ASTM D4529-2001(2006) Standard Test Method for Estimation of Net Heat of Combustion of Aviation Fuels《航空燃料燃烧净热值的评价的标准试验方法》.pdf

1、Designation: D 4529 01 (Reapproved 2006)Designation: 381/97An American National StandardStandard Test Method forEstimation of Net Heat of Combustion of Aviation Fuels1This standard is issued under the fixed designation D 4529; the number immediately following the designation indicates the year ofori

2、ginal adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. Asuperscript epsilon (e) indicates an editorial change since the last revision or reapproval.1. Scope1.1 This test method covers the estimation of the net heat ofcomb

3、ustion at constant pressure in metric (SI) units, mega-joules per kilogram.1.2 This test method is purely empirical, and it is applicableonly to liquid hydrocarbon fuels derived by normal refiningprocesses from conventional crude oil which conform to therequirements of specifications for aviation ga

4、solines 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 hydrocar-bon fuel from its aniline point temperature and density is justifiable onlywhen the fuel belongs to a well-defined class f

5、or which a relationshipbetween these quantities has been derived from accurate experimentalmeasurements on representative samples of that class. Even in this class,the possibility that the estimates can be in error by large amounts forindividual fuels should be recognized. The JP-8 fuel, although no

6、texperimentally tested, has properties similar to JP-5 and Jet A fuels andcan be considered in the same class. The classes of fuels used to establishthe correlation presented in this test method are represented by thefollowing applications:Fuel SpecificationAviation gasoline fuels: Specification D 9

7、10Grades 80, 82, 100/130, and 115/145 Specification D 6227DEF STAN 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-44JP-8, Avtur/FSII MIL-DTL-83133DEF STAN 9187NATO Code F-34Jet A, Jet A-1, Avtur

8、Specification D 1655DEF STAN 9191NATO Code F-351.3 The net heat of combustion can also be estimated byTest Method D 1405. Test Method D 1405 requires calculationof one of four equations dependent on the fuel type with theprecision equivalent to that of this test method.1.4 The values stated in accep

9、table metric units are to beregarded as the standard.1.5 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 o

10、f regulatory limitations prior to use.2. Referenced Documents2.1 ASTM Standards:2D 129 Test Method for Sulfur in Petroleum Products (Gen-eral Bomb Method)D 240 Test Method for Heat of Combustion of LiquidHydrocarbon Fuels by Bomb CalorimeterD611 Test Methods for Aniline Point and Mixed AnilinePoint

11、of Petroleum Products and Hydrocarbon SolventsD 910 Specification for Aviation GasolinesD 941 Test Method for Density and Relative Density (Spe-cific Gravity) of Liquids by Lipkin Bicapillary Pycnom-eter3D 1217 Test Method for Density and Relative Density(Specific Gravity) of Liquids by Bingham Pycn

12、ometerD 1250 Guide for Use of the Petroleum MeasurementTablesD 1266 Test Method for Sulfur in Petroleum Products(Lamp Method)1This test method is under the jurisdiction of ASTM Committee D02 onPetroleum Products and Lubricants and is the direct responsibility of SubcommitteeD02.05 on Properties of F

13、uels, Petroleum Coke and Carbon Material.Current edition approved July 1, 2006. Published August 2006. Originallyapproved in 1985. Last previous edition approved in 2001 as D 4529 01.2For referenced ASTM standards, visit the ASTM website, www.astm.org, orcontact ASTM Customer Service at serviceastm.

14、org. For Annual Book of ASTMStandards volume information, refer to the standards Document Summary page onthe ASTM website.3Withdrawn.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.D 1298 Test Method for Density, Relative Density (Sp

15、ecificGravity), or API Gravity of Crude Petroleum and LiquidPetroleum Products by Hydrometer MethodD 1405 Test Method for Estimation of Net Heat of Com-bustion of Aviation FuelsD 1655 Specification for Aviation Turbine FuelsD 2622 Test Method for Sulfur in Petroleum Products byWavelength Dispersive

16、X-ray Fluorescence SpectrometryD 3120 Test Method for Trace Quantities of Sulfur in LightLiquid Petroleum Hydrocarbons by Oxidative Microcou-lometryD 4052 Test Method for Density and Relative Density ofLiquids by Digital Density MeterD 4294 Test Method for Sulfur in Petroleum and PetroleumProducts b

17、y Energy-Dispersive X-ray Fluorescence Spec-trometryD 4809 Test Method for Heat of Combustion of LiquidHydrocarbon Fuels by Bomb Calorimeter (PrecisionMethod)D 5453 Test Method for Determination of Total Sulfur inLight Hydrocarbons, Spark Ignition Engine Fuel, DieselEngine Fuel, and Engine Oil by Ul

18、traviolet FluorescenceD 6227 Specification for Grade 82 Unleaded AviationGasoline2.2 U.S. Military Standards:4MIL-DTL-5624 Aviation Turbine Fuels, Grades JP-4, JP-5,and JP-5/JP-8 STMIL-DTL-83133 Aviation Turbine Fuel, Kerosene Types,NATO F-34 (JP-8), NATO F-35, and JP-8+1002.3 Directorate of Standar

19、dization, Ministry of Defence:5DEF STAN 9186 Aviation Turbine Fuel, High Flash Kero-sene Type with Fuel System Icing InhibitorDEF STAN 9187 Aviation Turbine Fuel, Kerosene Typewith Fuel System Icing InhibitorDEF STAN 9188 Aviation Turbine Fuel, Wide Cut Typewith Fuel System Icing InhibitorDEF STAN 9

20、190 Aviation GasolineDEF STAN 9191 Aviation Turbine Fuel, Kerosene Type,Jet A-12.4 NATO Codes:5F-18 Aviation GasolineF-34 Aviation Turbine Fuel, Grade JP-8F-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 Th

21、e aniline point, density, and sulfur content of thesample are determined by experimental test methods and thenet heat of combustion is calculated using the values obtainedby these test methods based on reported correlations.6,7,84. Significance and Use4.1 This test method is intended for use as a gu

22、ide 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 2).NOTE 2The procedures for the experim

23、ental determination of thegross and net heats of combustion are described in Test Methods D 240and D 4809.4.2 The net heat of combustion is a factor in the perfor-mance of all aviation fuels. Because the exhaust of aircraftengines contains uncondensed water vapors, the energy re-leased by fuel in va

24、porizing water cannot be recovered andmust be subtracted from gross heat of combustion determina-tions to calculate net heat of combustion. For high performanceweight-limited aircraft, the net heat of combustion per unitmass and the mass of fuel loaded determine the total saferange. The proper opera

25、tion of the aircraft engine also requiresa certain minimum net energy of combustion per unit volumeof fuel delivered.4.3 Because the heat of combustion of hydrocarbon fuel-mixtures are slowly varying functions of the physical proper-ties of the mixtures, the heat of combustion of the mixtures canoft

26、en be estimated with adequate accuracy from simple fieldtests of density and aniline point temperature, without theelaborate apparatus needed for calorimetry.4.4 The empirical quadratic equation for the net heat ofcombustion of a sulfur-free fuel was derived by the method ofleast squares from accura

27、te measurements on fuels, most ofwhich conformed to specifications for fuels found in Note 1and were chosen to cover a range of values of properties.Thosefuels not meeting specifications were chosen to extend therange of densities and aniline-point temperatures above andbelow the specification limit

28、s to avoid end effects. The sulfurcorrection was found by a simultaneous least-squares regres-sion analysis of sulfur-containing fuels among those tested.5. Procedure5.1 Determine the aniline point temperature of the sample tothe nearest 0.05C as described in Test Methods D611.5.2 Determine the dens

29、ity at 15C of the sample to thenearest 0.5 kg/m3as described in Test Methods D 941, D 1217,D 1298,orD 4052 or Guide D 1250.4Available from Department of Defense Single Stock Point, 700 Robbins Ave.,Building 4D, Philadelphia, PA 19111-5098.5Available from Directorate of Standardization, Stan Ops 1, R

30、oom 1138,Kentigern House, 65 Brown Street, Glasgow, G2 8EX, U.K.6Armstrong, G. T., Fano, L., Jessup, R. S. Maraatz, S., Mears, T. W., and Walker,J. A., “Net Heat of Combustion and Other Properties of Kerosine and RelatedFuels,” Journal of Chemical and Engineering Data, National Institute for Standar

31、dsand Technology, Washington, DC, Vol 7, No. 1, January 1962, pp. 107117.7Cogliance, J.A., and Jessup, R. S., “Relation Between Net Heat of Combustionand Aniline-Gravity Product of Aircraft Fuels,” ASTM Bulletin, ASTBA. No. 201.October 1954, p. 55 (TP 217); also the National Institute for Standards

32、andTechnology findings as reported by Armstrong, G. T., Jessup, R. S., and Mears, T.W., “Net Heat of Combustion of Aviation Gasoline and its Correlation with OtherProperties,” Journal of Chemical and Engineering Data, Vol 3, 1958, pp. 2028.8Nuttall, R. L., and Armstrong, G. T., “Estimation of Net En

33、thalpies of SomeAviation Fuels Expressed in the International System of Units (SI),” NISTTechnicalNote 937, April 1977.D 4529 01 (2006)25.3 Determine the sulfur content of the sample to the nearest0.02 mass % sulfur as described in Test Methods D 129,D 1266, D 2622, D 3120, D 4294,orD 5453.6. Calcul

34、ation6.1 Calculate the net heat of combustion using either Pro-cedure A or B.6.1.1 Procedure A (By Equation)Insert the measuredvalues in (Eq 1) and calculate Qp, the net heat of combustionat constant pressure on a sulfur-free basis (Note 3).Qp 5 22.9596 2 0.0126587 A1 26 640.9 1/r! 1 32.622 A/r!2 6.

35、69030 3 105A!22 9 217 760 1/r!2(1)where:r = density at 15C, kg/m3,A = aniline point temperature, C, andQp = net heat of combustion on sulfur-free basis, MJ kg1.NOTE 3In SI units the heat of combustion has the unit J kg1, but forpractical purposes a multiple is more convenient. The megajoule perkilog

36、ram (MJ kg1)is106Jkg1and is customarily used for therepresentation of heats of combustion of petroleum fuels, particularly formixtures such as those covered in this international standard.6.1.2 Procedure B (See Table 1)Make a linear interpo-lation between rows bracketing the density and within colum

37、nsbracketing the aniline point of the sample. Then make a linearinterpolation for the aniline point within the row for thecalculated density to obtain Qp.6.2 Calculate the net heat of combustion, Q8p, corrected forsulfur content in accordance with the following equation:Q8p 5 Qp 2 0.1163 S (2)where:

38、S = sulfur content, mass %.6.3 Calculate the volumetric net heat of combustion inaccordance with the following equation:qp5 Qpr31023(3)where:qp= volumetric heat of combustion, MJ L1.7. Report7.1 Report the following information:7.1.1 Report the result for the net heat of combustion in MJkg1to the ne

39、arest 0.001.7.1.2 Report the result for the volumetric net heat ofcombustion qpin MJ L1to the nearest 0.001, if required.8. Precision and Bias98.1 PrecisionThe following criteria shall be used forjudging the acceptability of estimated heat of combustionresults (95 % confidence) when using data on th

40、e aniline pointtemperature, the density, and the sulfur content of a fueldetermined by Test Methods D 611, D 1298, and D 129,respectively (Note 4):8.1.1 RepeatabilityThe difference between two test re-sults, obtained by the same operator with the same apparatus9The precision is based on the conversi

41、on of data in Test Method D 1405 to SIunits and the calculations using this test method.TABLE 1 Net Heat of CombustionFuel, r kg/m33 103Qp, MJ/kgA,C20 30 40 50 60 70 800.6500 42.8522 43.1941 43.5225 43.8376 44.1393 44.4276 44.70260.6600 42.8721 43.2064 43.5272 43.8347 44.1288 44.4095 44.67680.6700 4

42、2.8819 43.2087 43.5222 43.8223 44.1090 44.3824 44.64230.6800 42.8823 43.2020 43.5083 43.8013 44.0808 44.3470 44.59980.6900 42.8743 43.1870 43.4864 43.7723 44.0449 44.3042 44.55000.7000 42.8584 43.1644 43.4570 43.7362 44.0021 44.2545 44.49360.7100 42.8354 43.1348 43.4209 43.6935 43.9528 44.1987 44.43

43、130.7200 42.8059 43.0990 43.3786 43.6449 43.8973 44.1373 44.36350.7300 42.7704 43.0573 43.3307 43.5908 43.8375 44.0708 44.29080.7400 42.7295 43.0103 43.2778 43.5318 43.7725 43.9997 44.21360.7500 42.6837 42.9586 43.2201 43.4683 43.7031 43.9245 44.13250.7600 42.6332 42.9024 43.1582 43.4007 43.6297 43.

44、8454 44.04770.7700 42.5787 42.8423 43.0925 43.3294 43.5529 43.7630 43.95970.7800 42.5203 42.7785 43.0233 43.2547 43.4728 43.6775 43.86870.7900 42.4585 42.7114 42.9509 43.1771 43.3898 43.5892 43.77520.8000 42.3936 42.6413 42.8757 43.0967 43.3043 43.4985 43.67930.8100 42.3258 42.5685 42.7978 43.0138 4

45、3.2163 43.4055 43.58130.8200 42.2555 42.4933 42.7177 42.9287 43.1264 43.3106 43.48150.8300 42.1828 42.4158 42.6354 42.8417 43.0345 43.2140 43.38010.8400 42.1080 42.3363 42.5513 42.7528 42.9410 43.1158 43.27720.8500 42.0313 42.2551 42.4655 42.6624 42.8460 43.0163 43.17310.8600 41.9529 42.1722 42.3781

46、 42.5707 42.7498 42.9156 43.06500.8700 41.8730 42.0879 42.2895 42.4777 42.6524 42.8138 42.96190.8800 41.7917 42.0024 42.1997 42.3836 42.5541 42.7112 42.85500.8900 41.7092 41.9157 42.1085 42.2886 42.4549 42.6079 42.7475D 4529 01 (2006)3under constant operating conditions on identical test material,wo

47、uld in the long run, in the normal and correct operation ofthe test method, exceed the following values only in one casein twenty:Repeatability 0.012 MJ/kg or 5 BTU/lb8.1.2 ReproducibilityThe difference between two singleand independent results obtained by different operators work-ing in different l

48、aboratories on identical test material would, inthe long run, in the normal and correct operation of the testmethod, exceed the following values only in one case intwenty:Reproducibility 0.035 MJ/kg or 14 BTU/lbNOTE 4Use of fuel property data obtained with greater or lesserprecision than that of the

49、 test methods indicated will have a like trend onthe precision of the predicted heat of combustion.NOTE 5As a guide, an estimate of the precision on a volume basiscalculated for a fuel with a density of 810.0 kg/m3is as follows:Repeatability 9.7 MJ/m3Reproducibility 28 MJ/m38.2 BiasNo general statement is made on bias for the testmethod since the data used to determine the correlation cannotbe compared with accepted reference materials.9. Keywords9.1 aviation fuel; gross heat of combustion; heat energy;heat of combustion; heating tests; net