Barbara Betti

Barbara Betti
Sapienza University of Rome | la sapienza · Department of Mechanical and Aerospace Engineering

Ph.D.

About

24
Publications
6,468
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224
Citations

Publications

Publications (24)
Article
Cooling of liquid rocket thrust chamber walls to allowable solid material temperatures induces near-wall chemical reactions, which are knownto have an important role on the heat transfer from the hot gas to the wall. In this study, the contribution of near-wall chemical reactions to heat flux is investigated and quantified by suitable numerical ana...
Article
The paper is intended to evaluate the relative weight of convective and radiative wall heat transfer in LRE thrust chambers. In particular, an appropriate computational tool, based on the Discrete Transfer Method, is set up to evaluate the radiative heat flux at the wall. Numerical results are compared against experimental data from the literature,...
Conference Paper
Full-text available
In this paper we propose an analysis of the heat transfer problem between cooling channels and thrust chamber of a liquid rocket engine. The approach consists in coupling the system analysis tool EcosimPro with external software to enhance locally the modelling of a single component. The considered tests case is the Space Shuttle Main Engine (SSME)...
Article
Numerical simulations of the flowfield in a gaseous oxygen/hydroxyl-terminated polybutadiene hybrid rocket engine are carried out with a Reynolds-averaged Navier–Stokes solver including detailed gas/surface interaction modeling based on surface mass and energy balances. Fuel pyrolysis is modeled via finite-rate Arrhenius kinetics. A simplified two-...
Conference Paper
Full-text available
A computational procedure able to describe the coupled hot-gas/wall/coolant environ-ment that occurs in most liquid rocket engines is presented and demonstrated. The coupled analysis is performed by loose coupling of the two-dimensional axisymmetric Reynolds-Averaged Navier-Stokes equations for the hot-gas flow and the conjugate three-dimensional m...
Conference Paper
The dual bell nozzle belongs to the family of Altitude Compensating Nozzles (ACN), which constitutes an option of great interest to improve launcher first stage performance. The internal flow of this nozzle adapts to the external pressure by separating at the wall inflection at low altitude (first operating mode) and by full flowing at high altitude (se...
Conference Paper
Full-text available
In this paper a new thrust chamber component for the object oriented tool EcosimPro is presented. The numerical approach consists of a finite volume formulation of the unsteady quasi one-dimensional Euler equations for multispecies flow coupled with finite-rate chemistry. The inviscid convective fluxes are treated with two schemes, specifically for...
Conference Paper
Cooling of thrust chamber walls to allowable solid material temperature induces near wall recombination which may add a non-negligible contribution to the heat transfer from the hot gas to the wall. In this study, the role of near wall recombination is studied by suitable numerical analyses. Numerical results are compared to literature experimental...
Conference Paper
Numerical simulations of the flowfield in a GOX/HTPB hybrid rocket engine are carried out with a Reynolds averaged Navier-Stokes solver including detailed gas surface interaction modeling based on surface mass and energy balances. Fuel pyrolysis is modeled via finite- rate Arrhenius kinetics. A simplified two-step global reaction mechanism is consi...
Article
Heat transfer enhancement due to longitudinal wall ribs inserted in a rocket engine thrust chamber is analyzed by means of a Reynolds-Averaged Navier-Stokes equations solver. A ribbed wall experiment is numerically reproduced to assess the capability of the simplified approach to properly capture the heat transfer enhancement. Then, a parametric an...
Article
The coupled hot gas-wall-coolant environment that occurs in regeneratively cooled liquid rocket engines is studied by a computational procedure able to provide a quick and reliable prediction of thrust chamber wall temperature and heat flux as well as coolant flow characteristics, like pressure drop and temperature gain in the regenerative circuit....
Article
Numerical simulations of the flow in a GOX/HTPB hybrid rocket engine are carried out with a Reynolds averaged Navier-Stokes solver including detailed gas surface interaction modeling based on mass and energy balances. Fuel pyrolysis and heterogeneous reactions at the nozzle wall are modeled via finite-rate Arrhenius kinetics. Global mechanisms are...
Article
Full-text available
The Sapienza aerospace research center (CRAS) is involved in the design and manufacturing of a cold gas micropropulsion system for attitude control to be tested on board the Ursa Maior CubeSat in the frame of the QB50 project. The main goal is to design and test a new integrated MEMS (Micro Electro Mechanical System) valve-nozzle system. The whole...
Article
The increasing market request for mini and microsatellites has led in the recent years to the development of small propulsion devices referred to as microthrusters. In the realm of microthruster different classifications have been made which help understanding the possible solutions depending on the satellite mass class and on the required thrust l...
Conference Paper
Film cooling as a thermal protection for the walls of liquid rocket engines is studied numerically for hydrogen and methane thrust chamber tests. The aim is to verify the capability of the Reynolds Average Navier-Stokes model to capture the basic characteristics of film-cooled thrust chambers, considering a simplified approach, named pseudo-injecto...
Conference Paper
A computational procedure able to describe the coupled hot-gas/wall/coolant environment that occurs in most liquid rocket engines and to provide a quick and reliable prediction of thrust-chamber wall temperature and heat flux as well as coolant-flow characteristics, like pressure drop and temperature gain in the regenerative circuit is presented an...
Conference Paper
This paper describes the design and the manufacturing of the 3U Cubesat URSA MAIOR (University of Rome la SApienza Micropropulsion for Attitude and In Orbit debris Removal testing), designed in collaboration between the II Faculty of Engineering of Bologna University and the Centro Ricerca Aerospaziale Sapienza (CRAS). The Cubesat is developed in t...
Conference Paper
Full-text available
This paper presents the results of the experimental investigation as well as the numerical analysis of the film cooling performance in an O2/CH4 subscale combustion chamber. The presented investigation provides detailed information about the cooling film efficiency and thermal load distribution on the hot inner surfaces of the combustion chamber at...
Conference Paper
Full-text available
Oxygen/methane liquid rocket engines are valuable candidates for future launch systems and deep-space missions. In this frame, reliable cooling methods, depending on the engine application are necessary such as regenerative cooling, film cooling and ablative cooling to face typical thrust chamber environment characterized by high temperatures and h...
Conference Paper
High performance liquid rocket engines environment is characterized by high temperature and high heat fluxes. Heat transfer accurate prediction is one of the key features for the development of these engines, especially in the case of expander cycle feed system. In the present study, hot-gas side heat transfer enhancement due to ribbed walls in an...
Conference Paper
The demand of a more comprehensive engineering tool for parametric investigations of rocket thrust chambers thermal environment is pushing the improvement of hot-gas side heat transfer prediction tools. In this work, the capability of predicting the heat transfer characteristics of a literature test case for a liquid oxygen / gaseous methane single...
Conference Paper
The increasing market request for mini and microsatellites has led in the recent years to the development of small propulsion devices referred to as microthrusters. In the realm of microthruster dierent classifications have been made which help understanding the possible solutions depending on the satellite mass class and on the required thrust lev...

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