The Experts below are selected from a list of 267 Experts worldwide ranked by ideXlab platform
A S Nejad - One of the best experts on this subject based on the ideXlab platform.
-
future direction of Supersonic Combustion research air force nasa workshop on Supersonic Combustion
35th Aerospace Sciences Meeting and Exhibit, 1997Co-Authors: Tishkoff M Julian, Drummond J Philip, T Edwards, A S NejadAbstract:The Air Force Office of Scientific Research, the Air Force Wright Laboratory Aero Propulsion and Power Directorate, and the NASA Langley Research Center held a joint Supersonic Combustion workshop on 14-16 May 1996. The intent of this meeting was to: (1) examine the current state-of-the-art in hydrocarbon and/or hydrogen fueled scramjet research; (2) define the future direction and needs of basic research in support of scramjet technology; and (3) when appropriate, help transition basic research findings to solve the needs of developmental engineering programs in the area of Supersonic Combustion and fuels. A series of topical sessions were planned. Opening presentations were designed to focus and encourage group discussion and scientific exchange. The last half-day of the workshop was set aside for group discussion of the issues that were raised during the meeting for defining future research opportunities and directions. This paper summarizes the discussions that took place at the workshop.
-
Future Direction of Supersonic Combustion Research: Air Force/NASA Workshop on Supersonic Combustion
35th Aerospace Sciences Meeting and Exhibit, 1997Co-Authors: M Tishkoff Julian, Drummond J Philip, T Edwards, A S NejadAbstract:The Air Force Office of Scientific Research, the Air Force Wright Laboratory Aero Propulsion and Power Directorate, and the NASA Langley Research Center held a joint Supersonic Combustion workshop on 14-16 May 1996. The intent of this meeting was to: (1) examine the current state-of-the-art in hydrocarbon and/or hydrogen fueled scramjet research; (2) define the future direction and needs of basic research in support of scramjet technology; and (3) when appropriate, help transition basic research findings to solve the needs of developmental engineering programs in the area of Supersonic Combustion and fuels. A series of topical sessions were planned. Opening presentations were designed to focus and encourage group discussion and scientific exchange. The last half-day of the workshop was set aside for group discussion of the issues that were raised during the meeting for defining future research opportunities and directions. This paper summarizes the discussions that took place at the workshop.
Johan Steelant - One of the best experts on this subject based on the ideXlab platform.
-
Methodology of a combined ground based testing and numerical modelling analysis of Supersonic Combustion flow paths
Shock Waves, 2010Co-Authors: Klaus Hannemann, Sebastian Karl, Jan Martinez Schramm, Johan SteelantAbstract:In the framework of the European Commission co-funded LAPCAT (Long-Term Advanced Propulsion Concepts and Technologies) project, the methodology of a combined ground-based testing and numerical modelling analysis of Supersonic Combustion flow paths was established. The approach is based on free jet testing of complete Supersonic Combustion ramjet (scramjet) configurations consisting of intake, combustor and nozzle in the High Enthalpy Shock Tunnel Göttingen (HEG) of the German Aerospace Center (DLR) and computational fluid dynamics studies utilising the DLR TAU code. The capability of the established methodology is demonstrated by applying it to the flow path of the generic HyShot II scramjet flight experiment configuration.
-
Advance in Supersonic Combustion Modeling and Simulations
45th AIAA Aerospace Sciences Meeting and Exhibit, 2007Co-Authors: Antonella Ingenito, Claudio Bruno, E. Giacomazzi, Johan SteelantAbstract:Mixing and Combustion of Supersonic reacting flows are currently under investigation for scramjet engines. Experimental results at NASA-Langley RC with single-jet hydrogen injection at Mach 2.5 in a Mach 2 airstreams showed Combustion taking place in a very short lenght: this indicates that Supersonic Combustion may indeed be very fast. Numerical simulations of the same test case have also done using LES and the subgrid scale model, ISCM, developed purposely for Supersonic Combustion. This model accounts for the effects of compressibility on reaction rate and on mixing. Numerical simulations indicate that the flame is unsteady: it anchors at about 15 cm from the injector, develops downstream and lifts off. Periodical ignition and quenching have been investigated by means of frequency analysis.
-
Ground testing of the HyShot Supersonic Combustion flight experiment in HEG
Shock Waves, 2005Co-Authors: Anthony Donald Gardner, Klaus Hannemann, A Paull, Johan SteelantAbstract:The first phase of the HyShot Supersonic Combustion ramjet (scramjet) flight exper- iment program of The University of Queensland in Australia was designed to provide benchmark data on Supersonic Combustion for a flight Mach number of approximately M=8. The second flight of the HyShot program, performed on July 30th 2002, was successful and Supersonic com- bustion was observed along the specified trajectory range. The operating range of the High Enthalpy Shock Tunnel Gottingen (HEG) of the German Aerospace Centre (DLR) was recently extended. The facility has now the capability of testing a complete scramjet engine with internal Combustion and external aerodynamics at M=7.8 flight conditions in altitudes of about 30 km. A post flight analysis of the HyShot flight experiment was performed using an operational scramjet wind tunnel model with a geometry which is identical to that of the flight configuration.
-
ground testing of the hyshot Supersonic Combustion flight experiment in heg and comparison with flight data
40th AIAA ASME SAE ASEE Joint Propulsion Conference and Exhibit, 2004Co-Authors: Anthony Donald Gardner, Johan Steelant, Klaus Hannemann, A PaullAbstract:The first phase of the HyShot Supersonic Combustion ramjet (scramjet) flight experiment program of The University of Queensland in Australia was designed to provide benchmark data on Supersonic Combustion for a flight Mach number of approximately M=8. The second flight of the HyShot program, performed on July 30th 2002, was successful and Supersonic Combustion was observed along the specified trajectory range. The operating range of the High Enthalpy Shock Tunnel Gottingen (HEG) of the German Aerospace Centre (DLR) was recently extended. The facility now has the capability of testing a complete scramjet engine with internal Combustion and external aerodynamics at M=7.8 flight con-ditions in altitudes of about 30 km. A post-flight analysis of the HyShot flight experiment was performed using an operational scramjet wind tunnel model with a geometry which is identical to that of the flight configuration.
Wang Zhen-guo - One of the best experts on this subject based on the ideXlab platform.
-
EVALUATION OF PARTIALLY PREMIXED FLAMELET APPROACH IN Supersonic Combustion
Advances in Mechanics, 2010Co-Authors: Wang Zhen-guoAbstract:Partially premixed flamelet approach is becoming one of the most promising formulations for mod-eling and simulating Supersonic Combustion.A systematic review is presented on the development history of flamelet approach for Supersonic Combustion.Two fundamental issues of this approach are summarized,i.e.the physical rationality of the flamelet approach for Supersonic Combustion and its modeling problem.The difficulties in applying flamelet approach to Supersonic Combustion are emphasized,and the overall considerations needed for modeling the suitable flamelet models for Supersonic Combustion are outlined.This paper suggests a reasonable direction for the development and application of partially premixed flamelet approach to Supersonic turbulent Combustion.
Sun Ying-ying - One of the best experts on this subject based on the ideXlab platform.
-
Numerical study on Supersonic Combustion of kerosene-air premixed flow
Journal of Propulsion Technology, 2004Co-Authors: Sun Ying-yingAbstract:A numerical study was conducted for the Supersonic Combustion of premixed kerosene-air flow ignited by a high-temperature hot gas as the pilot flame. Many factors, which have important influences on Supersonic Combustion, were systematically explored. These factors include the temperature, pressure, equivalence ratio of the Supersonic premixed flow, and the pressure matching relations between the premixed flow and the hot gas. The results show that with the rise of the static temperature or the static pressure of the premixed flow, the compression wave induced by ignition intensifies, resulting in an increased highest temperature and an expanded flame-spreading angle. When the equivalence ratio of the premixed flow is exactly stoichiometric, the Combustion temperature reaches the highest. When the static pressure of the premixed flow is higher than that of the hot gas, the ignition distance is shorten, compared with the static pressures matched cases. On the contrary, when the latter is higher than the former, the ignition distance is prolonged. Moreover, the flame-spreading angle is larger in the non-matched cases than that of the matched case. Besides, auto-ignition occurs in the boundary layer at the lower wall in many cases.
-
Investigation on Supersonic Combustion of kerosene using fuel-rich hot gas as pilot flame
Journal of Propulsion Technology, 2001Co-Authors: Sun Ying-yingAbstract:Experimental investigation on Supersonic Combustion of kerosene was conducted using fuel-rich hot gas as pilot flame on direct-connect Supersonic Combustion facility.Based on the measured wall static pressure,experimental data were interpreted using one-dimensional theoretical model Combustion efficiency and total pressure recovery coefficient were obtained.The characteristic of static pressure profiles in Supersonic combustor was analyzed.The effects of Supersonic flow temperature,fuel injection location,and global equivalence ratio on combustor performances were discussed.
Foluso Ladeinde - One of the best experts on this subject based on the ideXlab platform.
-
The effects of pressure treatment on the flamelet modeling of Supersonic Combustion
Combustion and Flame, 2019Co-Authors: Foluso Ladeinde, Zhipeng LouAbstract:Abstract The flamelet method has been used extensively as an affordable turbulence-Combustion interaction model that obviates the need to solve the evolution equations for the species mass fractions during a large-eddy or Reynolds-averaged Navier–Stokes calculation of a reactive flow field, leading to substantial savings in the simulation time and enabling modeling with relatively complex kinetic mechanisms. The canonical problem analyzed and stored in a look-up array in the flamelet procedure usually assumes some baseline fields; in particular, the pressure is often specified at a fixed value that is characteristic of the examined configuration. However, pressure in Supersonic Combustion has significant dynamical roles, unlike in low-Mach number or incompressible flows, and a constant pressure field will not be adequate for the former. To remedy this problem, reaction rate in the combustor is often assumed to scale squarely with pressure. This approach, which is probably acceptable for low-speed, high pressure combustors, is not suitable for dealing with the variable pressure conditions in Supersonic Combustion. This paper focuses on the assessment of the aforementioned scaling, in absolute sense, and also relative to an approach where pressure is added as a control parameter in the flamelet library. To achieve this, three classes of reactive systems with different levels of modeling complexities are investigated to show that representative chemical variables do not scale squarely with pressure. For the case of Supersonic Combustion, the scaling treatment in general leads to over-prediction of pressure and Combustion and also tends to stabilize the flame. To the knowledge of the authors, no previous studies have reported on the issues addressed in the present paper.
-
Improved Flamelet Modeling of Supersonic Combustion
Journal of Propulsion and Power, 2018Co-Authors: Foluso Ladeinde, Zhipeng LouAbstract:This paper has the objective of addressing a few basic issues pertaining to the use of the laminar flamelet method to model turbulence-Combustion interactions in Supersonic Combustion. Specifically...
-
Differential Turbulent Supersonic Combustion of Hydrogen, Methane, and Ethylene, Without Assisted Ignition
AIAA Journal, 2018Co-Authors: Foluso LadeindeAbstract:Although hydrogen has the desired ignition properties for Supersonic Combustion in a scramjet, it has the disadvantage of low energy density, thereby motivating the interest in alternate, mostly hy...
