Author: A. J. Zazzi
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
The investigation was conducted mainly to determine the possibility of burning fuel-rich combustible exhaust gas mixtures by the injection of either gaseous oxygen or gaseous carbon dioxide into the exhaust stream. The burning of the combustibles, especially hydrogen, results in a large volume decrease when the hot gas in cooled. The reaction of the oxygen or carbon dioxide with combustible products (hydrogen rich in this test) was possible, as evidenced by the results of the chemical analysis of the exhaust products. The possibility of generating an electrostatic field along the viscous mixing boundary between two gases was studied using argon, helium, and stream jets at different energy levels. An electrostatic field along the viscous mixing boundary between two gases (one being steam) was produced in an ungrounded installation; even with only a steam jet in an ungrounded installation, an electrostatic field was generated. (Author).
Some Experimental Tests to Change the Total Volume And/or Molecular Weight of Rocket Engine Exhaust Gas in an Altitude Test Facility
Author: A. J. Zazzi
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
The investigation was conducted mainly to determine the possibility of burning fuel-rich combustible exhaust gas mixtures by the injection of either gaseous oxygen or gaseous carbon dioxide into the exhaust stream. The burning of the combustibles, especially hydrogen, results in a large volume decrease when the hot gas in cooled. The reaction of the oxygen or carbon dioxide with combustible products (hydrogen rich in this test) was possible, as evidenced by the results of the chemical analysis of the exhaust products. The possibility of generating an electrostatic field along the viscous mixing boundary between two gases was studied using argon, helium, and stream jets at different energy levels. An electrostatic field along the viscous mixing boundary between two gases (one being steam) was produced in an ungrounded installation; even with only a steam jet in an ungrounded installation, an electrostatic field was generated. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 58
Book Description
The investigation was conducted mainly to determine the possibility of burning fuel-rich combustible exhaust gas mixtures by the injection of either gaseous oxygen or gaseous carbon dioxide into the exhaust stream. The burning of the combustibles, especially hydrogen, results in a large volume decrease when the hot gas in cooled. The reaction of the oxygen or carbon dioxide with combustible products (hydrogen rich in this test) was possible, as evidenced by the results of the chemical analysis of the exhaust products. The possibility of generating an electrostatic field along the viscous mixing boundary between two gases was studied using argon, helium, and stream jets at different energy levels. An electrostatic field along the viscous mixing boundary between two gases (one being steam) was produced in an ungrounded installation; even with only a steam jet in an ungrounded installation, an electrostatic field was generated. (Author).
Experimental Investigation in an Altitude Test Facility of Burning of Excess Combustibles in a Rocket Engine Exhaust
Author: Harry E. Bloomer
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 30
Book Description
Publisher:
ISBN:
Category : Rocket engines
Languages : en
Pages : 30
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1064
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1064
Book Description
Government Reports Announcements
Author:
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 948
Book Description
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 948
Book Description
Analysis of Flammability Limits and Gas Properties of a Solid Rocket Motor Test in a High Altitude Test Facility
Author: Richard Scott Kirkpatrick
Publisher:
ISBN:
Category :
Languages : en
Pages : 61
Book Description
The testing of solid and liquid rocket propulsion systems in a confined test facility often produces explosive or flammable gases which must be safely handled. Often inert gases such as nitrogen are used to lower the molar fraction of oxygen to low enough levels to minimize the probability of an explosion or deflagration. For this thesis, the chemical composition of these rocket exhaust gases mixed with air were used to determine the flammability limits of the gas mixture. Using the ideal gas law and the conservation of mass, the exhaust gas composition and gas properties such as pressure, temperature, volume and mole fractions inside the test facility were calculated. This exhaust gas composition along with La Chatelier's law was applied to an air-free basis for calculating the flammability limits of the rocket exhaust gas in air. Using Test Driven Development and Object Oriented Programming, a computer program using the Python programming language was created with a Graphical User Interface (GUI) to automate these calculations. This program was validated using existing analytical techniques developed at the Arnold Engineering Development Complex (AEDC). The results from the Python program agree well, a maximum of 1.4% difference, with the validated AEDC techniques.
Publisher:
ISBN:
Category :
Languages : en
Pages : 61
Book Description
The testing of solid and liquid rocket propulsion systems in a confined test facility often produces explosive or flammable gases which must be safely handled. Often inert gases such as nitrogen are used to lower the molar fraction of oxygen to low enough levels to minimize the probability of an explosion or deflagration. For this thesis, the chemical composition of these rocket exhaust gases mixed with air were used to determine the flammability limits of the gas mixture. Using the ideal gas law and the conservation of mass, the exhaust gas composition and gas properties such as pressure, temperature, volume and mole fractions inside the test facility were calculated. This exhaust gas composition along with La Chatelier's law was applied to an air-free basis for calculating the flammability limits of the rocket exhaust gas in air. Using Test Driven Development and Object Oriented Programming, a computer program using the Python programming language was created with a Graphical User Interface (GUI) to automate these calculations. This program was validated using existing analytical techniques developed at the Arnold Engineering Development Complex (AEDC). The results from the Python program agree well, a maximum of 1.4% difference, with the validated AEDC techniques.
Government Reports Announcements & Index
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 208
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 208
Book Description
Government Reports Index
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1074
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1074
Book Description
Determination of Rocket Exhaust Gas Temperatures and Emissivities by Infrared Spectral Methods. Simulated High Altitude Tests of a Scale Model Rocket Engine
Author: STANLEY A. DOLIN
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
To supplement laboratory studies of infrared radiance of flames, infrared spectral emittance and absorptance of the exhaust plume of a Hydrogen-Oxygen rocket engine were measured. The engine, a tenth-scale model of the Saturn-IV, was fired in an altitude test chamber, under conditions simulating altitudes from 96,000 to 145,000 feet. Exhaust gas temperatures and emissivities were determined from the infrared spectral measurements. Laboratory measurements of hydrogen-oxygen flame emissivities were extrapolated to the case of the test rocket engine. The measured results verified the extrapolation, within the range of error determined by experiment and the limitations of the extrapolation procedure. It is concluded that the results support the extrapolation from laboratory flame measurements, and that refinement of both theory and experiment are required, to improve accuracy. The tests also demonstrated the utility of the IMRA infrared technique and instrumentation for measuring gas temperatures in rocket engines. (Author).
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
To supplement laboratory studies of infrared radiance of flames, infrared spectral emittance and absorptance of the exhaust plume of a Hydrogen-Oxygen rocket engine were measured. The engine, a tenth-scale model of the Saturn-IV, was fired in an altitude test chamber, under conditions simulating altitudes from 96,000 to 145,000 feet. Exhaust gas temperatures and emissivities were determined from the infrared spectral measurements. Laboratory measurements of hydrogen-oxygen flame emissivities were extrapolated to the case of the test rocket engine. The measured results verified the extrapolation, within the range of error determined by experiment and the limitations of the extrapolation procedure. It is concluded that the results support the extrapolation from laboratory flame measurements, and that refinement of both theory and experiment are required, to improve accuracy. The tests also demonstrated the utility of the IMRA infrared technique and instrumentation for measuring gas temperatures in rocket engines. (Author).
Bibliography of Scientific and Industrial Reports
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 980
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 980
Book Description
EPA-600/7
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 528
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 528
Book Description