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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 253 records · Page 14
All sourcesNASA NTRSDOE OSTI
DOE OSTI2022

Quasi-isentropic compression of an additively manufactured aluminum alloy to 14.8 GPa

We uniaxially and shocklessly compressed an additively manufactured aluminum alloy, laser powder bed fusion (LPBF) AlSi10Mg, to peak stresses ranging from 4.4 to 14.8 GPa at peak strain rates on the order of [Formula: see text] via a series of magnetic loading experiments to measure the principal isentrope, yield strength, and shear modulus as a function of material orientation and applied stress. We did not observe significant anisotropy in any of the measured quantities. We found that the principal isentrope, within the uncertainty and up to our peak stress, overlaps the material’s Hugoniot. We measured yield strengths and shear moduli ranging from 0.28 to 0.81 GPa and 36 to 52 GPa, respectively. Our results indicate that LPBF AlSi10Mg behaves similarly to wrought Al alloys under quasi-isentropic compression.

Brown, Nathan P.↗
NASA NTRS1966

Thermal stress-relief treatments for 2219 aluminum alloy are evaluated

Evaluation of three thermal stress relief treatments for 2219 aluminum alloy in terms of their effect on residual stress, mechanical properties, and stress corrosion resistance. The treatments are post aging and stress relieving fullscale and subscale parts formed in the aged T81 condition, and aging subscale parts formed in the unaged T31 condition.

Source record↗
NASA NTRS1973

Crack growth behavior of 2219-T87 aluminum alloy from 20 K (-423 F) to 422 K (300 F)

The aluminum alloy 2219-T87 has great potential for use as a cryogenic material for various manned and unmanned aerospace vehicles. Although its properties are generally known, toughness characteristics in various grain directions when the material is machined from thick plates and subjected to various environments have not been documented. This program, sponsored by the NASA Johnson Space Center, was designed to determine these properties between 20 K (-423 F) and 423 K (300 F).

Witzell, W. E.↗
NASA NTRS1974

Investigation of the plastic fracture of high-strength aluminum alloys

In a study of plastic fracture in five high-strength aluminum alloys (2014, 2024, 2124, 7075, and 7079), it has been shown that fracture toughness is affected primarily by the size and volume fraction of the larger (2 to 10 microms) second-phase particles. Certain of these particles crack at small plastic strains, nucleating voids which, with further plastic strain, coalesce to cause fracture. Not all second-phase particles crack at small plastic strains, and qualitative analysis of those which are primarily responsible for void nucleation shows that they contain iron or silicon or both. This result suggests that a reduction in the iron and silicon impurity content of the alloys should improve fracture toughness without loss of strength.

Van Stone, R. H.↗
NASA NTRS1990

Through-the-thickness fatigue crack closure behavior in an aluminum alloy

The variation in fatigue crack closure behavior across the thickness of aluminum alloy specimens was investigated. The specimen geometries examined were the middle crack tension M(T) and compact tension C(T). The fatigue crack closure behavior was determined using remote displacement and strain gages, near tip strain gages, and fatigue striations. A hybrid experimental/numerical method was also used to infer the crack opening loads. The results indicate a variation in crack opening load, of 0.2 in the specimen interior to 0.4 to 0.5 at the surface.

Dawicke, D. S.↗
NASA NTRS1991

Cleavage crystallography of liquid metal embrittled aluminum alloys

The crystallography of liquid metal-induced transgranular cleavage in six aluminum alloys having a variety of microstructures has been determined via Laue X-ray back reflection. The cleavage crystallography was independent of alloy microstructure, and the cleavage plane was 100-plane oriented in all cases. It was further determined that the cleavage crystallography was not influenced by alloy texture. Examination of the fracture surface indicated that there was not a unique direction of crack propagation. In addition, the existence of 100-plane cleavage on alloy 2024 fracture surfaces was inferred by comparison of secondary cleavage crack intersection geometry on the 2024 surfaces with the geometry of secondary cleavage crack intersections on the test alloys.

Reynolds, A. P.↗
NASA NTRS1990

Through-the-thickness fatigue crack closure behavior in an aluminum alloy

The variation in fatigue crack closure behavior across the thickness of aluminum alloy specimens was investigated. The specimen geometries examined were the middle crack tension M(T) and compact tension C(T). The fatigue crack closure behavior was determined using remote displacement and strain gages, near tip strain gages, and fatigue striations. A hybrid experimental/numerical method was also used to infer the crack opening loads. The results indicate a variation in crack opening load, of 0.2 in the specimen interior to 0.4 to 0.5 at the surface.

Dawicke, D. S.↗
NASA NTRS1928

Corrosion Embrittlement of Duralumin II Accelerated Corrosion Tests and the Behavior of High-Strength Aluminum Alloys of Different Compositions

The permanence, with respect to corrosion, of light aluminum alloy sheets of the duralumin type, that is, heat-treatable alloys containing Cu, Mg, Mn, and Si is discussed. Alloys of this type are subject to surface corrosion and corrosion of the interior by intercrystalline paths. Results are given of accelerated corrosion tests, tensile tests, the effect on corrosion of various alloying elements and heat treatments, electrical resistance measurements, and X-ray examinations.

Rawdon, Henry S↗
NASA NTRS1993

Measurement and analysis of critical CTOA for an aluminum alloy sheet

The stable tearing behavior of thin sheets of 2024-T3 aluminum alloy was investigated for middle crack tension, M(T), and compact tension, C(T), specimens. The surface crack-tip opening angle (CTOA), applied loads, crack extension, and local displacements were measured. A critical CTOA fracture criterion was incorporated into a two-dimensional, elastic plastic finite element code and used to simulate the experimental fracture behavior. The CTOA measurements and observations of the fracture surfaces have shown that large values for surface CTOA were observed for small crack extensions (less than the sheet thickness); substantial tunneling of the crack was associated with small crack extensions; crack tunneling in the M(T) specimen was less than that observed in the C(T) configuration; for larger crack extensions, the measured CTOA values were determined to be approximately 6 degrees for both the M(T) and C(T) configuration; and for larger crack extensions, crack tunneling remained constant. The two-dimensional finite element predictions of fracture behavior assumed a constant critical CTOA value of 6 degrees and accounted for local crack tip constraint with a plane strain core of elements ahead of the crack tip. The plane strain core extended 5 mm above the crack plane. The simulations were within +/- 4 percent of the maximum applied load for the C(T) tests within 2 percent for the M(T) tests.

Dawicke, D. S.↗
NASA NTRS1961

Experimental Investigation at Mach Number 3.0 of the Effects of Thermal Stress and Buckling on the Flutter of Four-Bay Aluminum Alloy Panels with Length-Width Ratios of 10

Skin-stiffener aluminum alloy panels consisting of four bays, each bay having a length-width ratio of 10, were tested at a Mach number of 3.0 at dynamic pressures ranging from 1,500 psf to 5,000 psf and at stagnation temperatures from 300 F to 655 F. The panels were restrained by the supporting structure in such a manner that partial thermal expansion of the skins could occur in both the longitudinal and lateral directions. A boundary faired through the experimental flutter points consisted of a flat-panel portion, a buckled-panel portion, and a transition point at the intersection of the two boundaries. In the region where a panel must be flat when flutter occurs, an increase in panel skin temperature (or midplane compressive stress) makes the panel more susceptible to flutter. In the region where a panel must be buckled when flutter occurs, the flutter trend is reversed. This reversal in trend is attributed to the panel postbuckling behavior.

Dixon, Sidney C.↗
NASA NTRS1974

The failure of notched specimens of boron-fiber reinforced 6061 aluminum alloy

The effect of notches on the strength of boron fiber reinforced 6061 aluminum alloy was determined at room temperature, 300 F, and 600 F. Both unidirectional and cross-plied specimens were tested. The strengths of individual fibers were measured, and upper and lower bounds of composite strength were calculated using bundle theory. Fracture tests were performed on specimens containing center slots of various lengths, and the values of the critical stress intensity factor for initial crack propagation or final failure were calculated. For unidirectional specimens, these parameters depended on thickness; for cross-plied specimens, fairly constant values were obtained at room temperature. The cross-plied material invariably failed at a lower stress as the environmental temperature was raised.

Wright, M. A.↗
NASA NTRS1981

Low strain creep and aging of aluminum alloy 2219-T87 sheet

The constant load creep and isothermal aging characteristics of aluminum alloy 2219-T87 sheet have been studied experimentally and analytically in the temperature range 250 to 650 F at stress levels between 2.9 and 4.0 ksi (20 to 283 MPa). Testing variables were closely and automatically monitored. The data generated agree somewhat with the literature data base at lower temperatures, but above 500 F, discrepancies of greater than an order of magnitude in the time to 1% creep strain occur. Good correlation was found with the Larson-Miller parameter as modeled by a second-order polynomial in stress. Constitutive equations for time to 0.1%, 0.2%, 0.5%, and 1.0% creep are given. Information on residual mechanical properties and electrical conductivity is also provided.

Navrotski, G.↗