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Heat Transfer And Deposition Behavior Of Hydrocarbon Rocket Fuels
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Book Synopsis Heat Transfer and Deposition Behavior of Hydrocarbon Rocket Fuels by :
Download or read book Heat Transfer and Deposition Behavior of Hydrocarbon Rocket Fuels written by and published by . This book was released on 2002 with total page 3 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 transfer characteristics) of hydrocarbon rocket fuels is suggested. As part of that methodology, an experimental research program to investigate the thermal performance of several new candidate hydrocarbon rocket fuels has been started. The experimental program uses a series of test rigs of increasing complexity and fidelity to successively screen identified fuels without the cost and complexity of a full engine system level test. Results of small-scale thermal decomposition experiments utilizing a System for Thermal Decomposition Studies (STDS) test rig provide an initial evaluation of the thermal stability performance of fuels from very small fuel samples. Measurements of heat transfer coefficient and the effect of wall temperature, flow velocity, and wetted-material on deposit formation in heated test channels are obtained from larger rigs, such as the NASA/GRC Heated Tube Facility and the AFRL/PRS High Heat Flux Facility. Representative results from early testing will be presented to illustrate the effectiveness of the overall approach.
Book Synopsis Deposit Formation and Heat Transfer in Hydrocarbon Rocket Fuels by :
Download or read book Deposit Formation and Heat Transfer in Hydrocarbon Rocket Fuels written by and published by . This book was released on 1983 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Deposit Formation in Hydrocarbon Rocket Fuels by :
Download or read book Deposit Formation in Hydrocarbon Rocket Fuels written by and published by . This book was released on 1981 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Deposit Formation and Heat Transfer in Hydrocarbon Rocket Fuels by : Anthony J. Giovanetti
Download or read book Deposit Formation and Heat Transfer in Hydrocarbon Rocket Fuels written by Anthony J. Giovanetti and published by . This book was released on 1983 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit July 11-14, 2004, Fort Lauderdale, FL.: 04-3850 - 04-3899 by :
Download or read book 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit July 11-14, 2004, Fort Lauderdale, FL.: 04-3850 - 04-3899 written by and published by . This book was released on 2004 with total page 556 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Heat-transfer Effects in Rocket Nozzles Operating with Very High-temperature Hydrogen by : John R. Howell
Download or read book Analysis of Heat-transfer Effects in Rocket Nozzles Operating with Very High-temperature Hydrogen written by John R. Howell and published by . This book was released on 1965 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical technique suitable for & the solution of complex energy transfer problems involving coupled radiant and convective energy transfer is developed. Solutions for the coupled axial wall energy flax distribution in rocket nozzles using hydrogen as a propellant are presented. Flow rates and temperatures studied are near those forecast for gaseous-core nuclear-propulsion systems. Parameters varied are nozzle shape, inlet propellant temperature, mean reactor cavity temperature, and nozzle wall temperature level. The effects of variation of the propellant radiation absorption coefficient with pressure, temperature, and wavelength are presented, and real property variations are used where they appear to be significant. Comparison is made to a simplified, coupled solution using a modified second-order one-dimensional diffusion equation for the radiative transfer. At the temperature levels assumed, radiative transfer may account for a greater portion of the total energy transfer over important portions of the nozzle, and its effects cannot, therefore, be neglected. Extreme energy flaxes (near 3XlO to the 8 Btu/(hr)(sq ft)) are observed for certain cases, and this implies that new nozzle cooling techniques must be developed.
Book Synopsis Journal of Propulsion and Power by :
Download or read book Journal of Propulsion and Power written by and published by . This book was released on 2008 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Study of the Effect of the Fuel Film on Heat Transfer in a Rocket Engine Combustion Chamber by : Sing H. Goh
Download or read book Numerical Study of the Effect of the Fuel Film on Heat Transfer in a Rocket Engine Combustion Chamber written by Sing H. Goh and published by . This book was released on 2003-12-01 with total page 89 pages. Available in PDF, EPUB and Kindle. Book excerpt: The combustion chamber of a liquid-fueled rocket engine with an injected fuel film on the wall has been numerically simulated. The engine has been modeled to operate on a RP-1/gaseous oxygen mixture at a chamber pressure of 35 atmospheres. The fuel is a hydrocarbon blend and is used for both engine operation and the fuel-film layer. The fuel layer acts as a flowing thermal insulating shield, reducing the amount of convective and radiative heat flux from the hot combustion gases to the chamber wall. This effort evaluates the effectiveness of the fuel layer in achieving a reduced heat flux to the chamber wall under varying emission/absorption conditions. The tendency of hydrocarbon fuels to produce soot precipitates at near 550K directly affects the optical properties of the fuel layer and the resulting heat transfer to the wall has been modeled and discussed.
Book Synopsis 43rd AIAA Aerospace Sciences Meeting & Exhibit by :
Download or read book 43rd AIAA Aerospace Sciences Meeting & Exhibit written by and published by . This book was released on 2005 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat- and Mass-transfer Characteristics of an Axial-flow Liquid-core Nuclear Rocket Employing Radiation Heat Transfer by : Robert G. Ragsdale
Download or read book Heat- and Mass-transfer Characteristics of an Axial-flow Liquid-core Nuclear Rocket Employing Radiation Heat Transfer written by Robert G. Ragsdale and published by . This book was released on 1967 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Combustion Characteristics of Thermally Stressed Hydrocarbon Fuels by : Colin William Curtis
Download or read book Combustion Characteristics of Thermally Stressed Hydrocarbon Fuels written by Colin William Curtis and published by . This book was released on 2016 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: Liquid propelled propulsion systems, which range from rocket systems to hypersonic scramjet and ramjet engines, require active cooling in order to prevent additional payload requirements. In these systems, the liquid fuel is used as a coolant and is delivered through micro-channels that surround the combustion chambers, nozzles, as well as the exterior surfaces in order to extract heat from these affected areas. During this process, heat exchange occurs through phase change, sensible heat extraction, and endothermic reactions experienced by the liquid fuel. Previous research has demonstrated the significant modifications in fuel composition and changes to the fuel's physical properties that can result from these endothermic reactions. As a next step, we are experimentally investigating the effect that endothermic reactions have on fundamental flame behavior for real hydrocarbon fuels that are used as rocket and jet propellants. To achieve this goal, we have developed a counter-flow flame burner to measure extinction limits of the thermally stressed fuels. The counter-flow flame system is to be coupled with a high pressure reactor, capable of subjecting the fuel to 170 atm and 873 K, effectively simulating the extreme environment that cause the liquid fuel to experience endothermic reactions. The fundamental flame properties of the reacted fuels will be compared to those of unreacted fuels, allowing us to determine the role of endothermic reactions on the combustion behavior of current hydrocarbon jet and rocket propellants. To quantify the change in transport properties and chemical kinetics of the reacting mixture, simultaneous numerical simulations of the reactor portion of the experiment coupled with a counterflow flame simulation are performed using n-heptane and n-dodecane.
Book Synopsis 41st AIAA Aerospace Sciences Meeting & Exhibit by :
Download or read book 41st AIAA Aerospace Sciences Meeting & Exhibit written by and published by . This book was released on 2003 with total page 566 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Application of Various Techniques for Determining Local Heat-transfer Coefficients in a Rocket Engine from Transient Experimental Data by : Curt H. Liebert
Download or read book Application of Various Techniques for Determining Local Heat-transfer Coefficients in a Rocket Engine from Transient Experimental Data written by Curt H. Liebert and published by . This book was released on 1960 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer in Rocket Engines by : H. Ziebland
Download or read book Heat Transfer in Rocket Engines written by H. Ziebland and published by . This book was released on 1971 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the first part of this book the various basic heat transfer processes are considered, -- simple convective heat transfer from hot gases to the engine walls under various conditions, radiation heat transfer, and coolant heat transfer processes. This part is followed by one describing the various methods of cooling used in liquid propellant rocket engines, such as regenerative, film, ablation and radiation cooling. The final part concerns the properties of materials that will have to be known by the engine designer, from the transport properties of the hot combustion gases to those of the materials from which the engine will be constructed. Emphasis was placed on presenting simple methods for calculating the magnitude of heat transfer rather than providing the most modern and rigorous theories, particularly in the field of developing boundary layers. (Author).
Book Synopsis Experimental Heat-transfer Study of a Regeneratively Cooled Hydrogen-fluorine Rocket Engine at Low Chamber Pressure by :
Download or read book Experimental Heat-transfer Study of a Regeneratively Cooled Hydrogen-fluorine Rocket Engine at Low Chamber Pressure written by and published by . This book was released on 1967 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of the Transient Radiation Heat Transfer of an Uncooled Rocket Engine Operating Outside Earth's Atmosphere by : William H. Robbins
Download or read book Analysis of the Transient Radiation Heat Transfer of an Uncooled Rocket Engine Operating Outside Earth's Atmosphere written by William H. Robbins and published by . This book was released on 1959 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hot-gas-side Heat Transfer Characteristics of Subscale, Plug-nozzle Rocket Calorimeter Chamber by : Richard J. Quentmeyer
Download or read book Hot-gas-side Heat Transfer Characteristics of Subscale, Plug-nozzle Rocket Calorimeter Chamber written by Richard J. Quentmeyer and published by . This book was released on 1993 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
