Author: Harvey E. NeumannPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 36
Book Description
A Comparative Analysis of Convective Heat Transfer in a Nuclear Rocket Nozzle
Author: Harvey E. NeumannPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 36
Book Description
Analysis of Heat-transfer Effects in Rocket Nozzles Operating with Very High-temperature Hydrogen
Author: John R. HowellPublisher:
ISBN:
Category : Energy transfer
Languages : en
Pages : 44
Book Description
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.
Analysis, Feasibility, and Wall-temperature Distribution of a Radiation-cooled Nuclear-rocket Nozzle
Author: William H. RobbinsPublisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 36
Book Description
Comparison of Predicted Nozzle Coolant Side Heat Transfer and Fluid Flow with Experimental Values from Phoebus-2A Nuclear Tests
Author: Maynard F. TaylorAnalysis of Heat-transfer Effects in Rocket Nozzles Operating with Very High-temperature Hydrogen
Author: John R. HowellPublisher:
ISBN:
Category : Energy transfer
Languages : en
Pages : 42
Book Description
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.
Comparative Studies of Convective Heat Transfer Models for Rocket Engines
Author: J. C. DeLiseNASA Technical Note
Author: An Analysis of Nuclear-rocket Nozzle Cooling
Author: William H. RobbinsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
A nuclear-rocket regenerative-cooling analysis was conducted over a range of reactor power of 46 to 1600 megawatts and is summarized herein. Although the propellant (hydrogen) is characterized by a large heat-sink capacity, an analysis of the local heat-flux capability of the coolant at the nozzle throat indicated that, for conventional values of system pressure drop, the cooling capability was inadequate to maintain a selected wall temperature of 1440 R. Several techniques for improving the cooling capability were discussed, for example, high pressure drop, high wall temperature, refractory wall coatings, thin highly conductive walls, and film cooling. In any specific design a combination of methods will probably be utilized to achieve successful cooling.
NASA Technical Note
Author: An Analysis of Thermal Radiation Heat Transfer in a Nuclear-rocket Nozzle
Author: William H. RobbinsPublisher:
ISBN:
Category : Propulsion systems
Languages : en
Pages : 28
Book Description