Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720518440
Category :
Languages : en
Pages : 28
Book Description
Rocket thrusters for Rocket Based Combined Cycle (RBCC) engines typically operate with hydrogen/oxygen propellants in a very compact space. Packaging considerations lead to designs with either axisymmetric or two-dimensional throat sections. Nozzles tend to be either two- or three-dimensional. Heat transfer characteristics, particularly in the throat, where the peak heat flux occurs, are not well understood. Heat transfer predictions for these small thrusters have been made with one-dimensional analysis such as the Bartz equation or scaling of test data from much larger thrusters. The current work addresses this issue with an experimental program that examines the heat transfer characteristics of a gaseous oxygen (GO2)/gaseous hydrogen (GH2) two-dimensional compact rocket thruster. The experiments involved measuring the axial wall temperature profile in the nozzle region of a water-cooled gaseous oxygen/gaseous hydrogen rocket thruster at a pressure of 3.45 MPa. The wall temperature measurements in the thruster nozzle in concert with Bartz's correlation are utilized in a one-dimensional model to obtain axial profiles of nozzle wall heat flux.Santoro, Robert J. and Pal, SibtoshMarshall Space Flight CenterHEAT TRANSFER; ROCKET NOZZLES; COMPUTATIONAL FLUID DYNAMICS; LIQUID COOLING; HYDROGEN; OXYGEN; PROPELLANTS; HEAT FLUX; TEMPERATURE PROFILES; WALL TEMPERATURE
Experimental Studies of the Heat Transfer to Rbcc Rocket Nozzles for Cfd Application to Design Methodologies
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720518440
Category :
Languages : en
Pages : 28
Book Description
Rocket thrusters for Rocket Based Combined Cycle (RBCC) engines typically operate with hydrogen/oxygen propellants in a very compact space. Packaging considerations lead to designs with either axisymmetric or two-dimensional throat sections. Nozzles tend to be either two- or three-dimensional. Heat transfer characteristics, particularly in the throat, where the peak heat flux occurs, are not well understood. Heat transfer predictions for these small thrusters have been made with one-dimensional analysis such as the Bartz equation or scaling of test data from much larger thrusters. The current work addresses this issue with an experimental program that examines the heat transfer characteristics of a gaseous oxygen (GO2)/gaseous hydrogen (GH2) two-dimensional compact rocket thruster. The experiments involved measuring the axial wall temperature profile in the nozzle region of a water-cooled gaseous oxygen/gaseous hydrogen rocket thruster at a pressure of 3.45 MPa. The wall temperature measurements in the thruster nozzle in concert with Bartz's correlation are utilized in a one-dimensional model to obtain axial profiles of nozzle wall heat flux.Santoro, Robert J. and Pal, SibtoshMarshall Space Flight CenterHEAT TRANSFER; ROCKET NOZZLES; COMPUTATIONAL FLUID DYNAMICS; LIQUID COOLING; HYDROGEN; OXYGEN; PROPELLANTS; HEAT FLUX; TEMPERATURE PROFILES; WALL TEMPERATURE
Publisher: Createspace Independent Publishing Platform
ISBN: 9781720518440
Category :
Languages : en
Pages : 28
Book Description
Rocket thrusters for Rocket Based Combined Cycle (RBCC) engines typically operate with hydrogen/oxygen propellants in a very compact space. Packaging considerations lead to designs with either axisymmetric or two-dimensional throat sections. Nozzles tend to be either two- or three-dimensional. Heat transfer characteristics, particularly in the throat, where the peak heat flux occurs, are not well understood. Heat transfer predictions for these small thrusters have been made with one-dimensional analysis such as the Bartz equation or scaling of test data from much larger thrusters. The current work addresses this issue with an experimental program that examines the heat transfer characteristics of a gaseous oxygen (GO2)/gaseous hydrogen (GH2) two-dimensional compact rocket thruster. The experiments involved measuring the axial wall temperature profile in the nozzle region of a water-cooled gaseous oxygen/gaseous hydrogen rocket thruster at a pressure of 3.45 MPa. The wall temperature measurements in the thruster nozzle in concert with Bartz's correlation are utilized in a one-dimensional model to obtain axial profiles of nozzle wall heat flux.Santoro, Robert J. and Pal, SibtoshMarshall Space Flight CenterHEAT TRANSFER; ROCKET NOZZLES; COMPUTATIONAL FLUID DYNAMICS; LIQUID COOLING; HYDROGEN; OXYGEN; PROPELLANTS; HEAT FLUX; TEMPERATURE PROFILES; WALL TEMPERATURE
Analysis of Heat-transfer Effects in Rocket Nozzles Operating with Very High-temperature Hydrogen
Author: John R. Howell
Publisher:
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.
Publisher:
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.
The Use of Energy Thickness in Prediction of Throat Heat Transfer in Rocket Nozzles
Author: Robert W. Graham
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 36
Book Description
Energy thickness in prediction of throat heat transfer in rocket nozzles using nozzle geometries and temperature ratios.
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 36
Book Description
Energy thickness in prediction of throat heat transfer in rocket nozzles using nozzle geometries and temperature ratios.
Experimental Investigation of the Feasibility of Ablation-cooling a Rocket Nozzle with Possible Application to Solid-propellant Engines
Author: Richard R. Cullom
Publisher:
ISBN:
Category : Ablation (Aerothermodynamics)
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category : Ablation (Aerothermodynamics)
Languages : en
Pages : 44
Book Description
Application of Various Techniques for Determining Local Heat-transfer Coefficients in a Rocket Engine from Transient Experimental Data
Author: Curt H. Liebert
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 38
Book Description
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 38
Book Description
Experimental Evaluation of Heat Transfer on a 1030:1 Area Ratio Rocket Nozzle
Author: Kenneth J. Kacynski
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
Book Description
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
Book Description
International Aerospace Abstracts
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 974
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 974
Book Description
Prediction of Local and Integrated Heat Transfer in Nozzles Using an Integral Turbulent Boundary Layer
Author: Donald R. Boldman
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 36
Book Description
An empirical modification of an existing integral energy turbulent boundary layer method is proposed in order to improve the estimates of local heat transfer in converging-diverging nozzles and consequently, provide better assessments of the total or integrated heat transfer. The method involves the use of a modified momentum-heat analogy which includes an acceleration term comprising the nozzle geometry and free stream velocity. The original and modified theories are applied to heat transfer data from previous studies which used heated air in 30 deg - 15 deg, 45 deg - 15 deg, and 60 deg - 15 deg water-cooled nozzles.
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 36
Book Description
An empirical modification of an existing integral energy turbulent boundary layer method is proposed in order to improve the estimates of local heat transfer in converging-diverging nozzles and consequently, provide better assessments of the total or integrated heat transfer. The method involves the use of a modified momentum-heat analogy which includes an acceleration term comprising the nozzle geometry and free stream velocity. The original and modified theories are applied to heat transfer data from previous studies which used heated air in 30 deg - 15 deg, 45 deg - 15 deg, and 60 deg - 15 deg water-cooled nozzles.
CFD and Heat Transfer Analysis of Rocket Cooling Techniques on an Aerospike Nozzle
Author: Geoffrey Sullivan
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 0
Book Description
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 0
Book Description
Journal of Thermophysics and Heat Transfer
Author:
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 1238
Book Description
This journal is devoted to the advancement of the science and technology of thermophysics and heat transfer through the dissemination of original research papers disclosing new technical knowledge and exploratory developments and applications based on new knowledge. It publishes papers that deal with the properties and mechanisms involved in thermal energy transfer and storage in gases, liquids, and solids or combinations thereof. These studies include conductive, convective, and radiative modes alone or in combination and the effects of the environment.
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 1238
Book Description
This journal is devoted to the advancement of the science and technology of thermophysics and heat transfer through the dissemination of original research papers disclosing new technical knowledge and exploratory developments and applications based on new knowledge. It publishes papers that deal with the properties and mechanisms involved in thermal energy transfer and storage in gases, liquids, and solids or combinations thereof. These studies include conductive, convective, and radiative modes alone or in combination and the effects of the environment.