2 edition of Application of light extinction measurements to the study of combustion in solid fuel ramjets found in the catalog.
Application of light extinction measurements to the study of combustion in solid fuel ramjets
Michael E. Hewett
An experimental investigation of the combustion behavior in solid fuel ramjets was conducted. Light extinction measurements were employed to determine the effects of fuel composition and bypass ratio on the combustion efficiency and the percent and size of unburned carbon. Utility and limitations of the optical method are presented.
|Statement||by M. E. Hewett and D. W. Netzer|
|Contributions||Netzer, David Willis, Naval Postgraduate School (U.S.)|
|The Physical Object|
|Pagination||vii, 33 p. :|
|Number of Pages||33|
The combustion process in the burner occurs at constant pressure from station 3 to station 5. The temperature increase depends on the type of fuel used and the fuel-air ratio. For scramjets, there may be additional entropy losses associated with the mixing of the fuel and the air. Following combustion, the hot exhaust is then passed through the. The results of mathematical modeling of the thermal state of combustion chambers with regenerative cooling for ramjet engines of promising flying vehicles are Cited by: 4.
A combustor is a component or area of a gas turbine, ramjet, or scramjet engine where combustion takes place. It is also known as a burner, combustion chamber or flame a gas turbine engine, the combustor or combustion chamber is fed high pressure air by the compression system. The combustor then heats this air at constant pressure. After heating, air passes from the combustor through. Hello everyone I am trying to design a ramjet engine. For that I need measurements of its parts. Does anyone know how to calculate them or have a link to a website where I .
the s, when gas turbine combustors, afterburners, and subsonic combustion ramjets were being intensively developed, considerable attention was directed to the study of heat addition to subsonic flows in constant-area combustion chambers. After some early confusion, an expository paper by Foa & Rudinger (a). Ramjet Combustion Chamber Paul Cameron Stone California Polytechnic State University, 1 Grand Avenue, San Luis Obispo, California, A ramjet combustion chamber is designed and some initial assembly fabrication and test completed as a component of a ramjet graduate project for California Polytechnic State.
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Ramjets can be classified according to the type of fuel, liquid or solid; and the booster.  In a liquid fuel ramjet (LFRJ), hydrocarbon fuel (typically) is injected into the combustor ahead of a flameholder which stabilises the flame resulting from the combustion of the fuel with the compressed air from the intake(s).
Solid fuel ramjets (SFRJ) are known for their operational simplicity and high specific impulse. The performance of the SFRJ propulsion system is directly tied to the energy density and combustion behavior of the fuel. A typical solid fuel used in a ramjet application is a collection of metal particles suspended in a polymeric by: The solid fuel ramjet (SFRJ) combustor design proposed in this paper employs a swirler at the entryway of the combustor tube to introduce a larger radial velocity component in the flow.
The swirler geometry at the inlet is comprised of a central hub with angled airfoil. Menter F R, Two equation eddy viscosity turbulence models for engineering application, AIAA Journal ; 8:  Schulte G, Pein R, and HÃ–gl A.
Temperature and concentration measurements in a solid fuel ramjet combustion chamber, Journal of Propulsion and Power ; 2:  Baurle R A, Mathur T, Gruber M R, Jackson K by: 2. Particle size measurements were obtained at the grain exit and nozzle entrance in a solid fuel ramjet combustor using a boron based fuel.
The particle size distributions at the aft end of the fuel. Combustion Characteristics of the Solid-Fuel Ramjet with Star Solid Fuel The three-dimensional code developed in the present study adopted third-order monotonic upwind scheme for conservation laws A sudden increase in pressure during the combustion of star solid fuel was observed experimentally, which requires further investigations.
Actually, fuel is stored within the combustion chamber allowing for more efficient packaging and higher mass fractions than liquid ramjets. No need for pumps, external tankage, injectors or plumbing for fuel delivery.
The concept has been around f. Projects on Solid Fuel Ramjets SFRJ has been a propulsion system of research-interest at least for the last thirty years.
Based on open literature, the countries which are taking interest in SFRJ application in missile system are China (Taiwan), Germany, Israel, Netherlands, Russia, Sweden, and USA, against maneuvering targets.
The solid fuel ramjet is especially attractive for the propulsion of projectiles, because it is simple, cheap and has a high fuel density. Figure 1 shows a sketch of a solid fuelramjet combustor.
It consists of an inlet, a solid fuel combustion chamber, and a nozzle. The incoming. An experimental investigation of combustion pressure oscillations in solid fuel ramjets. Item Preview An experimental investigation of combustion pressure oscillations in solid fuel ramjets.
by Parafiorito, Ted Michael. Publication date some content may be lost due to the binding of the book. Addeddate Call numberPages: The performance of the SFRJ propulsion system is directly tied to the energy density and combustion behavior of the fuel.
A typical solid fuel used in a ramjet application is a collection of metal. Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection An experimental investigation of combustion pressure oscillations in solid fuel ramjets.
Calhoun: The NPS Institutional Archive Theses and Dissertations Thesis Collection An experimental investigation of the combustion behavior of solid fuel ramjets.
Silicon Light Machines, Sunnyvale, California Randy J. Locke QSS Group, Inc., Cleveland, Ohio Robert C.
Anderson Glenn Research Center, Cleveland, Ohio Combustion Temperature Measurement by Spontaneous Raman Scattering in a Jet-A Fueled Gas Turbine Combustor Sector NASA/TM— May Cited by: 2.
ABSTRACT. The paper presents the combustion phenomena of boron-containing fuels in solid fuel ramjet (SFRJ) motors. It is shown that the peculiarities of boron ignition and combustion along with the SFRJ condensed phase processes and flowfield characteristics inherently lead to poor combustion efficiencies, preventing utilization of the remarkable theoretical energetic potential of the boron.
Supersonic Free-Jet Combustion in a Ramjet Burner Charles J. Trefny and Vance F. Dippold III National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio Abstract A new dual-mode ramjet combustor concept intended for operation File Size: 2MB. STEPHANIE BARONE: Supersonic Combustion Ramjet: Analysis on Fuel Options This report focuses on different fuel options available to use for scramjet engines.
The advantages and disadvantages of JP-7, JP-8, and hydrogen fuels are covered, also the effectiveness and requirements for File Size: KB. Methods for determining the combustion efficiency, thermodynamics parameters of propellants, and characteristics of ramjets are analyzed.
Energetic and multizone models taking into account various physical processes of incomplete combustion are considered. An approach based on comparison of the combustion efficiency evaluated by different models is developed, and Cited by: 3.
From Introduction: "The concept of supersonic combustion is by no means new, although little work appears to have been published on the subject. For example, an analysis of supersonic combustion to provide lift under a wing is given in reference 1.
Reference 2 discusses applications to hypersonic ramjets being studied at the University of Michigan."Cited by: The Bussard ramjet purported to address two issues that would seem to prevent Nearly As Fast As Light (NAFAL) travel from becoming a reality: fuel and protection from the.
Measurements have been made of the propulsive effect of supersonic combustion ramjets incorporated into a simple axisymmetric model in a free piston shock tunnel. The nominal Mach number was 6, and the stagnation enthalpy varied from to MJ kg − by: A Method for Performance Analysis of a Ramjet Engine in a Free-jet Test Facility and Analysis of Ramjet and scramjet engines are being developed to provide a more fuel efficient means of propulsion at high Mach numbers.
Part of the development of these engines It considered typical measurements for an engine test (pressures.Series: Fuel and energy science series Hardcover: pages Publisher: Applied Science Publishers Ltd () Language: English ISBN ISBN Package Dimensions: 9 x 6 x 1 inches Shipping Weight: pounds Customer Reviews: Be the first to write a review Amazon Best Sellers Rank: #9, in Books (See Top in Books)Author: J.