Statistical description of the size properties of non uniform particulate substances

Hatch, Theodore F.; Choate, Sarah P.

doi:10.1016/s0016-0032(29)91451-4

Cited by 274 publications

(86 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…The median diameter of the distribution of any moment is equal to the corresponding geometric mean diameter, and is related to the integral of that moment by a simple factor. The median size of any moment is connected to the median size of any other moment by an analytical relationship derived by Hatch and Choate (1929).…”

Section: Introductionmentioning

confidence: 99%

Properties of the Log-Normal Particle Size Distribution

Heintzenberg

1994

Aerosol Science and Technology

169

View full text Add to dashboard Cite

show abstract

Section: Introductionmentioning

confidence: 99%

Properties of the Log-Normal Particle Size Distribution

Heintzenberg

1994

Aerosol Science and Technology

169

View full text Add to dashboard Cite

show abstract

“…If the drop size distribution is log-normal, the MMD can readily be related to other statistical drop size quantities using the Hatch-Choate formula [68]. and 10% of centerline gas velocity, respectively.…”

Section: Hatch-choate Formulamentioning

confidence: 99%

“…In case of nozzle configuration of Crowe et al [50], the chamber pressures are chosen to compensate pressure variation according to Hermsen [10]. Table 3.4 The particle phase inlet boundary conditions -for Crowe et al [68]'s experiments …”

Section: Dispersed Phase Boundary Conditionsmentioning

confidence: 99%

Fuel Chemistry And Combustion Distribution Effects On Rocket Engine Combustion Stability

Anderson¹,

Heister²,

Son³

2015

View full text Add to dashboard Cite

Air Force Materiel Command REPORT DOCUMENTATION PAGE Form Approved OMB No. 0704-0188The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. 1. REPORT DATE (DD-MM-YYYY)2. REPORT TYPE (From -To) Final Technical DATES COVERED SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)AF Office of Scientific Research 875 N. Randolph St. Room 3112 Arlington, VA 22203 SPONSOR/MONITOR'S ACRONYM(S) AFOSR SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for Public Release; Distribution Unlimited SUPPLEMENTARY NOTES ABSTRACTThe goal of the project was to understand how changes in the rate of energy addition can be used to alter the combustion instability characteristics of liquid rocket engines. Fuels with increased energy, either due to higher heats of formation or energetic additives, presumably result in higher performance. This study seeks to understand how changes in combustion rate, due to fuel chemistry changes, might be used to develop high-performing, stable rocket engines. The overall objective of the project was to develop a fundamental understanding of how the spatial distribution of combustion and its temporal response to pressure oscillations depends on kinetic rates, flammability limits, and energy release density. The study combines basic drop combustion experiments, an in situ study using a spontaneously unstable model rocket combustor, and associated modeling of particles in combustion chamber gas flows. SUBJECT TERMSenergetic propellants, combustion stability, particulate dynamics FUEL CHEMISTRY AND COMBUSTION DISTRIBUTION EFFECTS ON ROCKET ENGINE COMBUSTION STABILITYThe goal of the project was to understand how changes in the rate of energy addition can be used to alter the combustion instability characteristics of liquid rocket engines. Fuels with increased energy, either due to higher heats of formation or energetic additives, presumably result in higher performance. This study seeks to understand how changes in combustion rate, due to fuel chemistry changes, might be used to develop high-performing, stable rocket engines. The overall objective of the project was to develop a fundamental understanding of how the spatial distri...

show abstract

“…Additionally, the particles were assumed to be spherical. This has been shown to be a reasonable assumption for solution MDIs (8) The following equations use the theory developed by Hatch and Choate (9) and adapted by Hinds (10). For a spherical particle, the relationship between aerosol mass, M, and number of particles, N, is shown in Eq.…”

Section: Estimating the Number Of Drug Particles In An MDI Plumementioning

confidence: 99%

Estimating the Number of Droplets and Drug Particles Emitted from MDIs

Stein

2008

AAPS PharmSciTech

View full text Add to dashboard Cite

Abstract. The objective of this paper is to assess the number of drug particles or droplets contained in metered dose inhaler (MDI) aerosols. Equations were developed to estimate this. The number of drug particles was estimated to be as high as about 300 million for QVAR ® solution MDIs and as low as 670,000 for Beclovent™ MDIs. The number of particles in MDI aerosols was shown to be highly dependent on the mass median aerodynamic diameter (MMAD) and geometric standard deviation, and to a lesser extent the total mass of the aerosol. It was demonstrated that when the number of particles are calculated assuming that the aerosol is monodisperse and using the MMAD as the particle size, the number of particles are significantly underestimated. The number of droplets atomized from HFA-134a MDIs was estimated to range from about 220 million to about 1.1 billion droplets per actuation. For solution MDIs, each of the atomized droplets contains drug and thus the number of drug particles is the same as the number of atomized droplets. However, for suspension MDI formulations many of the droplets do not contain any micronized drug particles and the number of drug particles is much lower than the number of atomized droplets.

show abstract

Statistical description of the size properties of non uniform particulate substances

Cited by 274 publications

References 0 publications

Properties of the Log-Normal Particle Size Distribution

Properties of the Log-Normal Particle Size Distribution

Fuel Chemistry And Combustion Distribution Effects On Rocket Engine Combustion Stability

Estimating the Number of Droplets and Drug Particles Emitted from MDIs

Contact Info

Product

Resources

About