack-closure analyses under constant-amplitude and spectrum loading. (April 2019)

• Record Type: Journal Article
• Authors: Newman, J.C.; Walker, K.F.
• Is Part Of: Theoretical and applied fracture mechanics. Volume 100(2019)
• Page Start: 307
• Page End: 318
• Publication Date: 2019-04
• Subjects: Crack growth -- Aluminum alloy -- Crack closure -- Stress-intensity factor -- Spectrum loading; Fracture mechanics -- Periodicals; 620.1126
• DOI: 10.1016/j.tafmec.2019.01.029
• Languages: English
• ISSNs: 0167-8442

Abstract

Highlights: Constant-amplitude fatigue-crack-growth tests conducted on compact specimens made of 7075-T6 and 7249-T76511 alloy. Crack-closure concept correlated crack-growth-rate data over many orders-of-magnitude in rates. Simulated aircraft spectrum crack-growth tests conducted on middle-crack-tension specimens made of two alloys. Comparisons made between spectrum tests and crack-closure model calculations were very good. Abstract: Fatigue-crack-growth tests were conducted on compact, C(T), and middle-crack tension, M(T), specimens made of 7075-T6 and 7249-T76511 aluminum alloys. The 7075 tests were conducted on thin-sheet (2-mm thick) material; whereas, the 7249 tests were conducted on three thicknesses (2, 3.2 and 6.35-mm). The thin-sheet 7075 alloy did not have residual stresses, but the 7249 alloy (B = 2 mm) had low-level (<10 MPa) residual stresses from measurements. However, the other two 7249 alloy thicknesses were residual-stress free based on measurements. These tests were conducted to generate fatigue-crack-growth-rate data from threshold to near fracture at two load ratios (R = 0.1 and 0.7). Two methods were used to generate near threshold data on C(T) specimens: (1) compression pre-cracking constant-amplitude (CPCA) and (2) compression pre-cracking load-reduction (CPLR). Constant-amplitude tests were conducted on the M(T) specimens at the same two load ratios. Crack-closure measurements using a compliance method were made on some of the low R tests and a crack-closure model were used to develop an effective stress-intensity factor range against rate relation using a constant constraint factor (α = 1.85). The constraint factor accounts for three-dimensional stress-state effects on plastic yielding at crack tips and crack-closure behavior. Simulated aircraft wing spectrum tests were conducted on the M(T) specimens using two modified full-scale-fatigue-test (FSFT) spectra used on the P-3C aircraft. Tensile pre-cracking was used on all of the M(T) specimens, except one 3.2-mm thick 7249 specimen, before the spectra were applied. The same spectrum sequence was applied, but one had tension-compression loads, whereas, the other only tension-tension loads. The spectrum tests were used to calibrate the constraint-loss regime (plane-strain to plane-stress; α = 1.85–1.0) behavior for the FASTRAN strip-yield model. Comparisons were made between the spectrum tests and calculations made with the FASTRAN life-prediction code; and the calculated crack-growth lives were generally within ±20% of the test results.