Searched for: author:"Wanhill, R.J.H."
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document
Wanhill, R.J.H. (author)
Archaeological silver may be embrittled by long-term corrosion and microstructural changes. The embrittlement increases with increasing grain size, and the combination of a large grain size with synergistic embrittlement (conjoint action of corrosion-induced and microstructurally-induced embrittlement) is particularly detrimental....
report 2001
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Wanhill, R.J.H. (author), Hattenberg, T. (author), van der Hoeven, W. (author), Koolloos, M.F.J. (author)
Longitudinal lap splices from several types of transport aircraft pressure cabins were investigated for Multiple Site Damage (MSD) fatigue and corrosion. The lap splices came from five service aircraft, three Fokker F28s, a British Aerospace BAC 1-11 and a Boeing B727-100; and a fullscale test on a Fokker F100. The results are compared with NASA...
report 2001
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Wanhill, R.J.H. (author)
Archaeological silver may be embrittled by long-term corrosion and microstructural changes. The embrittlement of artifacts increases with increasing grain size. This is explained by considering the grain boundary character and models describing the interactions between microcracks, lattice dislocations and grain boundaries. Severely embrittled...
report 2001
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Wanhill, R.J.H. (author), Koolloos, M.F.J. (author)
Aircraft structures are susceptible to fatigue and corrosion damage, notably at joints. There may be interactions between fatigue and corrosion, especially as aircraft age. Longitudinal lap splices from several types of transport aircraft pressure cabins were disassembled and investigated for Multiple Site Damage (MSD) fatigue cracking and...
report 2000
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Schra, L. (author), Wanhill, R.J.H. (author)
In 1991 a simple automated stress corrosion testing method called the ASCOR (Automated Stress corrosion Ring) test was developed to test aluminium alloys according to ASTM specification G49. The present investigation concentrated on evaluating two aspects of the test method: The SCC initiation criterion (2 % load decrease). The possibility of...
report 1997
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Wanhill, R.J.H. (author), Oldersma, A. (author)
Separation of an engine fi-om a 747-200 cargo aircraft resulted in a catastrophic aircraft accident near Amsterdam. The engine separated, together with its pylon, owing to fatigue and fracture of components connecting the pylon to the wing. These components were high strength steel lugs and two "fuse pins". One fuse pin was not recovered, but...
report 1996
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Wanhill, R.J.H. (author), Boogers, J.A.M. (author), Huisman, H.N. (author), Ottens, H.H. (author)
In 1995 an air supply manifold support rod from a high-performance turbofan engine failed by bending fatigue. The rod material was Inconel 718, operating at about 550° in an air environment. Diagnostic aspects of the failure (fatigue in bending, Stage I and Stage II fatigue fracture characteristics, and interference colours due to fracture...
report 1996
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Oldersma, A. (author), Wanhill, R.J.H. (author)
Discussions between D-BAA and the NLR have shown that significant variability in fatigue crack growth properties is possible for the industry standard damage tolerant aluminium alloy, 2024-T3 sheet. This is important for two reasons: (1) design assumptions and (2) comparisons of different candidate materials, such as 6013-T6, with 2024-T3....
report 1996
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Wanhill, R.J.H. (author), Leenheer, R. (author), Steijaert, J.P.H.M. (author), Koens, J.F.W. (author)
An Egyptian metal vase from the Ptolemaic period was investigated metallurgically and fractographically. The metal is nearly pure silver, and chemical analysis indicates it was obtained from the cupellation of lead. Despite its high purity (in archaeological terms) the metal is severely cracked and embrittled, with fractures mainly along grain...
report 1995
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Wanhill, R.J.H. (author)
This paper reviews currently available information on corrosion and fatigue in aircraft as a background to discussing the assessment of corrosion and fatigue damage. The main topics are: - aircraft operating environments and loads - corrosion - fatigue - corrosion and fatigue - corrosion and fatigue damage assessment. Aircraft structures are...
report 1995
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Wanhill, R.J.H. (author)
doctoral thesis 1995
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Wanhill, R.J.H. (author), Schra, L. (author)
An investigation was made of the effect of starter notch geometry on flight simulation fatigue crack growth in three damage tolerant aluminium sheet alloys, 2024-T3, 2091-T84 and 8090-T81. Changing the starter notch geometry resulted in significant differences in initial nonstabilized fatigue crack growth behaviour. However, there was only a...
report 1995
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Wanhill, R.J.H. (author), Schra, L. (author), 't Hart, W.G.J. (author)
This report compares the mechanical properties, fracture toughness and fatigue crack growth properties of the damage tolerant/medium strength aluminium plate alloys 2024-T351, 2324-T39, 8090-T651 and 8090-T8171. The main objective, in view of previous work, was to determine whether damage tolerant 8090-T8171 plate can advantageously replace the...
report 1995
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Wanhill, R.J.H. (author)
This report reviews currently available information on corrosion and fatigue in aircraft as a background to discussing the assessment of corrosion and fatigue damage. The main topics are: * aircraft operating environments and loads * corrosion * fatigue * corrosion and fatigue * corrosion and fatigue damage assessment. Aircraft structures are...
report 1994
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Wanhill, R.J.H. (author)
The NLR examined by fractography nine ruptured creep specimens supplied by EGT. Three specimens had been tested at 600° C and six specimens had been tested at 650° C. Internal (creep) cracking occured by transgranular microvoid coalescence, which is likely to be characteristic for standard heat treatment Inconel 718. One specimen tested at 600°...
report 1994
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Wanhill, R.J.H. (author)
This report contains the overhead sheets of a short course on fatigue and fracture of aerospace aluminium alloys, plus an annex in the form of a review paper.
report 1994
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Wanhill, R.J.H. (author)
report 1993
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Wanhill, R.J.H. (author), Boogers, J.A.M. (author)
An investigation was made of dwell crack growth, including the effects of peak loads and underloads, in Inconel 718 forged pancake material at 600ºC in an air environment. This investigation was done as part of the NLR's analytical workshare in the European collaborative programme lEPG TA31: Lifing Concepts for Military Aero-Engine Components,...
report 1993
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Wanhill, R.J.H. (author)
Flight simulation fatigue crack growth tests are necessary for verification of aircraft damage tolerance analyses and crack growth prediction methods, and also for comparing candidate materials for aircraft structural applications. However, such tests involve complicating issues that have emerged from many investigations on aluminium alloys...
report 1993
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Wanhill, R.J.H. (author)
This paper examines the status and prospects for widespread application of Al-Li alloys in aircraft structures. Particular attention is paid to the damage tolerance engineering properties of fatigue crack growth and fracture. At present the application of Al-Li alloys is very limited. This is because they are not direct replacements for...
report 1992
Searched for: author:"Wanhill, R.J.H."
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