Luiz Gilberto Barreta

Instituto de Estudos Avançados da Universidade de São Paulo

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Dermeval Carinhana

Instituto de Estudos Avançados da Universidade de São Paulo

Pedro A. Matos

Instituto de Estudos Avançados da Universidade de São Paulo

Maria Esther Sbampato

Instituto Tecnológico de Aeronáutica

Alberto Monteiro dos Santos

Instituto de Estudos Avançados da Universidade de São Paulo

Leila Ribeiro dos Santos

Instituto Tecnológico de Aeronáutica

Cristiane Aparecida Martins

Instytut Lotnictwa

Renan G. Vilela

Technology Innovation Institute

Pedro Teixeira Lacava

Instituto Tecnológico de Aeronáutica

Tiago Leite Rolim

Instituto de Estudos Avançados da Universidade de São Paulo

Carla S. T. Marques

Universidade de São Paulo

Cooperative Institutions

Instituto de Estudos Avançados da Universidade de São Paulo

Instituto de Estudios Avanzados

Instituto Tecnológico de Aeronáutica

Instituto de Aeronáutica e Espaço

Departamento de Ciência e Tecnologia

Universidade de São Paulo

Universidade Federal do ABC

EarthTech International (United States)

Rensselaer Polytechnic Institute

Arizona State University

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Study of the Evolution of Soot Formation using Laser-induced Incandescence

Lincoln Tolomelli e Tolomelli Luiz Gilberto Barreta Pedro Teixeira Lacava Dermeval Carinhana

Incandescence

10.5220/0004714501020106

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Citations (0)

Single image molecular tagging velocimetry

Measurement Science and Technology (2020)

Pedro A. Matos Luiz Gilberto Barreta Cristiane Aparecida Martins Dermeval Carinhana

Abstract A single-image nitric-oxide molecular tagging velocimetry (NO-MTV) is reported and employed in a real air driven hypersonic shock tunnel and provided velocities of 3240 ± 170(5.2%) and 3030 ± 160(5.3%) m s − 1 , insignificantly different from previous results of 3037 ± 98(3.2%) obtained by an ordinary multi-image MTV technique. The proposed methodology relies on an one-dimensional analytical description of the spatial intensity profile registered by a single MTV image.

10.1088/1361-6501/abbba2

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Citations (12)

Methodology for the application of velocimetry by molecular tagging of hypersonic flows

Flow Measurement and Instrumentation (2022)

Leda Marise Vialta Pedro A. Matos Luiz Gilberto Barreta Dermeval Carinhana

Pitot tube

Expansion tunnel

SIGNAL (programming language)

Velocimetry

10.1016/j.flowmeasinst.2022.102265

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Citations (7)

Determination of liquefied petroleum flame temperatures using emission spectroscopy

Journal of the Brazilian Chemical Society (2008)

Dermeval Carinhana Luiz Gilberto Barreta Cláudio José da Rocha Alberto Monteiro dos Santos Celso A. Bertran

Emission spectroscopy was used in the temperature determination of LPG (liquefied petroleum gas) premixed flames. Natural emission of CH* radicals was investigated in flames under three different burning conditions: fuel/oxydizer stoichiometric ratio, fuel excess (rich flame), and oxidizer excess (lean flame). An average value of 2845 ± 70 K was obtained for CH* rotational temperature in the set up used in the experiments. This value did not show significant change with the type of flame analyzed and it is compatible with the calculated adiabatic flame temperatures of the investigated systems. This temperature value also agrees with that determined by an indirect measurement, using the sodium line reversal method, which is independent from the radical natural emission and well established in literature. Vibrational temperatures of ca. 4600 K were calculated, indicating that the CH* lifetime is insufficient for the establishment of an equilibrium state between the rotational and vibrational modes.

Adiabatic flame temperature

Liquefied petroleum gas

Stoichiometry

Propane

Liquefied natural gas

10.1590/s0103-50532008000700015

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Citations (14)

Experimental Investigation of the Shock Wave/Boundary Layer Interaction at a Compression Corner Model

15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference (2023)

Ana Maria Pereira Lara Tiago Leite Rolim Luiz Gilberto Barreta Pedro A. Matos Rafael d. Santos

The separation of the boundary layer is one of the main failures in scramjets due to its influence on the amount of oxygen used in combustion, reducing thrust and specific impulse. The main objective of this paper was to perform experimental investigations to study the shock wave/boundary layer interaction and boundary layer separation. The models were designed for the study of this interaction when there is a change in the surface of the body through a compression corner. The tests were carried out in a shock tunnel at a nominal Mach number of 6.5 and 8.5, using compression ramps of 20 deg. and 30 deg. Compression ramp models made of aluminum and 3D printed were designed and produced. The flow analysis was performed using pressure sensors and the schlieren image technique. As a result of these experiments, it was possible to visualize the leading edge shock, the normal shock wave, the boundary layer, the adverse pressure gradient, the flow separation structure, including the separation bubble and the reattachment of the boundary layer, the recompression shock and the shock-shock interaction. In addition, it was possible to evaluate the influence on the flow structure as the compression angle, Mach number, pressure and surface quality of the models are varied.

Expansion tunnel

10.2514/6.2023-3095

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Velocity and NO-Lifetime Measurements in an Unseeded Hypersonic Air Flow

Journal of Fluids Engineering (2018)

Pedro A. Matos Luiz Gilberto Barreta Cristiane Aparecida Martins

A laser-induced fluorescence (LIF)-based nitric-oxide flow-tagging technique was applied to measure both velocity and NO lifetime in a hypersonic shock tunnel from two experimental test runs. The results were supported by an analytical profile proposed in this paper that provides a way to correct velocity measurements under unknown systematic error sources. This procedure provided velocities with discrepancies lower than 3% for a total of five measurements, and lower than 2% when compared with that obtained from a linear fit. Additionally, the comparison between the proposed and experimental profiles allowed us to obtain the fluorescence NO lifetime from only one image.

Expansion tunnel

Systematic error

10.1115/1.4039863

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Citations (10)

The effect of lambda-doublet levels in ethanol flame temperature estimation

Journal of the Brazilian Chemical Society (2010)

Dermeval Carinhana Luiz Gilberto Barreta Celso A. Bertran Alberto Monteiro dos Santos

Rotational temperatures of CH* species present in ethanol flames with different diluent gas compositions were determined using natural emission spectroscopy. Spectrum fine-structures showed two different rotational temperatures. The results of A" symmetry levels were slightly higher than A' for all flames investigated. The temperature values also indicated a non-equilibrium distribution.

Diluent

Adiabatic flame temperature

10.1590/s0103-50532010000900026

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Citations (5)

Study of OH radicals distribution in atmospheric ethanol/O2 flames by laser-induced fluorescence (LIF)

Resumos (2005)

Maria Esther Sbampato Luiz Gilberto Barreta Alberto Monteiro dos Santos Leila Ribeiro dos Santos Harrald Victor Linnert

Source

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Temperature measurements by oh lif and chemiluminescence kinetic modeling for ethanol flames

Química Nova (2009)

Carla S. T. Marques Leila Ribeiro dos Santos Maria Esther Sbampato Luiz Gilberto Barreta Alberto Monteiro dos Santos

FOR ETHANOL FLAMES.OH LIF-thermometry was applied to premixed ethanol flames at atmospheric pressure in a burner for three flame conditions.Flame temperatures were simulated from energy equation with PREMIX code of CHEMKIN software package for comparison.A kinetic modeling based on a model validated through chemiluminescence measurements and on a set of reactions for nitrogen chemistry was evaluated.Marinov's mechanism was also tested.Sensitivity analysis was performed for fuel-rich flame condition with F = 1.34.Simulated temperatures from both reaction mechanisms evaluated were higher than experimental values.However, the proposed kinetic modeling resulted in temperature profiles qualitatively very close to the experimental.

CHEMKIN

Adiabatic flame temperature

10.1590/s0100-40422009000800017

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Citations (8)

Experimental laminar burning velocity of syngas from fixed-bed downdraft biomass gasifiers

Renewable Energy (2020)

Guthman Palandi Oliveira Maria Esther Sbampato Cristiane Aparecida Martins Leila Ribeiro dos Santos Luiz Gilberto Barreta

CHEMKIN

Wood gas generator

Laminar flame speed

10.1016/j.renene.2020.02.083

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Citations (15)