Apr 16, 1989 - 0808-01004, RND 2. BREECH. 175.5. 560.4. 1026-08. 0809-02004, RND 4. BREECH. 271.3. 1144.4. 1026-09. 0809-03004, RND 6. BREECH.
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FILE COT'
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IITRI C06673 COMBUSTION PRODUCT EVALUATION OF VARIOUS LHARGE SIZES AND PROPELLANT FORMULATIONS
(D
FINAL REPORT
00 N
by
DTIC I
Alan Snelson Paul AseT Kevin Taylor
Sydney Gordon
April 1989
V
f
W
Supported by: U. S. Army Medical Research and Development Command Fort Detrick, Frederick, Maryland 21702-5012 Contract No. DAMD17-88-C-8006 lIT Research Institute 10 West 35th Street Chicago, Illinois 60616
I
Contracting Officer's Representative: Steve Hoke U. S. Army Biomedical Research and Development Laboratory Fort Detrick, Frederick, Maryland 21702-5010 Approved for public release; distribution unlimited The findings in this report are not to be construed as an official Department of the Army position unless so designated by other authorized document
I016
T
0ELECTE
*EE
I
SECURITY CLASSIFICATION OF THIS PAGE Form Approved
REPORT DOCUMENTATION PAGE
OMNo.rod18
la. REPORT SECURITY CLASSIFICATION
lb. RESTRICTIVE MARKINGS
2a. SECURITY CLASSIFICATION AUTHORITY
3. DISTRIBUTION /AVAILABILITY OF REPORT
UnclassifiedI
Approved for public release: distribution unlimited
2b. DECLASSIFICATION IDOWNGRADING SCHEDULE 4. PERFORMING ORGANIZATION REPORT NUMBER(S)
5. MONITORING ORGANIZATION REPORT NUMBER(S)
IITRI C06673 6a. NAME OF PERFORMING ORGANIZATION
6b. OFFICE SYMBOL
lIT Research Institute
7a. NAME OF MONITORING ORGANIZATION
U.S. Army Biomedical Research
(Ifapplicable)
and Development Laboratory
6c. ADDRESS (City, State, and ZIP Code)
Chicago, Illinois
7b. ADDRESS (City, State, and ZIP Code)
60616
8a. NAME OF FUNDING/SPONSORING
Fort Detrick Frederick, Maryland
U.S. Army Medical Research & Development Command
8b. OFFICE SYMBOL
ORGANIZATION
9. PROCUREMENT INSTRUMENT IDENTIFICATION NUMBER
DAMDl7-88-C-8006
(If applicable)
8c. ADDRESS (City, State, and ZIP Code)
Fort Detrick Frederick, Maryland
21702-5010
10. SOURCE OF FUNDING NUMBERS TASK PROGRAM PROJECT
ELEMENT NO.
21702-5012
62787A
NO.
3E1
WORK UNIT
ACCESSION NO.
NO.
CA
62787A878
304
11. TITLE (Include Security Classification)
Combustion Product Evaluation of Various Charge Sizes and Propellant
Formulations
12. PERSONAL AUTHOR(S)
Snelson, Alan; Ase, Paul; Taylor, Kevin; and Gordon, Sydney 13a. TYPE OF REPORT
13b. TIME COVERED
Final Report
FROM
114. DATE OF REPORT (Year,Month,Day)
10/15/87To3/31/89
11. PAGE COUNT
1989 April
16. SUPPLEMENTARY NOTATION
17. FIELD,
06 \ 19 19 ABSTRA
COSATI CODES GROUP SUB-G OUP
14 06 (Continue on reverse if
(
-?SUBJECT TERMS(Cofvt*nue-n riwse-tlg e.aryandi'Of r' Tniumber)-'-
P 'opel lant Combustion Products f~m-2 4-mer guns, Propel 1ants; WG890...i30-,-JA2-and-M30A- -Spec-ies inorganic gases, 644r, aldehydes, PAWa nd volatile orqanicsRA3
ecessary and identify by block dumber)
',-j..C
Combustion produc s from 25, 105, 120, and 155 mm caliber guns firing rounds containing WC890, M30, JA2, nd M30Al propellants, respectively have been determined. Combustion gases were sampled from t e breech on all guns, from spent casings (25 and 105mmcaiiberguns) and from a bore evacuator Pn a 155mmcaliber run. To a greater or lesser degree thefollowing species wereruantified:
"1) volatile inorganic gases and methane: C0 , CO, H , CH , HCN,
2 2 4 NH HX, NOx, and S0j (2 aldehydes; formaldehyde, acetaldehyde,, acrolein/acetone, propionaldehyde, crotonaldehyde, sobutyl aldehyde, benzaldehyde, and hexanaldehyde; (3) Polynuclear Aromatic Hydrocarbons: pheranthrene, anthracene, pyrene, benz-a-anthracene, chrysene, benz-bfluoranthene, benz-k-fluor nthene, benz-a-pyrene, and benz-ghi-perylene; and (4)selected volatile organics: benzene acrylonitrile, ethylbenzene, toluene, pyridine, styrene, cyanobenzene, and naphthalene. Where possible predicted propellant combustion product distributions based on thermodynamic equilibrium calculation (Blake Tiger Code) were compared with those measured experimentally in the study. In general, the agreement was poor. Combustion 20. DISTRIBUTION /AVAILABILITY OF ABSTRACT j-'UNCLASSIFIED/UNLIMITED 0 SAME AS RPT. 22a. NAME OF RESPONSIBLE INDIVIDUAL
21. ABSTRACT SECURITY CLASSIFICATION 0
Unclassified
DTIC USERS
22b. TELEPHONE (Include Area Code) 22c. OFFICE SYMBOL
Mrs. Virginia M. Miller DD Form 1473, JUN 86
301/663-7325 Previous editions are obsolete.
ii
SGRD-RMI-S SECURITY CLASSIFICATION OF THIS PAGE
I FOREWORD lIT Research Institute (IITRI) is pleased to submit this final report on the study entitled "Combustion Product Evaluation of Various Charge Sizes and Propellant Formulations" performed under Contract DAMD17-88-C-8006 for the U.S. Army Biomedical Research and Development Laboratory. The program started in October 1987 and the experiiiental work ended in March 1989. The report contains new information on the nature and amounts of combustion products formed from four gun types and propellant systems not previously available.
I
3 I
We would like to acknowledge the enthusiasm and support received from Dr. Steve Hoke of the U.S. Army Biomedical Researrh and Development Laboratory. Dr. Eli Freeman of the Interior Eallistics Division, Ballistics Research Laboratory, Aberdeen Proving Gruund, kindly provided theoretical performance calculations on some 30 propellant types. Finally, we offer our thanks to the following personnel: Mr. Chilean Smith, Mr. Cecil E. Martin, Mr. Robert Schnell, Mr. Dewey Collins, Mr. Thomas Dieter, Mr, Jim Andrew, Mr. Gary Hoss, and Ms. Sharon L. Hickey of the Combat Systems Test Activity, Advanced Systems Division of Aberdeen Proving Ground, without whose help and cooperation this study could not have been performed.
I
Citations of commercial organizations and trade names in this report does not constitute an official Department of the Army endorsement or approval of the products and services of these organizations. Acoessior NTIS GR
Respectfully submitted, !ITResearch Institute
r
DTIC TAB Unannounced
n
A
Alan Snelson By Distribution/ Availability Codos Avail and/or Specla6 Dist
a
Iiii
Science Advisor :\Chemistry
Research Section
4, -
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IITRI C06673-Final
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EXECUTIVE SUMMARY Maintenance of the soldier's health and mental acuity on the battlefield is of obvious importance to the U.S. Army. Exposure of the soldier to propellant combustion products, both gaseous and particulate, represents a potential health hazard.
5 3l I
Conventional nitro-based propellants are known to produce relatively large amounts of nitrogen, hydrogen, water, carbon monoxide and carbon dioxide and smaller amounts of nitrogen oxides and ammonia on combustion. If sulfur is present in the propellant mix, small amounts of hydrogen sulfide and sulfur oxides are also formed. In enclosed weapo; systems, such as tanks, inadequately designed ventilating systems could subject the crew to dangerous toxic gas exposure. In a recent study for the U.S rmy Medical Refearch and Development Command, the combustion products fr%.,a an M16 rifle ?iring rounds containing WC844 propellant were subjected to u rather detailed chemical analyses. A large number of trace chemical species, volatile organics and PAHs were identified in addition to the more abundant combustion products noted above. Computer modeling of the combustion product distribution showed good agreement with experiment for the major combustion products H 2, CO, C02, and N 2 based on
the concept of "frozen equilibrium", but was of more limited value in replicating concentrations of the minor species such as HCN, CH4 , and NOx .
i
Alant
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The present program had several objectives all related to the chemical characterization of gun propellant smoke: (a) Are the qualitative and quantitative yields of combustion products from a given gun propellant in any way related to the gun caliber? (b) Are the qualitative and quantitative yields of combustion products from a given caliber gun dependent on the propeltype? (c) Is computer modeling of gun propellent combustion product distribution a realistic approach for determining the real world combustion product distributions?
lIT RESEARCH INSTITUTE
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IITRI C06673-Final
I, (d) Are combustion product distributions determined in breech gases, the same as those present in spent shell casings? (e) Are combustion product distributions in gases sampled from a bore evacuator indicative of a composition that might be expected if the breech gases were subjected to the phenomenon of muzzle flash? Originally, it was hoped that definitive answers could be obtained to all the above questions. However, very early in the program it became evident that although the experiments required to obtain answers to (a) and (b) above were conceptually straightforward, practically they would be extremely expensive to perform since special propellant formulations (non-standard) would have to be manufactured. Accordingly, the decision was made early in the program to study combustion product yields from weapons of a variety of calibers using whatever rounds and associated propellants that were available at Aberdeen Proving Ground.
5I
In previous studies by IITRI, the results from thermodynamic computer modeling of propellant combustion product formation were compared to those derived from experimental data. Using the concept of "frozen equilibrium" it was shown that theoretically computed combustion product distributions were in fairly good agreement with experimental values for major products such as CO, C02 , and H2 but were of rather uncertain value with respect to predicting the
more minor species. The purpose of the present study was to further assess the usefulness of the computer modeling of combustion product distributions respect to real world behavior.
5with
There have been reports from personnel in the field that emissions from spent shell casings were more objectionable than emissions directly inhaled form the gun breech. The purpose of the present study was to determine if the product emissions from spent shell casings were in any way different from those from the breech.
5combustion P
Finally, it is well known that with many larger caliber guns a phenomenon called muzzle flash occurs. In this situation, the fuel-rich gases in the propellant combustion products on exiting the muzzle undergo a secondary oxidation which changes the composition of the primary propellant combustion products.
Since military personnel may be exposed to the muzzle flash gases,
it was of interest to determine their composition.
Due to severe over-
lIT RESEARCH INSTITUTE
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IITRI C06673-Final
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3
pressures that result on firing large caliber guns, sampling combustion products from the muzzle gases is extremely difficult. A suggestion was made that the gases contained in a bore evacuator may undergo oxidation similar to that occurring in muzzle flash and thus provide a relatively simple means of determining muzzle gas compositions. An attempt was therefore made to analyze samples of gas extracted from a bore evacuator on a 155 mm caliber gun. Combustion Product Distribution Determined for Breech, Spent Casing, and Bore Evacuator Gun Smoke Samples
I
3 5
At the initiation of the program a detailed report (4) was prepared entitled "Sampling and Analytical Procedures Prepared for the In Gun Propellant Combustion Product Characterization" that described the sampling and analytical procedures to be used in the program. The methods proposed were largely based on IITRI prior experience in the subject area. The report has been accepted as an end product of the program and will not be further discussed here. In the program, sampling and analytical procedures noted in the above report were implemented to obtain combustion products from 25, 105, 120, and 155 mm caliber guns firing rounds containing WC890, M30, JA2, and M30A1 propellants, respectively. Combustion gases were sampled from the breech on all guns, from spent casings of 25 mm and 105 mm caliber guns (the 120 mm round has a combustible cartridge case, and the 155 mm round uses a bag charge neither of which has a casing to be sampled), and from the bore evacuator on a 155 mm caliber gun. To a greater or lesser degree the following species were quantified:
(1) volatile inorganic gases and methane: C02, CO, H 2, CH4 , HCN,
NH3 , H2S, N0x , and S0 X; (2) aldehydes: formaldehyde, acetaldehyde, acrolein/ acetone, propionaldehyde, crotonaldehyde, isobutyl aldehyde, benzaldehyde, and hexanaldehyde; (3) polynuclear aromatic hydrocarbons: phenanthrene, anthracene, pyrene, benz-a-anthracene, chrysene, benz-b-fluoranthene, benz-k-fluoranthene, benz-a-pyrene, and benz-ghi-perylene; and (4) selected volatile organics: benzene, acrylonitrile, ethylbenzene, toluene, pyridine, styrene, cyanobenzene, and naphthalene. The analytical data for the species have been presented in their final form in terms of the ratio of the moles of analyte per mole of carbon monoxide in the sampled combustion gas. Carbon monoxide was chosen as the reference gas for the following reasons: lIT RESEARCH INSTITUTE
vi
IITRI C06673-Final
(1) Thermodynamic propellant combustion product calculations indicate that all commonly used propellants generate significant quantities of carbon monoxide, up to 40 mole % of the total gaseous combustion products. (2) Background concentration levels of CO are low, probably 0000 0000) 00 00 00 o oc00
toC~\-4 (y
00 q~* M
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0
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111' RESEARCH INSTITUTE
IITRI C06673-Final
I [Table 5]), are in close agreement as anticipated.
3
3
Similar behavior is shown
in most of the other groupings. There are clearly some exceptions. Thus in the group, GC Run Nos. 37, 43, 29 and 49, the concentrations (Vol %) of the analyzed gases found in flask #49 are clearly lower than those found in the other three flasks sampling the same combustion gas. It is possible that the valve on flask #49 was not fully opened when the sample was taken resulting in a gas volume being collected at less than atmospheric pressure. However, since the final analytical results are reported in terms of species concentration relative to unit concentration of CO, the data are not compromised. There is also a marked difference in the inorganic gases and methane concentrations determined in the initial sampling experiments (04/28/88) and those determined later (08/09/88). This in part could be due to differing amounts of dilution air entering the gun barrel during the two sampling processes. Another contributing factor may be related to the nature of the projectile. In the initial tests, the projectile was of conventional "bullet shape", whereas in the later series of tests the projectile (heavier and blunt) was designed to deliberately produce maximum gun recoil (high impulse) with the object of "proofing" new barrels prior to their installation in tanks. 4.2.2 Raw Data Sets for Analytically Determined CN-, NH3 , S = , SOx, and NOx
Combustion gases collected in the 1-liter glass flask were analyzed initially for their CO, C02 , H 2 , N 2 and CH4 content using gas chromatography and
5 3
the data assembled as described in 4.2.1. After these analyses the solutions in these flasks were removed and analyzed for the above titled species. According to TEI control or spiked samples (EPA certified solutions) were made during these analyses to confirm integrity of the reported data. The resulting analytical data are presented in Tables 6 through 9. Cyanide and ammonia samples were analyzed by TEl of Niles, Illinois, and the results quoted in terms of concentration of the species determined in a 50-ml sample volume. Sulfide ion was analyzed at IITRI and results reported as total S= in the sample. Similarly, SOx and NOx were determined at IITRI in terms of the mass
5
of S04 and NO
m
converted to micrograms of analyte per liter of collected sample and combined with analogous data for the CO associated with each sample, Table 10.
I 3
contained in a 1-liter gas sample.
These data were then all
lIT RESEARCH INSTITUTE
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IITRI C06673-Final
I 1
TABLE 6. COMBUSTION PRODUCT DATA EXAMPLE:
GUN, XM256; BORE, 120 14;
PROPELLANT, JA2 - HCN ANALYSIS RAW DATA
m
Total (1) Sample No.
Cyanide (mg/L)
Emission Source
0428-01001[A] 0428-01001[B] 0428-02001[Al 0428-02001[B] 0428-06001 0809-01001 0809-02001 0809-03001 0809-04001 0809-05001 0809-06001 0809-11001 0809-12001 0809-13001
BREECH BREECH BREECH BREECH BACKGROUND BREECH BREECH BREECH BREECH BREECH BACKGROUND STANDARD, 0.302 mg/L(a) STANDARD, 3.02 mg/L STANDARD, 15.11 mg/L
18.3 12.3 23.8 18.9 *
12.4 23.5 9.82 12.5 14.8 0.29 3.31 16.7
(1)SOLUTION VOLUME = 50 mL (a) DETECTION LIMIT (0.1 mg/L) =BELOW SAMPLES a) CONTROL
3
TABLE 7. COMBUSTION PRODUCT DATA EXAMPLE:
GUN, XM256; BORE, 120 MM;
PROPELLANT, JA2 - NH3 ANALYSIS RAW DATA
Sample No.
3
0428-01002[A] 0428-01002[B] 0428-020021[Al 0428-020021[B] 0428-06002 0809-01002 0809-02002 0809-03002 0809-04002 0809-05002 0809-06002 0809-11002 0809-12002 0809-13002
Emission Source BREECH BREECH BREECH BREECH BACKGROUND BREECH BREECH BREECH BREECH BREECH BACKGROUND STANDARD, 2.42 mg/L(a) STANDARD, 9.66 mg/L STANDARD, 48.3 mg/L
Total(1) Ammonia
(mg/L) 25.6 27.2 32.2 37.8 100 109 104 103 116 0.16 2 7.64 34.1
(1) SOLUTION VOLUME = 50 mL *
=
BELOW DETECTION LIMIT (0.1 mg/L)
(a) CONTROL SAMPLES
I 3
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IITRI C06673-Final
I TABLE 8. COMBUSTION PRODUCT DATA EXAMPLE: GUN, XM256; BORE, 120 MM; PROPELLANT, JA2- H2S ANALYSIS RAW DATA
Sample No.
Emission Source
0809-01003 0809-02003 0809-03003 0809-04003 0809-05003 0809-06003
BREECH BREECH BREECH BREECH BREECH BACKGROUND
3=BELOW
(from H 2S) (micrograms) 34.2 121.1 33.2 27.3 74.2 *
DETECTION LIMIT (0.4 micrograms)
i I TABLE 9. COMBUSTION PRODUCT DATA EXAMPLE: GUN, X)256; BORE, 120 MM; PROPELLANT, JA2, - NOX AND SOX ANALYSIS RAW DATA 1 ) (
Total Sample Concentration (microgram/L Air) Analysis No. 0719-02 0719-04 0719-08 0719-09 1026-07 1026-08 1026-09 1026-10 1026-11 1026-12
1
(
Emissions Source
Sample Source
NO-
SO2-
0428-01004, 0428-03004, 0428-04004, 0428-06004, 0808-01004, 0809-02004, 0809-03004, 0809-04004, 0809-05004, 0809-06004,
BREECH BREECH BREECH BKGD BREECH BREECH BREECH BREECH BREECH BKGD
79.5 80.9 70.1 8.1 175.5 271.3 122.9 167.6 242.6 14.4
1096.0 1271.1 1077.3 10.7 560.4 1144.4 288.0 336.6 731.1 11.0
RND 1 RND 2 RND 2 BACKGROUND RND 2 RND 4 RND 6 RNO 8 RND 9 BACKGROUND
DETECTION LIMIT - NO- = 0.1 micrograms/L AIR -
so -
= 0.1
micrograms/L AIR
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CONTROL SAMPLES 4.2.3 Final Data Compilation for Inorganic Gases and Methane Relative to Carbon Monoxide (Moles/Mole) Present in the Combustion Products Io Table 11 the data for the inorganic gases and methane are presented in their final form in terms of moles of species per mole of carbon monoxide in the combustion products. The table contains data derived for each species separately and average values. On examination of the data in Taule 11 it is clear that the analytical results obtained on 04/28/89 were not in good agreement with those obtained on 8/09/89. were computed for these data.
For this reason, two separate averages
4.2.4 Raw and Final Data Sets for PAH Analyses
3 m
m
m * m
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Data are presented in Table 12 from the analyses of PAHs in combustion product gases in terms of mass concentration of a given PAH per liter of combustion gas sampled. In the initial tests on 04/28/89, this volume was set at 30 liters whereas in the second series of tests a volume of 20 liters was used. Under the heading Emissions Source in Table 12 for rounds 3 and 4 sampled on 04/28/89, the abbreviation SM, FULL EVAC is used. This indicates that the metal cylinder used to obtain a sample of the collected combustion gas f,. subsequent CO analyses had a volume of 281 ml and was fully evacuated prior to obtaining the sample. This designation was used to differentiate the different metal cylinder sampling volumes used in the initial range finding studies. In all subsequent studies, only one sampling volume was used, the small metal cylinder fully evacuated. Hence, it was not necessary to indicate this in future data compilations. Data are presented in Table 13 giving the final results in terms of moles of PAH per mole of carbon monoxide in the combustion gases. In deriving these data corrections were made for the background PAH concentrations. In some cases, this resulted in negative values for the ratios. Examination of these results shows that PAH concentrations relative to carbon monoxide were approximately two orders of magnitude greater in the tests on 04/28/89 than those reported in the tests of 08/09/89.
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1 0 0101 IITRI 0667-Fna
m I
observed, could well be in good agreement at some temperature in the 1,500 to 1,000K range. However, the temperature dependence of the C02 /CO ratio clearly indicates that the observed and computed values of the ratio will never be in agreement within this temperature range.
m
It should be noted that the thermodynamic equilibrium calculations are made for pure propellant compositions. All the propellant systems studied had additional material present in the reaction zone consisting of primers, Strand Benite and inerts (see Table 1 for details). Thus, the computed combustion product distribution for Strand Benite (Table 22) an ingredient in the JA2 propellant round, has a markedly different combustion product/CO ratio distribution than that of the main propellant, JA2. With the JA2 propellant system two different sets of experimentally observed combustion product ratios were obtained, one set corresponding to a normal projectile firing (04/28/89) and a second set from firings of a heavier, blunted projectile to maximize gun recoil (08/09/89). Neither set of combustion product ratios is in good agree-
m
ment with each other or with the theoretical values. These above computed data are for the main propellant charges only and do not add much support to the suggestion that for the four species, H 2 , CO, C02,
3 *
3 3 m m
and H20, equilibrium becomes "frozen in" at temperatures in the range 15001200K. However, the conclusion is compromised since the computed values assume a pure propellant whilst in the real world systems studied this was not the case. In an effort to overcome this deficiency a series of calculations were made for the WC890, JA2, M30, and M30A1 propellants in which the additives to the main charges (Table 1) were included in the combustion product calculations. In order to do this it was necessary to assume that all the materials, main propellant charge plus additives, were homogenously mixed prior to and after firing the charge. Clearly this assumption is not correct prior to firing the charge. How well mixing of small amounts of additive combustion products with those of the main charge occurs after firing is problematical. Data from these calculations are presented in Tables 19B through 23B. Comparison of the H2/CO and C02 /CO computed ratios for the main propellant charge and main propellant charge plus additives show in general only small differences and no improvement in their agreement with the experimental values.
m
3
lIT RESEARCH INSTITUTE
56
IITRI C06673-Final
m Similarly, the two methods of computations for the minor species/CO combustion product ratios are generally similar, and no consistent improvement in agreement is obtained between the computed and experimentally observed product ratios. Inclusion of the additives in the computations does provide one distinct benefit in those cases where the additives contain sulfur and the main propellant charge does not (e.g., JA2, M30, and M3OA1) in so much that sulfur compounds do appear in the computed combustion products in agreement with experimental findings. i
3
Overall, theoretical combustion product calculations for trace species appear to be of little value. Data presented in Tables 19, 20, 21, an d 23 show that for the species for which computed and experimental combustion product ratios are available, differences in the latter quantities range from i2 to 106 ignoring the concept of "frozen equilibrium" and trying to obtain the best match between the calculated (any temperature in the range computed) and experimental ratios. In the one propellant where the concept of "frozen equilibrium" appears to apply for H 2, CO, and C02 at =1,40OK (i.e., M30) the
difference between the computed and experimental ratios ranges from =6 (CH4 /CO) to 2 x 10s (NO/CO) at the "equilibrium" temperature. This finding implies equilibrium for these species is "frozen in" at temperatures different than those for H 2, CO and C02 . For HCN, NO, and SOX computed combustion prod-
uct/CO ratios are most nearly in agreement with observed values at temperatures much greater than 1,500K, in most cases, close to the computed maximum flame temperature of .2,600K. 5.2
3
EXPERIMENTAL DATA FOR INORGANIC GASES/CO AND CH4 /CO COMBUSTION PRODUCT RATIOS 5.2.1
Breech Samples
Experimentally determined average values and relative standard deviations for inorganics gases/CO and CH4 /CO combustion product ratios are presented in
m
I 3
Table 24 for the four gun types studied. It is noted that two sets of data are presented for breech gas analyses of the 120 mm and 155 mm caliber weapons. In both cases, the weapons were sampled on different dates and under different conditions. The first set of data for the 120 mm weapon (Table 24) on breech gas samples was made with the gun firing a regular projectile. When obtaining the second set of data, a heavier blunt projectile was fired with lIT RESEARCH INSTITUTE
57
IITRI C06673-Final
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lIT RESEARCH INSTITUTE
358
IITRI C06673-Final
m the object of maximizing the recoil action of the weapon. The first set of data for the 155 mm caliber weapon (10/04/88, Table 24) was obtained on breech gas samples with rounds fired at ambient temperature, whereas when obtaining the second set of data (03/04-07/89) the rounds were conditioned to 125°F. m
Comparison of these data sets shows that the differing firing conditions for the same propellant had an effect on the combustion product distribution, most marked in 120 mm data, not only for the major species H 2, C02 and CO, but also
for the trace species. m
3
The range of values found for the combustion product ratios obtained experimentally for the four weapons and propellant systems studies are summarized at the bottom of Table 24.
For the major species H 2 and C02, the high
and low values vary by factors of 2.1 and 3, respectively.
For the trace
species, the low and high values vary by factors ranging from 7.5 (NH3/CO) to
5
220 (SO). It is noted that differences in computed and experimental combustion product ratios for these same trace species (Section 5.1) varied from a low of 6 to a high of 2 x 1 5.2.2 Breech Versus Spent Casing Samples
I
3 m
3
Experimentally determined average values and relative standard deviations for inorganic gas/CO and CH4 /CO combustion product ratios are presented in Table 24 for breech and spent casing samples obtained from 25 mm and 105 mm caliber weapons. For both weapons differences between product ratios obtained from breech and spent casing samples are quite small and generally overlap within the stated error limits. For these combustion product species no convincing differences are apparent in data from breech and spent casing samples. As noted earlier, it was not possible to obtain spent casing combustion product samples from the 120 mm (combustible cartridge) and 155 mm (bag charge) weapons. 5.2.3
Breech Versus Bore Evacuator Samples
Experimentally determined average values and relative standard deviations for inorganic gas/CO and CH4 /CO combustion product ratios are presented in
I
3 m
3
Table 24 for breech and bore evacuator samples obtained from a 155 mm caliber weapon. The data are limited. With the exception of product ratios for CH4/CO and HCN/CO, the ratios for the other gases are not significantly different from the two sources. -Although the breech and bore evacuator ratios lIT RESEARCH INSTITUTE
59
IITRI C06673-Final
I for HCN/CO are markedly different, the negative value for one of the ratios raises significant questions with respect to its validity. The larger value
3
found for the bore evacuator ratio for CH 4/CO compared to the breech value suggests that oxidation of hot gases in the bore evacuator must occur to a very minor degree if at all. It is further noted that the pressure of gas (combustion products plus air originally present) in the evacuator builds up to .200 psi during its operation. The mole ratio of oxygen to combustible species (H2 and CO) is about 1:35 at the highest operational pressure, suggesting that at best only a very minor degree of combustion gas oxidation is likely to occur. These findings indicate that oxidation of combustion product gases in the bore evacuator cannot be used to simulate the effect of muzzle flash on the combustion product distribution as was originally hoped. 5.3
EXPERIMENTAL DATA FOR POLYNUCLEAR HYDROCARBONS/CO COMBUSTION PRODUCT RATIOS
Experimentally determined average values and relative standard deviations for PAH/CO combustion product ratios are presented in Table 25. Of the ten PAHs that were assayed, all were detected in the combustion products from all four weapons studies with the exception of anthracene which was absent from the 120 and 155 mm caliber guns. Most of the PAH/CO ratios were in the 10-8 10-10Orange with a few values ccurring in the 10- range for the heavier
3
molecular weight PAHs. For the 25 mm and 105 mm caliber weapons, PAH/CO ratios were remarkedly similar in both, varying only by a factor of two for the individual ratios. Overall, the PAH/CO ratios were found to be largest in the 155 caliber gun, (anthracene excepted), with all values lying in the 10-8 to 10-7 range.
35.4 1
EXPERIMENTAL DATA FOR ALDEHYDE/CO COMBUSTION PRODUCT RATIOS
Experimentally determined average values and relative standard deviations for aldehyde/CO combustion product ratios are presented in Table 26. For the eight aldehydes analyzed, measured aldehyde/CO ratios varied from a high of 3.31 x 10-5 to a low of 1.31 x 10-8 excluding the one zero value. There was a weak indication that aldehyde/CO ratios in the spent casing samples (25 and 105 mm caliber guns) were slightly larger than in the corresponding breech samples.
IlIT
RESEARCH INSTITUTE
60
IITRI C06673-Final
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