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Record 1 of 16587
A fast sampling device for the mass spectrometric analysis of liquid rocket engine exhaust
Author and Affiliation:
Ryason, P. R.(California Institute of Technology, Jet Propulsion Laboratory, Pasadena, Calif., United States)
Abstract: The design of a device to obtain compositional data on rocket exhaust by direct sampling of reactive flow exhausts into a mass spectrometer is presented. Sampling at three stages differing in pressure and orifice angle and diameter is possible. Results of calibration with pure gases and gas mixtures are erratic and of unknown accuracy for H2, limiting the usefulness of the apparatus for determining oxidizer/fuel ratios from combustion product analysis. Deposition effects are discussed, and data obtained from rocket exhaust spectra are analyzed to give O/F ratios and mixture ratio distribution. The O/F ratio determined spectrometrically is insufficiently accurate for quantitative comparison with cold flow data. However, a criterion for operating conditions with improved mixing of fuel and oxidizer which is consistent with cold flow results may be obtained by inspection of contour plots. A chemical inefficiency in the combustion process when oxidizer is in excess is observed from reactive flow measurements. Present results were obtained with N2O4/N2H4 propellants.
Publication Date: Sep 01, 1975
Document ID:
19750061597
(Acquired Dec 01, 1995)
Accession Number: 75A45669
Subject Category: INSTRUMENTATION AND PHOTOGRAPHY
Report/Patent Number: AIAA PAPER 75-1270
Document Type: Conference Paper
Publisher Information: United States
Meeting Information: American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference; 11th; Sept. 29, 1975-Oct. 1, 1975; Anaheim, CA
Meeting Sponsor: American Institute of Aeronautics and Astronautics;
Society of Automotive Engineers
Contract/Grant/Task Num: NAS7-100
Financial Sponsor: NASA; United States
Description: 8p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: COMBUSTION PRODUCTS; LIQUID PROPELLANT ROCKET ENGINES; MASS SPECTROSCOPY; ROCKET EXHAUST; SPECTROSCOPIC ANALYSIS; CALIBRATING; CHEMICAL COMPOSITION; JET IMPINGEMENT; SPECTRUM ANALYSIS
Imprint And Other Notes: American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference, 11th, Anaheim, Calif., Sept. 29-Oct. 1, 1975, AIAA 8 p.
Availability Source: Other Sources
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