1、Designation: D1405/D1405M 08 (Reapproved 2013)Standard Test Method forEstimation of Net Heat of Combustion of Aviation Fuels1This standard is issued under the fixed designation D1405/D1405M; the number immediately following the designation indicates theyear of original adoption or, in the case of re
2、vision, the year of last revision. A number in parentheses indicates the year of lastreapproval. A superscript epsilon () indicates an editorial change since the last revision or reapproval.This standard has been approved for use by agencies of the Department of Defense.1. Scope1.1 This test method
3、covers the estimation of the net heat ofcombustion at constant pressure in SI units (megajoules perkilogram) or inch-pound units Btu per pound.1.2 This test method is purely empirical and is applicableonly to liquid hydrocarbon fuels derived by normal refiningprocesses from conventional crude oil, w
4、hich conform to therequirements of specifications for aviation gasolines, or aircraftturbine and jet engine fuels of limited boiling ranges andcompositions as described in Note 1.NOTE 1The estimation of the net heat of combustion of a hydrocarbonfuel from aniline-gravity product is justifiable only
5、when the fuel belongsto a well-defined class for which a relation between heat of combustionand aniline-gravity product has been derived from accurate experimentalmeasurements on representative samples of that class. Even in this case,the possibility that the estimates may be in error by large amoun
6、ts forindividual fuels should be recognized. The classes of fuels used toestablish the correlation presented in this test method are represented bythe following specifications:Fuel SpecificationAviation gasoline fuels: Specification D910Grades 80, 82, 100/130, and 115/145 Specification D6227DEF STAN
7、 9190NATO Code F-18Aviation turbine fuels: MIL-DTL-5624JP-4,Avtag/FSII DEF STAN 9188NATO Code F-40JP-5,Avcat/FSII MIL-DTL-5624DEF STAN 9186NATO Code F-44Jet A, Jet A-1, Avtur Specification D1655DEF STAN 9191NATO Code F-351.3 This test method is not applicable to pure hydrocarbons.It is not intended
8、as a substitute for experimental measurementsof heat of combustion.1.4 The heat of combustion may also be determined in SIunits by Test Method D4529. Test Method D4529 requirescalculation of a single equation for all aviation fuels with aprecision equivalent to that of this test method.1.5 The value
9、s stated in either SI units or inch-pound unitsare to be regarded separately as standard. The values stated ineach system may not be exact equivalents; therefore, eachsystem shall be used independently of the other. Combiningvalues from the two systems may result in non-conformancewith the standard.
10、1.6 This standard does not purport to address all of thesafety concerns, if any, associated with its use. It is theresponsibility of the user of this standard to establish appro-priate safety and health practices and determine the applica-bility of regulatory limitations prior to use.2. Referenced D
11、ocuments2.1 ASTM Standards:2D129 Test Method for Sulfur in Petroleum Products (Gen-eral High Pressure Decomposition Device Method)D240 Test Method for Heat of Combustion of Liquid Hy-drocarbon Fuels by Bomb CalorimeterD287 Test Method for API Gravity of Crude Petroleum andPetroleum Products (Hydrome
12、ter Method)D611 Test Methods for Aniline Point and Mixed AnilinePoint of Petroleum Products and Hydrocarbon SolventsD910 Specification for Aviation GasolinesD941 Test Method for Density and Relative Density (Spe-cific Gravity) of Liquids by Lipkin Bicapillary Pycnom-eter (Withdrawn 1993)3D1217 Test
13、Method for Density and Relative Density (Spe-cific Gravity) of Liquids by Bingham PycnometerD1250 Guide for Use of the Petroleum Measurement TablesD1266 Test Method for Sulfur in Petroleum Products (LampMethod)1This test method is under the jurisdiction of ASTM Committee D02 onPetroleum Products and
14、 Lubricants and is the direct responsibility of SubcommitteeD02.05 on Properties of Fuels, Petroleum Coke and Carbon Material.Current edition approved May 1, 2013. Published August 2013. Originallyapproved in 1956. Last previous edition approved in 2008 as D1405/D1405M 08.DOI: 10.1520/D1405_D1405M-0
15、8R13.This test method has been approved by the sponsoring committee and acceptedby the Cooperating Societies in accordance with established procedures.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.org. For Annual Book of ASTMStan
16、dards volume information, refer to the standards Document Summary page onthe ASTM website.3The last approved version of this historical standard is referenced onwww.astm.org.Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States1D1298 Test M
17、ethod for Density, Relative Density, or APIGravity of Crude Petroleum and Liquid Petroleum Prod-ucts by Hydrometer MethodD1655 Specification for Aviation Turbine FuelsD2622 Test Method for Sulfur in Petroleum Products byWavelength Dispersive X-ray Fluorescence SpectrometryD3120 Test Method for Trace
18、 Quantities of Sulfur in LightLiquid Petroleum Hydrocarbons by Oxidative Microcou-lometryD4052 Test Method for Density, Relative Density, and APIGravity of Liquids by Digital Density MeterD4294 Test Method for Sulfur in Petroleum and PetroleumProducts by Energy Dispersive X-ray Fluorescence Spec-tro
19、metryD4529 Test Method for Estimation of Net Heat of Combus-tion of Aviation FuelsD4809 Test Method for Heat of Combustion of LiquidHydrocarbon Fuels by Bomb Calorimeter (PrecisionMethod)D5453 Test Method for Determination of Total Sulfur inLight Hydrocarbons, Spark Ignition Engine Fuel, DieselEngin
20、e Fuel, and Engine Oil by Ultraviolet FluorescenceD6227 Specification for Unleaded Aviation Gasoline Con-taining a Non-hydrocarbon Component2.2 U.S. Military Standards:4MIL-DTL-5624 Aviation Turbine Fuels, Grades JP-4, JP-5,and JP-5/JP-8 STMIL-T-83133 Aviation Turbine Fuel, Grade JP-82.3 Directorate
21、 of Standardization, Ministry of Defence:5DEF STAN 9186 Aviation Turbine Fuel, High Flash Kero-sene Type with Fuel System Icing InhibitorDEF STAN 9188 Aviation Turbine Fuel, Wide Cut Typewith Fuel System Icing InhibitorDEF STAN 9190 Aviation Gasoline 80 and 100LLDEF STAN 9191 Aviation Turbine Fuel,
22、Kerosene Type,Jet A-12.4 NATO Codes:5F-18 Aviation GasolineF-35 Aviation Turbine Fuel, Jet A TypeF-40 Aviation Turbine Fuel, Grade JP-4F-44 Aviation Turbine Fuel, Grade JP-53. Summary of Test Method3.1 Correlations6,7have been established between the netheat of combustion and the product of the anil
23、ine point andAPIgravity. These relations, assuming the sample to be sulfur free,are given by the following equations:3.1.1 Where the net heat of combustion is required in SIunits (Note 2) (megajoules per kilogram):Type Fuel EquationAviation gasoline, Grades100130 and 115145Qp snetd 5 41.95571 (1)0.0
24、0020543 sA 3GdJP-4Qp snetd 5 41.81451 (2)0.00024563 sA 3GdJP-5Qp snetd 5 41.66801 (3)0.00024563 sA 3GdKerosine Jet A or A-1Qp snetd 5 41.67961 (4)0.00025407 sA 3Gdwhere:Qp(net) = net heat of combustion, MJ/kg, on a sulfur-free basis,A = aniline point, F, andG = gravity, API.NOTE 2In SI, the unit of
25、heat of combustion has the dimensions J/kg,but for practical use a multiple is more convenient. The megajoule perkilogram (MJ/kg) is 106J/kg and is customarily used for the representa-tion of heats of combustion of petroleum fuels, particularly for mixturessuch as those covered in this International
26、 Standard.3.1.2 Where the net heat of combustion is required ininch-pound units or British Thermal Units Btu per pound.Type Fuel EquationAviation gasoline, Grades100130 and 115145Qp snetd 5 18037.71 (5)0.0883 sA 3GdJP-4Qp snetd 5 179771 (6)0.1056 sA 3GdJP-5Qp snetd 5 17914 (7)10.1056 sA 3GdKerosine
27、Jet A or A-1Qp snetd 5 179191 (8)0.10923 sA 3Gdwhere:Qp(net) = net heat of combustion, Btu/lb, on a sulfur-free basis,A = aniline point, F, andG = gravity, API.3.2 To correct for the effect of the sulfur content of thesample on the net heat of combustion, apply the followingequation:3.2.1 Where the
28、net heat of combustion is required in SIunits (megajoules per kilogram):Q 5 Qpnet! 3 1 2 0.01S!#10.1016S! (9)where:Q = net heat of combustion, MJ/kg, of the samplecontaining S % sulfur,4Available from Standardization Documents Order Desk, DODSSP, Bldg. 4,Section D, 700 Robbins Ave., Philadelphia, PA
29、 19111-5098, http:/www.dodssp.daps.mil.5Available from Directorate of Standardization, Stan Ops I, Room 1138,Kentigern House, 65 Brown Street, Glasgow, G2 8EX, U.K.6Cogliano, J. A., and Jessup, R. S., “Relation Between Net Heat of Combustionand Aniline-Gravity Product of Aircraft Fuels,” ASTM Bullet
30、in, ASTBA, No. 201,October 1954, p. 55 (TP 217); also the National Institute of Standards andTechnology findings as reported by Armstrong, G. T., Jessup, R. S., and Mears, T.W., “Net Heat of Combustion of Aviation Gasoline and its Correlations with OtherProperties,” Journal of Chemical and Engineeri
31、ng Data, Vol 3, 1958, pp. 2028.7Armstrong, G. T., Fano, L., Jessup, R. S., Marantz, S., Mears, T. W., andWalker, J. A., “Net Heat of Combustion and Other Properties of Kerosene andRelated Fuels,” Journal of Chemical and Engineering Data, National Institute ofStandards and Technology, Gaithersburg, M
32、D. Vol 7, No. 1, January 1962, pp.107117.D1405/D1405M 08 (2013)2S = sulfur content of the sample, mass, %, and0.1016 = a constant based on the thermo-chemical data onsulfur compounds.3.2.2 Where the net heat of combustion is required ininch-pound units or British Thermal Units Btu per pound:Q 5 Qpne
33、t! 3 1 2 0.01S!#143.7S! (10)where:Q = net heat of combustion, Btu/lb, of the sample con-taining S % sulfur,S = sulfur content of the sample, mass %, and43.7 = a constant based on the thermochemical data onsulfur compounds.3.3 The empirical linear Eq 1-4 and Eq 5-9 for the estimatednet heat of combus
34、tion were derived by the method of leastsquares from accurate data on fuels, most of which conformedat least approximately to specifications for aviation gasolines,or aircraft turbine and jet engine fuels of Types JP-4 and JP-5and to Specification D1655, Jet A and A-1.4. Significance and Use4.1 This
35、 test method is intended for use as a guide in caseswhere an experimental determination of heat of combustion isnot available and cannot be made conveniently, and where anestimate is considered satisfactory. It is not intended as asubstitute for experimental measurements of heat of combus-tion.NOTE
36、3The procedure for the experimental determination of the netheat of combustion is described in Test Methods D240 and D4809.5. Procedure5.1 Determine the aniline points of the sample to the nearest0.05C 0.1F as described in Test Method D611.5.2 Determine the API gravity of the sample to the nearest0.
37、1 API as described in Test Method D287. Alternatively,determine the relative density by Test Methods D941, D1217,and D4052 and correct the result to API gravity by GuideD1250.5.3 Determine the sulfur content of the sample to the nearest0.02 % sulfur as described in Test Methods D129, D1266,D2622, D3
38、120, D4294,orD5453 depending upon the volatil-ity of the sample.6. Calculation6.1 Calculate the product of the aniline point in degreesFahrenheit and the gravity in degrees API; round off the valueobtained to the nearest integer.6.2 From Tables 1-8, make a linear interpolation betweenrows bracketing
39、 the aniline-gravity products and within col-umns bracketing the sulfur content of the sample. Use the tableapplicable to the type of product being tested. Thus, use Table1 or Table 5 forAviation Gasolines, Table 2 or Table 6 for JP-4jet-type fuels; Table 3 or Table 7 for JP-5 jet type fuels, andTab
40、le 4 or Table 8 for kerosene-type aviation turbine fuels(Specification D1655, Jet A or A-1).TABLE 1 Values of Q for Aviation Gasolines Calculated from Eq1 and Eq 9 in MJ/kgAniline-GravityProductNet Heat of Combustion, MJ/kg0% Sulfur 0.1% Sulfur 0.2% Sulfur 0.3% Sulfur 0.4% Sulfur4 000 42.777 42.745
41、42.712 42.680 42.6474 200 42.819 42.786 42.753 42.721 42.6884 400 42.860 42.827 42.794 42.761 42.7294 600 42.901 42.868 42.835 42.802 42.7704 800 42.942 42.909 42.876 42.843 42.8115 000 42.983 42.950 42.917 42.884 42.8525 200 43.024 42.991 42.958 42.925 42.8925 400 43.065 43.032 42.999 42.966 42.933
42、5 600 43.106 43.073 43.040 43.007 42.9745 800 43.147 43.114 43.081 43.048 43.0156 000 43.188 43.155 43.122 43.089 43.0566 200 43.229 43.196 43.163 43.130 43.0976 400 43.270 43.237 43.204 43.171 43.1386 600 43.312 43.278 43.245 43.212 43.1796 800 43.353 43.319 43.286 43.253 43.2207 000 43.394 43.360
43、43.327 43.294 43.2617 200 43.435 43.402 43.368 43.335 43.3027 400 43.476 43.443 43.409 43.376 43.3437 600 43.517 43.484 43.450 43.417 43.3847 800 43.558 43.525 43.491 43.458 43.4248 000 43.599 43.566 43.532 43.499 43.4658 200 43.640 43.607 43.573 43.540 43.5068 400 43.681 43.648 43.614 43.581 43.547
44、8 600 43.722 43.689 43.655 43.622 43.5888 800 43.763 43.730 43.696 43.663 43.6299 000 43.805 43.771 43.737 43.704 43.6709 200 43.846 43.812 43.778 43.745 43.7119 400 43.887 43.853 43.819 43.786 43.7529 600 43.928 43.894 43.860 43.827 43.7939 800 43.969 43.935 43.901 43.867 43.83410 000 44.010 43.976
45、 43.942 43.908 43.87510 200 44.051 44.017 43.983 43.949 43.91610 400 44.092 44.058 44.024 43.990 43.95610 600 44.133 44.099 44.065 44.031 43.99710 800 44.174 44.140 44.106 44.072 44.03811 000 44.215 44.181 44.147 44.113 44.07911 200 44.257 44.222 44.188 44.154 44.12011 400 44.298 44.263 44.229 44.19
46、5 44.16111 600 44.339 44.305 44.270 44.236 44.20211 800 44.380 44.346 44.311 44.277 44.24312 000 44.421 44.387 44.352 44.318 44.284D1405/D1405M 08 (2013)36.3 From the values obtained in 6.2, make a linear interpo-lation for the sulfur content within the row for the calculatedaniline gravity constant
47、.6.3.1 Example:Sample: JP-4 Fuel6.3.1.1 Determined Values:Aniline point, A = 137FGravity, G = 54.8 APISulfur content = 0.10 mass %6.3.1.2 Calculated Value:AG product = 7508By interpolation from Table 2:A G 0 % Sulfur 0.1 % Sulfur 0.2 % Sulfur74007508A760043.63243.659B43.68143.625C43.56543.592B43.614
48、By interpolation from Table 6:AG 0.0 % Sulfur 0.1 % Sulfur 0.2 % Sulfur74007508A760018 75818 769B18 77918 755C18 72918 740B18 750AValue calculated from determined values.BFirst step interpolation between rows in columns bracketing the sulfur content.CSecond step interpolation within a row between co
49、lumns.6.3.1.3 Estimated Net Heat of Combustion:43.625 MJ/kg18 755 Btu/lb7. Report7.1 Report the result in megajoule per kilogram to thenearest 0.001 or British thermal units per pound to the nearestinteger as estimated Net Heat of Combustion, D1405 orD1405M.8. Precision and Bias8.1 RepeatabilityThe difference between successive testresults obtained by the same operator with the apparatus underconstant operating conditions on identical test material (usinga second set of measured values for the aniline pointtemperature, the
