| Discrete Film Cooling in a Rocket with Curved Walls |
Dec-2009 |
178 pages |
| Authors:
Jonathan F McCall; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
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 | This study quantified the effects of discrete wall-based film cooling in a rocket with curved walls. Simulations and experiments showed decreasing with wall radius of curvature, holding jet diameter constant, improves net heat flux reduction (NHFR) and adiabatic effectiveness (eta) for 90 compound injected cylindrical jets, though is reduced at the highest curvature. NHFR and eta improved further with a high favorable stream-wise pressure gradient (K=2.1x10-5) at all tested blowing ... |
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| Measurements of the Effectiveness of Concave Spherical Dimples for Enhancement of Hot-gas Side Heat Transfer (Preprint) |
04-Dec-2008 |
10 pages |
| Authors:
Stephen A Danczyk; Edward B Coy; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Measurements of the heat transfer enhancement effects of concave spherical dimples have been performed under hydrogenoxygen hot-fire conditions in a subscale combustion chamber. Seven configurations were tested with a range of area densities from 15-70% and depth to diameter ratios of 0.111 to 0.333. (Additional quantitiative results will included in the form of heat transfer coefficients and Stanton number.) Enhancements of 15-82% relative to a smooth surface were measured. Reynolds ... |
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| An Efficient Method for Calculating Surface Temperature and Heat Flux Based on Embedded Temperature Sensors (Preprint) |
09-May-2008 |
11 pages |
| Authors:
Edward B Coy; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
|
| Approximate analytical solutions have been obtained for surface temperature and heat flux for the case of two embedded temperature sensors. The solutions have been verified and the range of validity has been established using several methods including comparisons with an exact analytical solution for a linear problem and numerical calculations for a non-linear problem. The performance of the model is presented in both the frequency domain and the time domain. ... |
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| Ignition Characteristics for Transient Plasma Ignition of Ethylene/air and JP-10/Air Mixtures in a Pulse Detonation Engine |
DEC 2007 |
63 pages |
| Authors:
Jr Hackard Charles N.; NAVAL POSTGRADUATE SCHOOL MONTEREY CA DEPT OF MECHANICAL AND ASTRONAUTICAL ENGINEERING
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| The inlet mass flow, fuel injection profile, igniter characteristics, ignition delay, and operational frequency all dictate the success of a Pulse Detonation Engine (PDE). An optical sensor was developed and utilized for the observation of ignition zone characteristics over varying refresh conditions that showed decreasing ignition delay times when approaching marginally fuel-rich reactant mixtures. A wide range of equivalence ratios for ethylene/air mixtures were explored and a limited number of ... |
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| Investigation of Non-Conventional Bio-Derived Fuels for Hybrid Rocket Motors |
AUG 2007 |
144 pages |
| Authors:
Scott G. Putnam; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
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| Non-conventional bio-derived fuels have been evaluated for use in hybrid rocket motors. Tests were conducted at combustion pressures in the range of 100 - 220 psig and thrust levels of 40 - 170 newtons. Beeswax was tested with oxygen as the oxidizer and showed a regression rate at least three times as high as traditional hybrid propellant combinations such as hydroxyl-terminated polybutadiene (HTPB) and liquid oxygen (LOX). This provides the ... |
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| Design of a Premixed Gaseous Rocket Engine Injector for Ethylene and Oxygen |
DEC 2006 |
115 pages |
| Authors:
David F. Dausen; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
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| A premixed gaseous rocket injector was designed and successfully operated over a limited range of fuel-rich operating conditions for the purpose of soot modeling for ethylene and oxygen mixtures. The injector had the advantage of delivering a homogenous mixture to the combustion chamber, lower soot production, and higher performance potential by removing the fuel atomization process which affects the combustion process and is inherent for non-premixed injectors. The premixed injector ... |
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| Hydrogen Pressurization of LOX: High Risk/High Reward (Preprint) |
24 OCT 2006 |
5 pages |
| Authors:
Andrew E. Turner; Aaron Leichner; AEROJET SACRAMENTO CA
|
| Hydrogen safety has been an oxymoron in many circles since the catastrophic loss of the Hindenburg on May 6, 1937 due to a sudden fire consuming the huge 800 foot long, 100 foot diameter dirigible filled with hydrogen gas. Airship commercial service, enabled by relatively low-cost hydrogen, died along with the longest vehicle ever to fly, even though thousands of passengers had been transported without incident prior to that time. ... |
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| On the Behavior of a Shear-Coaxial Jet, Spanning Sub- to Supercritical Pressures, with and without an Externally Imposed Transverse Acoustic Field |
MAY 2006 |
262 pages |
| Authors:
Dustin W. Davis; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL AND NUCLEAR ENGINEERING
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| In the past, liquid rocket engines (LRE) have experienced high-frequency combustion instability, which impose an acoustic field in the combustion chamber. The acoustic field interacts with the fluid jets issuing from the injectors, thus altering the behavior of the jet compared to that of stable operation of the LRE. It is possible that this interaction could be a substantial feed back mechanism driving the combustion instability. In order to understand ... |
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| Shear-Coaxial Jets From a Rocket-Like Injector in a Transverse Acoustic Field at High Pressures (PREPRINT) |
JAN 2006 |
23 pages |
| Authors:
D. W. Davis; B. Chehroudi; ENGINEERING RESEARCH AND CONSULTING INC (ERC INC) EDWARDS AFB CA
|
| In order to gain a better understanding of some of the underlying physics associated with the interaction of high-amplitude acoustic waves and a coaxial-jet injector similar to those used in cryogenic liquid rockets, a non-reacting-flow experimental investigation was conducted under sub-, near-, and supercritical chamber pressures, with and without acoustical excitation. Past research works on this subject have shown both the relevance and importance of geometrical changes in an injector's ... |
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| Experimental and Numerical Analysis of Transpiration Cooling of a Rocket Engine Using Lamilloy (Trademark) Plates (POSTPRINT) |
DEC 2005 |
13 pages |
| Authors:
T. P. Auyeung; R. Cohn; E. Coy; S. A. Danczyk; C. Papesh; P. Sweeney; NORTHROP GRUMMAN SPACE AND MISSILE SYSTEMS CORP REDONDO BEACH CA SPACE TECHNOLOGY
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| Transpiration cooling of rocket engine thrust chamber walls has the potential for improving the performance of liquid rocket engines by reducing the required cooling flow. For the TR107 hydrocarbon booster engine, it is estimated that replacing the proposed chamber wall film cooling with transpiration cooling could result in an engine Isp increase of 2% to 3%, which provides the potential to increase the maximum booster delivery capability by 4000-5000 lbm. ... |
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| A Study of Projectile Response to Ballistics Environment |
NOV 2005 |
24 pages |
| Authors:
Stephen E. Ray; Michael J. Nusca; James F. Newill; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD WEAPONS TECHNOLOGY DIRECTORATE
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| The U.S. Army Research Laboratory s interior ballistics code, ARL-NGEN3, is a state-of-the-art modeling tool providing interior ballistics predictions and flowfield simulations of the ignition, flamespreading, and combustion of solid-propellant charges used to launch projectiles from guns. Modern solid mechanics codes such as DYNA3D and EPIC can complement the ARL-NGEN3 code by providing a capability to predict the mechanical response of the projectile to the unsteady, high-pressure environment within the ... |
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| Enhancement of Chamber Wall Heat Transfer by Surface Contouring |
18 OCT 2005 |
13 pages |
| Authors:
E. Coy; S. Danczyk; J. Watt; J. Poylio; NORTHROP GRUMMAN SPACE AND MISSILE SYSTEMS CORP REDONDO BEACH CA SPACE TECHNOLOGY
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| The effect of surface features on chamber wall heat transfer has been measured in a sub-scale combustion chamber. Results are reported for five different roughness patterns for conditions of hydrogen/oxygen combustion at mixture ratios of 2-6 and chamber pressures of 100-200 psig. The results include the measured levels of heat flux and Stanton number. The transverse ribs and grooves had the largest effect, resulting in approximately a doubling of the ... |
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| Supercavitating Projectile with Propulsion and Ventilation Jet |
14 SEP 2005 |
15 pages |
| Authors:
Thomas J. Gieseke; DEPARTMENT OF THE NAVY WASHINGTON DC
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| A supercavitating projectile is disclosed and includes a combustion chamber, a forward-directed jet nozzle and a comparatively larger gas duct/rear-directed jet nozzle. The combustion chamber is filled with a propellant having a hollowed core. The core serves as a pathway to fluidly allow combustion gases to the jet nozzles. In operation, the propellant combusts to form gasses forced forward through the forward-directed nozzle to generate a virtual cavitator in the ... |
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| Experiments on a Coaxial Injector Under an Externally-Forced Transverse Acoustic Field |
20 JUN 2005 |
22 pages |
| Authors:
D. W. Davis; B. Chehroudi; D. G. Talley; ENGINEERING RESEARCH AND CONSULTING INC (ERC INC) EDWARDS AFB CA
|
| In order to gain a better understanding of some of the underlying physics associated with the interaction of high-amplitude acoustic waves and a coaxial-jet type injector similar to those used in cryogenic liquid rockets, a non-reacting-flow experimental investigation was conducted under sub-, near-, and supercritical chamber pressures, with and without acoustical excitation. Past research works on this subject have shown both the relevance and importance of geometrical changes in an ... |
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| Meso and Micro Scale Propulsion Concepts for Small Spacecraft |
14 JUN 2005 |
26 pages |
| Authors:
R. A. Yetter; V. Yang; I. A. Aksay; F. L. Dryer; PENNSYLVANIA STATE UNIV UNIVERSITY PARK DEPT OF MECHANICAL AND NUCLEAR ENGINEERING
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| A meso/micro scale liquid propellant thruster is being developed for small spacecraft. In this thruster, the liquid propellant was injected directly into the chamber tangentially along the combustor wall. Heat feedback from the flame, once ignited, decomposed and gasified the liquid propellant. The gasification process of the propellant produced a voflex flow in the combustor, which stabilized the gas- phase flame. Modeling studies with gas-phase injection of reactants have shown ... |
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| Projectile With Tail-Mounted Gas Generator Assembly |
30 MAR 2005 |
16 pages |
| Authors:
Thomas J. Gieseke; NAVAL UNDERSEA WARFARE CENTER DIV NEWPORT RI
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| A projectile is provided that includes a body having a front tip portion and a rear end portion. A combustion chamber base plate is operatively arranged with the rear end portion of the body and defines a combustion chamber. At least one radial discharge aperture is partially defined by the combustion chamber base plate and is arranged in fluid communication with the combustion chamber. A gas generated by igniting a ... |
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| Mixing Effects of Pylon-Aided Fuel Injection Located Upstream of a Flameholding Cavity in Supersonic Flow |
MAR 2005 |
233 pages |
| Authors:
Daniel R. Montes; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| The Air Force Research Lab (AFRL), Propulsion Directorate, Wright- Patterson Air Force Base, Ohio is conducting ongoing research into propulsive efficiency in supersonic ramjet (scramjet) technology. One current focus of this research is the usefulness of flameholding cavities implemented in the supersonic hydrocarbon-fueled combustion chamber. Because good mixing and proper cavity-core interaction lead to more efficient combustion, methods of optimizing fuel/air mixing both within and upstream the cavity are investigated. ... |
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| Monte Carlo Simulation of a Rarefied Multiphase Plume Flow |
20 DEC 2004 |
5 pages |
| Authors:
Jonathan Burt; Iain D. Boyd; MICHIGAN UNIV ANN ARBOR DEPT OF AEROSPACE ENGINEERING
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| Exhaust flows from solid propellant rockets are characterized by a number of complex and often overlooked phenomena which should be considered for accurate numerical modeling. In a typical solid rocket motor (SRM), a 10 to 20% mass fraction of aluminum powder is used to reduce combustion instabilities and increase specific impulse. Within the combustion chamber, this aluminum content undergoes a complicated process of melting, heretogenous combustion, evaporation, agglomeration, and breakup. ... |
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| Coupling of CFD and CSM Codes for the Study of Projectile Response to Ballistics Environment |
DEC 2004 |
3 pages |
| Authors:
Stephen E. Ray; James F. Newill; Michael J. Nusca; Albert W. Horst; ARMY RESEARCH LAB ABERDEEN PROVING GROUND MD
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| The state-of-the-art interior ballistics (IB) code for the Army, ARL- NGEN3, is being used to predict the interior ballistics behavior of next- generation gun charges, which include densely-packed solid propellants. Recently, the results from ARL-NGEN3 code simulations were linked to structural dynamics codes in order to predict the in-bore behavior of the projectile afterbody. In the current paper results are presented from recent efforts to bring together the capabilities of ... |
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| Chemical Equilibrium Mixture Computations for Energetic Material Combustion in Closed Vessels |
DEC 2004 |
9 pages |
| Authors:
F. C. Wong; J. J. Gottlieb; L.-s. Lussier; TORONTO UNIV DOWNSVIEW (ONTARIO) INST FOR AEROSPACE STUDIES
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| A major computational code called CERV was developed to determine complex equilibrium compositions of a non-ideal mixture of numerous imperfect gases and compressible liquid and solid species with phase transitions for closed-vessel applications. This code minimizes Gibbs energy using reaction variables, in contrast to other major codes like BRL-Blake, BRCBagheera and NASA-CEA that use composition variables such as mole numbers. The CERV code has significant advantages in handling compressible condensed ... |
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| Determination of Laminar Flame Speed of Diesel Fuel for Use in a Turbulent Flame Spread Premixed Combustion Model |
DEC 2004 |
9 pages |
| Authors:
Peter Schihl; John Tasdemir; Walter Bryzik; TACOM RESEARCH DEVELOPMENT AND ENGINEERING CENTER WARREN MI
|
| One of the key challenges facing diesel engine system modelers lies in adequately predicting the fuel burning rate profile given the direct relationship between energy release and key performance parameters such as fuel economy, torque, and exhaust emissions. Current state-of-the-art combustion sub- models employed in such system simulation codes rely heavily on empiricism, and successful application of such sub-models for new engine designs is highly dependent on past experience with ... |
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| Comparison of Turbulence Models for an Internal Flow with Side Wall Mass Injection |
22 JUN 2004 |
31 pages |
| Authors:
B. A. Sen; U. G. Yuksel; K. Kirkkopru; ISTANBUL UNIV (TURKEY) DEPT OF MECHANICAL ENGINEERING
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| Solid propellant rocket boosters (SPRB) are used extensively in aerospace activities when a strong thrust is needed as in the case of lifting off the satellites for space activities. Flow structures occurring within the SPRB's have drawn the attention of the researchers either experimentally, or as it happens increasingly today, computationally. The flow field inside the combustion chamber experiences different processes since the characteristic velocity throughout the chamber is on ... |
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| The Effects of Pressure and an Acoustic Field on a Cryogenic Coaxial Jet |
22 JUN 2004 |
23 pages |
| Authors:
Dustin Davis; Bruce Chehroudi; Doug Talley; ENGINEERING RESEARCH AND CONSULTING INC (ERC INC) EDWARDS AFB CA
|
| OBJECTIVES: Document the nature of the acoustic wave/coaxial-jet injector interaction * Map a range of input variables * Explore application of the data and the findings for rocket combustion instability. MOTIVATION: Combustion instability has always been one of the most complex phenomena in liquid rocket engines * High amplitude and high frequency acoustic instabilities (screaming), can lead to local burnout of the combustion chamber walls and injector plates * APPROACH: ... |
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| Advanced Signal Processing for Integrated LES-RANS Simulations: Anti-Aliasing Filters |
24 MAR 2004 |
14 pages |
| Authors:
J. U. Schluter; DEPARTMENT OF ENERGY WASHINGTON DC
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| Currently, a wide variety of flow phenomena are addressed with numerical simulations. Many flow solvers are optimized to simulate a limited spectrum of flow effects effectively, such as single parts of a flow system, but are either inadequate or too expensive to be applied to a very complex problem. As an example, the flow through a gas turbine can be considered. In the compressor and the turbine section, the flow ... |
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| Determination of Laminar Flame Speed of Diesel Fuel for Use in a Turbulent Flame Spread Premixed Combustion Model |
2004 |
10 pages |
| Authors:
Peter Schihl; John Tasdemir; Walter Bryzik; TACOM RESEARCH DEVELOPMENT AND ENGINEERING CENTER WARREN MI
|
| One of the key challenges facing diesel engine system modelers lies in adequately predicting the fuel burning rate profile given the direct relationship between energy release and key performance parameters such as fuel economy, torque, and exhaust emissions. Current state-of-the-art combustion sub- models employed in such system simulation codes rely heavily on empiricism and successful application of such sub-models for new engine designs is highly dependent on past experience with ... |
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| Integrated RANS-LES Computations of Turbomachinery Components: Generic Compressor/Diffuser |
DEC 2003 |
12 pages |
| Authors:
J. U. Schluter; X. Wu; S. Kim; J. J. Alonso; H. Pitsch; DEPARTMENT OF ENERGY WASHINGTON DC
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| The goal of the ASCI project at Stanford is the computation of the entire aero-thermal flow in an aircraft gas turbine engine. As part of the project, high performance flow solvers are developed to address the prediction of the flow in components of the turbine. For the turbomachinery parts, a flow solver based on Reynolds-Averaged Navier-Stokes (RANS) approach is used. This flow solver is validated on a variety of turbomachinery ... |
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| Usage of supersonic Cold Gas-Dynamic Spraying (CGDS) for Obtaining a Catalytic Coatings for Systems of Steam Reforming of Fuel and Chemical Heat Recovery |
20 OCT 2003 |
8 pages |
| Authors:
D. V. Dzhurinskiy; T. S. Vinogradova; B. V. Farmakovskiy; I. C. Mashek; A. L. Kuranov; A. V. Korabelnikov; LENINETZ HOLDING CO NIPGS SAINT PETERSBURG (RUSSIA) HYPERSONIC SYSTEM RESEARCH INST
|
| The problem of development of new technologies dedicated for creation of materials which are capable to ensure implementation of active thermal protection of a HFV unique propulsion system, systems of directional power transmission and protection against radiation is one of the major ones among the problems of HFV creation. The complex of problems related to materials for creation of hypersonic flight vehicles includes development of catalytic materials for the power ... |
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| Numerical Research of Capabilities of Flat Thermochemical Reactor as Element of a Hypersonic Flight Vehicle Heat Protection |
20 OCT 2003 |
12 pages |
| Authors:
V. K. Vasilyev; A. V. Korabelnikov; A. V. Fedotov; AKADEMIYA NAUK SSSR MOSCOW
|
| Thermal protection of heat-stressed surfaces of a hypersonic flight vehicle (HFV) flying in dense layers of atmosphere with hypersonic velocities (M greater than or equal 7) is now one of the most actual problems 1,2. In HFV developed under the "Ajax" concept it is supposed that in the most heat- stressed parts of a skin and engine the chemical catalytic reactors will be placed in which the high endothermic processes ... |
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| Analysis of Scramjet with MHD Bypass |
OCT 2003 |
6 pages |
| Authors:
E. G. Sheikin; A. L. Kuranov; HYPERSONIC SYSTEMS RESEARCH INST SAINT PETERSBURG (RUSSIA)
|
| The propositions to use the MHD systems to control flow in a scramjet channel were put forward in development of the "M AJAX" concept. The paper 1, in which the basic principles for the MHD control in a scramjet were described for the first time in detail, was published in 1998. The main emphasis in the paper was put on analyzing the scramjet scheme with the control system composed of ... |
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| Upper Stage Engine Technology (USET) Effort |
17 JUL 2003 |
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| Authors:
Daniel Wright; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
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| Development of GOX/Kerosene Swirl-Coaxial Injector Technology |
30 JUN 2003 |
11 pages |
| Authors:
Gary C. Cheng; Rory R. Davis; Curtis W. Johnson; Jeffrey A. Muss; Daniel A. Griesen; SIERRA ENGINEERING INC CARSON CITY NV
|
| In developing an advanced liquid rocket engine, injector design is critical to obtaining the dual goals of long engine life and high-energy release efficiency in the main combustion chamber. A joint effort of Sierra Engineering (Sierra) and the Propulsion Directorate of the Air Force Research Lab (AFRL) was conducted to develop a design methodology, utilizing both high- pressure cold- flow testing and uni-element hot fire testing, to create a high ... |
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| High Thrust to Weight Bipropellant Reentry Vehicle Thrust Vector Control Thru Micro-Miniaturization |
08 MAY 2003 |
15 pages |
| Authors:
William Figueiredo; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE
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| With the advent of nanosat and picosat-size satellites, the design of miniature, efficient, high thrust-to-weight (T/W) ratio thrust vector control (TVC) thrusters with liquid bipropellants has been evolving. The extremely high T/W ratios achievable with micro miniaturization of liquid bipropellant engines are a result of the "cube-square-law". As the engine is scaled down linearly, the propellant flow, and thus the power, decreases with chamber cross-sectional area or the square of ... |
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| Development and Modeling of Angled Effusion Cooling for the BR715 Low Emission Staged Combustor Core Demonstrator |
MAR 2003 |
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| Authors:
M. Gerendas; K. Hoeschler; Th. Schilling; BMW ROLLS-ROYCE GMBH DAHLEWITZ (GERMANY)
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 | A technology program was started in 1994 within the framework of the German Aeronautics Research Program to develop axial-staged combustor technology up to a core engine demonstrator. The objective was to demonstrate a 50% NOx reduction against the ICAO CAEP II limit without any compromise on the CO, UHC, and smoke emission level compared to the latest single annular combustor technology. All other requirements, like ignition and relight capability, stability, ... |
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| Experimental Study of Geometric Effect for Design of Multihole Cooling for Combustion Chamber Walls |
MAR 2003 |
11 pages |
| Authors:
B. Leger; G. Schott; G. Grienche; TURBOMECA CEDEX (FRANCE)
|
| The increase of temperature and pressure in the gas turbines is a general trend that allows the engine performances to be increased. These higher thermodynamic cycles impose cooling systems of increasingly high performance. As a matter of fact, lean combustion, that is necessary to reduce the amount of nitrogen oxides (Nox) produced, consumes more and more air, and this air is taken mainly from the air usually reserved for cooling. ... |
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| High Bandwidth Heat Transfer Measurements in an Internal Combustion Engine Under Low Load and Motored Conditions |
MAR 2003 |
9 pages |
| Authors:
K. S. Chana; T. S. Wilson; P. Bryanston-Cross; M. Burnett; T. V. Jones; QINETIQ LTD FARNBOROUGH (UNITED KINGDOM)
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| Heat transfer between the working fluid and the combustion chamber in an internal combustion engine is one of the most important parameters for cycle simulation and analysis. The heat transfer influences the in-cylinder pressure and temperature levels, engine efficiency, and exhaust emissions. Most of the current research carried out on combustion chambers focuses on gas temperature measurement by Coherent Anti-Stokes Raman Scattering (CARS) and heat transfer measurement by thermocouples. Heat ... |
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| Numerical Investigation on Flow Field and Heat Transfer Phenomena in Multi-Hole Cooling Configurations |
MAR 2003 |
11 pages |
| Authors:
Dieter E. Bohn; Norbert Moritz; AACHEN UNIV OF TECHNOLOGY (GERMANY) INST OF STEAM AND GAS TURBINES
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| A transpiration cooled flat plate configuration is investigated numerically by application of a 3-D conjugate fluid flow and heat transfer solver, CHT-Flow. The geometrical setup and the fluid flow conditions are derived from modern gas turbine combustion chambers. The plate is composed of three layers, a substrate layer (CMSX-4) with a thickness of 2 mm, a bondcoat (MCrAIY) with a thickness 0.15 mm, and a thermal barrier coating (EB-PVD, Yttrium ... |
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| Influence of Combustion Condition and Air-Fuel Charge Rotation on Intensity of Heat Transfer in an IC Engine Operating on Gas Fuel |
MAR 2003 |
7 pages |
| Authors:
Janusz Rabiega; Leon Boguslawski; POZNAN UNIV OF TECHNOLOGY (POLAND)
|
| In the Heat Engineering Department of Poznan University of Technology, Poland, investigations of heat transfer processes on the wall of a single action internal combustion engine have been carried out for the last 10 years. Investigations of local heat transfer coefficients were carried out in different combustion conditions and the engine was propelled with a methane- carbon dioxide mixture (65% CH4 and 35% CO2). There were changes in timing, excess ... |
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| Military Vortices |
MAR 2003 |
13 pages |
| Authors:
D. A. Lovell; QINETIQ LTD FARNBOROUGH (UNITED KINGDOM)
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| The flow control methods being exploited by Micro-electro-mechanical systems (MEMS) devices rely in many cases on the manipulation of small-scale vortices to provide favorable mixing effects. By appropriate design and siting of MEMS very local effects on the flow can be made to provoke large-scale changes in the flow structure and, for example, control the conditions at which the flow separates. This topic area will not be considered further in ... |
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| Crack Growth-Based Predictive Methodologies for the Maintenance of structural Integrity of Repaired and Nonrepaired Aging Engine Stationary Components |
JAN 2003 |
320 pages |
| Authors:
George S. Hirko; Robert W. Hatala; Robert A. Mattern; PRATT AND WHITNEY EAST HARTFORD CT
|
| This report contains the results of work conducted by Pratt & Whitney between October 1994 and January 2001 under the Federal Aviation Administration contract to study the effect of aging on stationary engine components. The goal was to determine if long-term operation and multiple repairs affect the crack growth in engine-critical static structures and to provide a generic case management methodology to ensure continued airworthiness of these cases. The contract ... |
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| Nonlinear Dynamics and Ergodic Theory Methods in Control |
2003 |
15 pages |
| Authors:
Igor Mezic; HARVARD UNIV CAMBRIDGE MA
|
| We have continued to work on control of complex nonlinear systems and pursued applications to control of mixing, control of nanoscale processes and control of microscale mixing. At the Pi's group, 1 graduate student (Umesh Vaidya) was working on the problem of control of discrete-time, conservative systems and quantum control. Another student (Zoran Levnajic%) worked on problems in visualization of dynamical systems. A postdoctoral student (Dmitri Vainchtein) continued working on ... |
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| Heat Transfer and Deposition Behavior of Hydrocarbon Rocket Fuels |
27 DEC 2002 |
14 pages |
| Authors:
Ron Bates; Tim Edwards; Michael L. Meyer; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
| As the desire to increase the performance of hydrocarbon/liquid oxygen rocket engines naturally leads to increased combustion chamber pressures and higher energy hydrocarbon fuels, the combustion chamber and nozzle heat fluxes also increase. For engines regeneratively cooled with hydrocarbon fuel, this additional thermal stress must be effectively carried by the fuel without degradation of the cooling channel surfaces. A methodology for evaluation of the thermal performance (thermal stability and heat ... |
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| Swirl Coaxial Injector Development |
27 DEC 2002 |
15 pages |
| Authors:
R. K. Cohn; P. A. Strakey; R. W. Bates; D. G. Talley; J. A. Muss; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST
|
| Sierra Engineering and the Air Force Research Laboratory Propulsion Directorate, have undertaken a program to develop gas-centered, swirl coaxial injectors. This injector design will be used in the multi-element Advanced Fuels Tester (AFT) engine to test a variety of hydrocarbon propellants. As part of this program, a design methodology is being developed which will be applicable to future injector design efforts. The methodology combines cold flow data, acquired in the ... |
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| Pulse Combustion Rockets for Space Propulsion Applications |
20 DEC 2002 |
13 pages |
| Authors:
Edward B. Coy; AIR FORCE RESEARCH LAB EDWARDS AFB CA SPACE AND MISSILE PROPULSION DIV
|
| Pulse combustion propulsion devices are currently being considered as alternatives to conventional constant-pressure engines. Potential advantages include reduction or elimination of pumps and/or compressors, and improved Isp for a given feed system supply pressure. In this paper a model is presented for a monopropellant-fueled, constant-volume, pulse combustor which includes finite- rate processes. A zero-dimensional model is used for the combustion chamber and a one-dimensional, quasi-steady approximation is used for the ... |
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| Development of GOX/Hydrocarbon Multi-Element Swirl Coaxial Injector Technology |
26 NOV 2002 |
3 pages |
| Authors:
C. W. Johnson; J. Muss; G. C. Cheng; R. Davis; R. K. Cohn; SIERRA ENGINEERING INC CARSON CITY NV
|
| In developing the advanced liquid rocket engine, injector design is critical to obtaining the dual goals of long engine life as well as providing high-energy release efficiency in the main combustion chamber. Introducing a swirl component in the injector flow can enhance the propellant mixing and thus improve engine performance. Therefore, swirl coaxial injectors, which swirl liquid fuel around a gaseous oxygen core, show promise for the next generation of ... |
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| The Performance of Hydrocarbon Fuels with H2O2 in a Uni-Element Combustor. An Abstract for the 2003 AIAA/JPC |
12 NOV 2002 |
3 pages |
| Authors:
Jeff Muss; Curtis Johnson; William Kruse; Richard Cohn; SIERRA ENGINEERING INC CARSON CITY NV
|
| A team including Sierra%a Engineering, AFRL, and TRW tested several different hydrocarbon fuels in a 1200 pound thrust hydrogen peroxide hydrocarbon rocket unielement combustor at the AFRL propulsion directorate Edwards AFB research site. Tests were conducted with a variety of hydrocarbon fuels, including JP-8, RP-1-, JP-10, toluene quadricyclane, and turpentine as well as a several mixtures of these listed fuels. The combustor used decomposed hydrogen peroxide at concentrations of 90% ... |
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| Development of Synthesis and Large Scale Technology for Ultrahigh Energy Density Fluoro-Organic Compounds |
15 OCT 2002 |
18 pages |
| Authors:
W. R. Dolbier Jr.; T. W. Knight; S. Anghaie; FLORIDA UNIV GAINESVILLE DEPT OF CHEMISTRY
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| The goals of this Phase I STTR project were to address the technical feasibility and commercial aspects of producing high-density fluorine-rich compounds that are significantly more reactive and energetic than conventional explosives to neutralize and destroy chemical and biological agents During the one-year, Phase I STTR grant to NeTech, Inc., with subcontract to the University of Florida Department of Chemistry, the broad goals of the incipient project have been accomplished. ... |
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| Evaluation of the Ramjet Propulsion at a Energy Pulse Supply |
23 AUG 2002 |
6 pages |
| Authors:
V. P. Zamuraev; A. P. Kalinina; A. F. Latypov; RUSSIAN ACADEMY OF SCIENCES NOVOSIBIRSK INST OF THEORETICAL AND APPLIED MECHANICS
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| An attempt to model a working process of ramjet was made. A radiant energy in a pulse periodical regime is supplied in contrast to the classical scheme where the energy in a combustion chamber is supplied continuously by fuel burning. To simulate this problem the Euler equations in the "channel" approximation for a plane case are solved numerically. |
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| Preliminary Visualizations of Acoustic Waves Interacting with Subcritical and Supercritical Cryogenic Jets |
MAY 2002 |
7 pages |
| Authors:
Bruce Chehroudi; Doug Talley; ENGINEERING RESEARCH AND CONSULTING INC(ERC INC) EDWARDS AFB CA
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| The effect of large amplitude acoustic waves on subcritical and supercritical cryogenic jets was studied. A general trend was observed that acoustic waves cause the time averaged cross section of the jet to flatten in a direction where the minor axis becomes aligned with the direction of propagation of the waves. It was also found that the presence of acoustic waves shortened the breakup length of the jets compared with ... |
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| Investigations of Novel Energetic Materials to Stabilize Rocket Motors |
30 APR 2002 |
276 pages |
| Authors:
Merrill W. Beckstead; Fred E. Culick; Thomas B. Brill; Thomas A. Litzinger; Vigor Yang; Gary A. Flandro; Robert A. Frederick; M. C. Lin; E. W. Price; CALIFORNIA INST OF TECHNOLOGY PASADENA CA JET PROPULSION LAB
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| This document is the final report of the Caltech Multidisciplinary University Research Initiative (MURI), "Investigations of Novel Energetic Materials to Stabilize Rocket Motors," ONR Contract No. N00014-95-1-1338. With a one-year no-cost extension, the program covered the period 1 October 1995 to 30 September 2001 and involved Principal Investigators at nine Universities. In addition, for three years, funds from another source supported research by seven Russian research groups. Participants in the ... |
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| 2ND International Workshop on Rocket Combustion Modeling: Atomization, Combustion and Heat Transfer held in Lampoldshausen, Germany on 25-27 Mar 2001 |
14 MAR 2002 |
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| Authors:
Oskar J. Haiden; GERMAN AEROSPACE CENTER LAMPOLDSHAUSEN (GERMANY)
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| The aim of the workshop is to present the state-of-the art in computational fluid dynamics (CFD) tools used for liquid rocket propulsion purposes. The tools should be affordable, fast and reliable for predictive design of cryogenic liquid rocket components. |
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