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At least 217 records · Page 12
All sourcesNASA NTRSDOE OSTI
NASA NTRSDate not supplied

Investigating the Numerical Stability of Using an Impedance Boundary Condition to Model Broadband Noise Scattering With Acoustic Liners

Reducing aircraft noise is a major objective in the field of computational aeroacoustics. When designing next generation quiet aircraft, it is important to be able to accurately and efficiently predict the acoustic scattering by an aircraft body from a given noise source. Acoustic liners are an effective tool for achieving aircraft noise reduction and are characterized by a frequency-dependent impedance value. Converted into the time-domain using Fourier transforms, an impedance boundary condition can be used to simulate the acoustic wave scattering by geometric bodies treated with acoustic liners. A Broadband Impedance Model will be discussed in which the liner impedance is specified along a wide range of frequencies. The liner impedance boundary condition will be derived and coupled with a time-domain boundary integral equation to model acoustic scattering by a flat plate consisting of both un-lined and lined surfaces. The scattering solution will be obtained iteratively using both spatial and temporal basis functions and the stability will be demonstrated through eigenvalue analysis. Stability will be assessed for its dependence on time step, spatial discretization, as well as temporal basis function order. Both second- and third-order Lagrange temporal basis functions are considered.

acoustics↗
NASA NTRS2020

NASA Engineering and Safety Center Technical Bulletin No. 20-07: Evaluating and Mitigating Liner Strain Spikes in COPV's

Unexpected cracking and leaking in bonded composite overwrapped pressure vessel (COPV) liners occurring in recent test programs have been attributed to liner strain spikes observed through measurement and predicted by analysis. Diminished load transfer between the liner and composite overwrap can lead to localized excessive liner yielding in the dome section. This diminished constraint can occur due to yielding of the adhesive or a manufacturing unbond defect. COPVs should be assessed for susceptibility to this new failure mode.

Evaluating↗
NASA NTRS2020

An Over-the-Rotor Liner Investigation with Configurations Enabled by Additive Manufacturing

This paper presents the results of an investigation of over-the-rotor acoustic liner configurations enabled by additive manufacturing. NASA Langley and Glenn Research Centers have collaborated on the usage of acoustic liners in the turbofan aircraft engine nacelle wall at or very near the tip of the rotor. These liners absorb rotor-alone and rotor-stator interaction noise and, due to their proximity to the rotor tips, serve as a pressure release to inhibit the amount of generated noise. Initial tests with a metallic foam liner demonstrated good acoustic results, but there was concern regarding the durability of the material. NASA then decided to explore configurations enabled by additive manufacturing via tests in the NASA Langley Normal Incidence Tube. Measured data for uniform-depth and variable-depth cores with narrow and wide chambers were compared with predictions via the NASA Langley impedance prediction model. As these configurations were intended for eventual use in an over-the-rotor application, it was necessary to add facesheets to the wide-chamber cores to avoid deleterious flow effects caused by open cavities. A number of facesheets were tested in combination with each wide-chamber core. Finally, it has been shown that grooves near the rotor tips cause an improvement in aerodynamic performance. A small set of grooves were fabricated such that they could be combined with the wide-chamber configurations. The results of these tests were subsequently used to guide designs for further testing in higher technology readiness level test rigs at NASA Glenn Research Center.

acoustic↗
NASA NTRSDate not supplied

NASA Investigation of Flow Direction Effects on Impedance Eduction for Acoustic Liners

In support of a collaboration with the International Forum for Aviation Research (IFAR), the NASA Langley Liner Physics Team has acquired a detailed dataset for use in the evaluation of flow direction effects on the acoustic liner impedance eduction process. Measurements are acquired with four acoustic liners designed to cover a range of sensitivities to source sound pressure level and tangential mean flow effects, specifically at source levels of 120 and 140 dB and centerline Mach numbers of 0.0, 0.1, 0.2, and 0.3. These measurements include detailed flow profile surveys upstream and downstream of the liner test window, as well as acoustic pressure data over the extent of the test window. The results clearly demonstrate the importance of the choice of Mach number used in the impedance eduction analysis. Average Mach number differences of less than 0.01 result in significant variation in the educed impedance spectra. These data will soon be supplied to the IFAR partners and will be made available for the general public within the next year.

acoustic↗
NASA NTRSDate not supplied

Extending Acoustic Liner Bandwidth with Simple Embedded Septa

An acoustic liner design incorporating single-hole perforate septa was evaluated by the NASA Langley Liner Physics Team. The design, termed the ‘Simplified Septa’ concept, incorporates embedded septa as found in traditional, multidegree-of-freedom liners. Generally, such septa are composed of multihole perforates or porous mesh, whereas this concept uses septa with one hole per cell. An optimization scheme was employed to determine septa placement and hole diameters based on a target impedance cost function. Versions of the concept are tested in the NASA Langley Normal Incidence Tube (NIT) to determine impedance and absorption spectra for swept tonal excitation at 120 and 140 dB. Experimental results are compared to predictions from a liner model based on the Zwikker-Kosten Transmission Line (ZKTL) code and show good agreement for no-flow conditions.

acoustics↗
NASA NTRSDate not supplied

NASA Investigation of Flow Direction Effects on Impedance Eduction for Acoustic Liners

In support of a collaboration with the International Forum for Aviation Research (IFAR), the NASA Langley Liner Physics Team has acquired a detailed dataset for use in the evaluation of flow direction effects on the acoustic liner impedance eduction process. Measurements are acquired with four acoustic liners designed to cover a range of sensitivities to source sound pressure level and tangential mean flow effects, specifically at source levels of 120 and 140 dB and centerline Mach numbers of 0.0, 0.1, 0.2, and 0.3. These measurements include detailed flow profile surveys upstream and downstream of the liner test window, as well as acoustic pressure data over the extent of the test window. The results clearly demonstrate the importance of the choice of Mach number used in the impedance eduction analysis. Average Mach number differences of less than 0.01 result in significant variation in the educed impedance spectra. These data will soon be supplied to the IFAR partners and will be made available for the general public within the next year.

acoustic↗
NASA NTRSDate not supplied

Extending Acoustic Liner Bandwidth with Simple Embedded Septa

An acoustic liner design incorporating single-hole perforate septa was evaluated by the NASA Langley Liner Physics Team. The design, termed the ‘Simplified Septa’ concept, incorporates embedded septa as found in traditional, multidegree-of-freedom liners. Generally, such septa are composed of multihole perforates or porous mesh, whereas this concept uses septa with one hole per cell. An optimization scheme was employed to determine septa placement and hole diameters based on a target impedance cost function. Versions of the concept are tested in the NASA Langley Normal Incidence Tube (NIT) to determine impedance and absorption spectra for swept tonal excitation at 120 and 140 dB. Experimental results are compared to predictions from a liner model based on the Zwikker-Kosten Transmission Line (ZKTL) code and show good agreement for no-flow conditions.

acoustics↗
DOE OSTI2019

Implementation of Research and Development (R and D) Results in the Design of Liner System for the Near Surface Disposal Facility (NSDF) - 19089

Canadian Nuclear Laboratories (CNL) proposes to develop a Near Surface Disposal Facility (NSDF) at the Chalk River Laboratories (CRL) site in Ontario, Canada for disposal of CNL's Low Level Radioactive Waste (LLW) and other suitable wastes meeting the Waste Acceptance Criteria (WAC). The NSDF's Engineered Containment Mound (ECM) includes base liner and final cover systems. These liner systems are designed to perform effectively for a total of 550 years. The specified geomembrane in the NSDF detailed design is 2 mm thick High Density Polyethylene Geomembrane (HDPE GMB) double sided textured and white surface. CNL's approach to collaborate with Subject Matter Expert (SME) consultants and contractors, a Canadian university, and industry has enabled the NSDF to incorporate current best design practices, particularly for the design of the ECM's liner systems. This paper describes the HDPE GMB testing program and how the results of the state-of-the-art research have been utilized in the design of the NSDF's liner system and in selection of the best candidate materials to strengthen the confidence that the required service-life will be met. The testing program includes index properties and long-term performance evaluation tests of the five candidate HDPE GMBs using leachate simulant comparable to expected NSDF leachate and an index simulant used for testing many GMBs. The results of the tests are used as the basis to assess expected HDPE GMBs long-term performance. The expected long-term performance is applied as the key consideration for the final selection of the HDPE GMB in the NSDF project. Preliminary results of the testing program indicate that an expected service-life of 550 years will likely be met by the candidate HDPE GMB. (authors)

12 MANAGEMENT OF RADIOACTIVE AND NON-RADIOACTIVE W↗
DOE OSTI2018

Improving the energy efficiency of a refrigerator-freezer through the use of a novel cabinet/door liner based on polylactide biopolymer

This paper presents the energy savings potential of a newly developed liner applied on the foam insulation used in refrigerator and freezer cabinets, compared with using a more commonly used liner made from high-impact polystyrene. The new polylactic acid polymer liner is made from renewable feedstock such as carbon found in plant sugars. The energy use over the life of refrigerator and freezer is calculated using the Energy-Efficient Refrigerator Analysis program developed by the United States Department of Energy to estimate the energy savings potential of various technology option upgrades (cabinet and refrigeration system) for rulemaking purposes. The simulation results show that energy savings from implementing the Ingeo liner range from 818 to 1395tkWh (7.3–12.5% of total energy use) over a 15-year period. In addition to the energy savings, the slower increase in the thermal conductivity of the insulation could allow the compressor to run fewer hours per year compared with a case in which the foam thermal conductivity increases rapidly. This change could increase the life of the compressor and the refrigerators and freezers. As a result, this study does not attempt to quantify the impact of slower foam aging on the compressor life.

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATI↗
DOE OSTI2020

Corrosion protection of steel pipelines with metal-polymer composite barrier liners

Pipelines are efficient in transporting natural gas over large distances. Wet carbon dioxide present in pipelines can create an environment that is corrosive to steel. Polymer liners made from either polyethylene or polyamide (nylon) are presently used to mitigate internal corrosion in natural gas pipelines. Gas diffuses through all polymers over time, and polymer-only liners lower the steel corrosion rate by reducing the reactive gas flux to the internal surface of a pipeline. Composite liners, which incorporate one or more metallic layers that are impermeable to corrosive gases, offer better protection than polymer-only liners. In this study, we measured the methane, water vapor, and carbon dioxide permeability of a multi-layer barrier film and found it to be more effective in resisting gas permeation than polyethylene and nylon-11 films.

03 NATURAL GAS↗
DOE OSTI2016

Helical plasma striations in liners in the presence of an external axial magnetic field

Awe et al. found on the 20 MA Z machine [Acta Phys. Pol. A 115, 956 (2009)] that applying an externally generated axial magnetic field to an imploding liner leads to a helical pattern in the liner when viewed with soft x-ray radiography ([Phys. Rev. Lett. 111, 235005 (2013)] and [Phys. Plasmas 21, 056303 (2014)]). We show that this phenomenon is also observed in extreme ultraviolet self-emission images of 10 mm long cylindrical metal liners having varying diameters and varying wall thicknesses on a 1 MA, 100–200 ns pulsed power generator. The magnetic field in these experiments is created using either twisted return current wires positioned close to the liner, generating a time-varying B z , or a Helmholtz coil, generating a steady-state B z .

70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
DOE OSTI2020

Experimental characterization of a section of a spherically imploding plasma liner formed by merging hypersonic plasma jets

In this work, we report experimental results on merging of hypersonic plasma jets, which is the fundamental building block for forming spherically imploding plasma liners as a potential standoff compression driver for magneto-inertial fusion. Jets are formed and launched by contoured-gap coaxial plasma guns mounted at the six vertices and the center of a hexagon covering approximately one-tenth of the surface area of a 9-ft-diameter spherical chamber. First, from experiments with two and three merging jets of four different species (N, Ar, Kr, and Xe), we show that (1) density spatial non-uniformities can be large (with electron-density jumps ranging from 2.9 for N to 6.6 for Xe) when shocks form upon jet merging, but smaller (density jumps <2) when shocks do not form; (2) jet impurities (20% Ti in these experiments) can increase the level of density spatial non-uniformity by increasing the collisionality of jet merging, leading to shock formation rather than potentially more desirable shockless jet merging; and (3) the liner Mach number can remain high (≳10), as required for plasma liners to be an effective compression driver. Secondly, from experiments with six and seven merging jets using Ar, we present results with improved jet-to-jet mass balance of <2% across jets, including (1) evidence of substantially increased balance in the jet merging and symmetry of the liner structure and (2) potentially favorable changes in the jet-merging morphology with the addition of the seventh jet. Ultimately, for both experiments, we present comparisons between experimental and synthetic data from three-dimensional hydrodynamic codes.

70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
DOE OSTI2020

Characterizing laser preheat for laser-driven magnetized liner inertial fusion using soft x-ray emission

Laser heating of a gas in a cylindrical liner held in by a thin foil window is a critical process in the MagLIF (magnetized liner inertial fusion) concept. Window burn-through and gas heating for OMEGA scale MagLIF cylinders as a function of time have been determined using spectrally integrated soft x-ray diagnostics. Window laser absorption is classified in terms of the emitted x-rays from the window plasma as a function of laser energy, and shows that laser energy absorbed is weakly dependent on incident intensity. Radiation-hydrodynamic simulations overestimate the amount of laser energy absorbed by the window as evidenced by the increase in x-ray radiation across several photon energy bands compared to experiments. Gas temperatures inferred from soft x-ray emission from the front 1 mm of the liner are shown to evolve in time in a similar manner to simulation predictions. In conclusion, soft x-ray emission from the gas within the region of the liner that is normally imploded is shown to meet the 100 eV requirements set by the initial point design for laser-driven MagLIF.

70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
DOE OSTI2016

Experimental demonstration of the stabilizing effect of dielectric coatings on magnetically accelerated imploding metallic liners

Enhanced implosion stability has been experimentally demonstrated for magnetically accelerated liners that are coated with 70 μm of dielectric. The dielectric tamps liner-mass redistribution from electrothermal instabilities and also buffers coupling of the drive magnetic field to the magneto-Rayleigh-Taylor instability. A dielectric-coated and axially premagnetized beryllium liner was radiographed at a convergence ratio [CR=R in,0 /R in (z,t)] of 20, which is the highest CR ever directly observed for a strengthless magnetically driven liner. Lastly, the inner-wall radius R in (z,t) displayed unprecedented uniformity, varying from 95 to 130 μm over the 4.0 mm axial height captured by the radiograph.

70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
DOE OSTI2017

Experiment to Form and Characterize a Section of a Spherically Imploding Plasma Liner

Here, we describe an experiment to form and characterize a section of a spherically imploding plasma liner by merging six supersonic plasma jets that are launched by newly designed contoured-gap coaxial plasma guns. This experiment is a prelude to forming a fully spherical imploding plasma liner using many dozens of plasma guns, as a standoff driver for plasma-jet-driven magneto-inertial fusion. The objectives of the six-jet experiments are to assess the evolution and scalings of liner Mach number and uniformity, which are important metrics for spherically imploding plasma liners to compress magnetized target plasmas to fusion conditions. Lastly, this article describes the design of the coaxial plasma guns, experimental characterization of the plasma jets, six-jet experimental setup and diagnostics, initial diagnostic data from three- and six-jet experiments, and the high-level objectives of associated numerical modeling.

70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
DOE OSTI2021

PHELIX Shallow Cassette Liner Performance Tests 1 and 2 Post-Shot Simulation Report

PHELIX shallow cassette liner performance Tests 1 (PHELIX No. 151) and 2 (PHELIX No. 156) were conducted on August 07, 2020, and September 16, 2020, respectively. The primary purpose for these tests was to assess liner performance within the new shallow cassette PHELIX design configuration. Specific goals included: (1) an assessment of liner performance in terms of velocity and symmetry (both axial and azimuthal), and (2) an assessment of our ability to accurately predict liner performance. Test 1 was conducted with a driving potential of 70 kV. Test 2 was conducted with a driving potential of 75 kV.

42 ENGINEERING↗
DOE OSTI2024

Fabrication of a Liner Assembly for the MARVEL Microreactor

A liner assembly for an intermediate heat exchanger within the MARVEL microreactor at Idaho National Laboratory has been fabricated using laser-based additive manufacturing. The liner design includes challenging features such as long thin walls, overhangs, and tight geometric tolerances. Two versions of the liner assembly, one full length and the other shortened, were printed from several materials (316L SS, Inconel 625, and Inconel 718) using four powder-based laser printers (AddUp BeAM Modulo 400 DED, EOS 290M LPBF, GE Concept M2, and GE Concept Xline 2000R LPBF) located at the Manufacturing Demonstration Facility of Oak Ridge National Laboratory. Dimensional accuracy, print time, and powder utilization have been evaluated to help assess the feasibility of these AM approaches to liner fabrication. Based on this assessment, a potentially cost-effective pathway for fabrication has been proposed.

36 MATERIALS SCIENCE↗
NASA NTRS1973

Comparison of primary zone combustor liner wall temperatures with calculated predictions

Calculated liner temperatures based on a steady-state radiative and convective heat balance at the liner wall were compared with experimental values. Calculated liner temperatures were approximately 8 percent higher than experimental values. A radiometer was used to experimentally determine values of flame temperature and flame emissivity. Film cooling effectiveness was calculated from an empirical turbulent mixing expression assuming a turbulent mixing level of 2 percent. Liner wall temperatures were measured in a rectangular combustor segment 6 by 12 in. and tested at pressures up to 26.7 atm and inlet temperatures up to 922 K.

Norgren, C. T.↗