ASTM D1405-2001(2006) Standard Test Method for Estimation of Net Heat of Combustion of Aviation Fuels《航空燃料消耗的净热量的估算试验方法》.pdf

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1、Designation: D 1405 01 (Reapproved 2006)An American National StandardStandard Test Method forEstimation of Net Heat of Combustion of Aviation Fuels1This standard is issued under the fixed designation D 1405; the number immediately following the designation indicates the year oforiginal adoption or,

2、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.This standard has been approved for use by agencies of the Department of Defense.1. Scope1.1

3、 This test method 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 conve

4、ntional crude oil, which 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 hydrocar-bon fuel from aniline-gravity produc

5、t is justifiable only when the fuelbelongs to a well-defined class for which a relation between heat ofcombustion and aniline-gravity product has been derived from accurateexperimental measurements on representative samples of that class. Evenin this case, the possibility that the estimates may be i

6、n error by largeamounts for individual fuels should be recognized. The classes of fuelsused to establish the correlation presented in this test method arerepresented by the following specifications:Fuel SpecificationAviation gasoline fuels: Specification D 910Grades 80, 82, 100/130, and 115/145 Spec

7、ification 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-44Jet A, Jet A-1, Avtur Specification D 1655DEF STAN 9191NATO Code F-351.3 This test method is not applicable to pure hydroca

8、rbons.It is not intended as a substitute for experimental measurementsof heat of combustion.1.4 The heat of combustion may also be determined in SIunits by Test Method D 4529. Test Method D 4529 requirescalculation of a single equation for all aviation fuels with aprecision equivalent to that of thi

9、s test method.1.5 The values stated in SI units are to be regarded as thestandard, unless otherwise stated (see 1.1).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-priat

10、e safety and health practices and determine the applica-bility of 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 Calori

11、meterD 287 Test Method forAPI Gravity of Crude Petroleum andPetroleum Products (Hydrometer Method)D611 Test Methods for Aniline Point and Mixed AnilinePoint of Petroleum Products and Hydrocarbon SolventsD 910 Specification for Aviation GasolinesD 941 Test Method for Density and Relative Density (Spe

12、-cific Gravity) of Liquids by Lipkin Bicapillary Pycnom-eter3D 1217 Test Method for Density and Relative Density(Specific Gravity) of Liquids by Bingham PycnometerD 1250 Guide for Use of the Petroleum MeasurementTablesD 1266 Test Method for Sulfur in Petroleum Products(Lamp Method)D 1298 Test Method

13、 for Density, Relative Density (SpecificGravity), or API Gravity of Crude Petroleum and LiquidPetroleum Products by Hydrometer MethodD 1655 Specification for Aviation Turbine Fuels1This test method is under the jurisdiction of ASTM Committee D02 onPetroleum Products and Lubricants and is the direct

14、responsibility of SubcommitteeD02.05 on Properties of Fuels, Petroleum Coke and Carbon Material.Current edition approved July 1, 2006. Published July 2006. Originally approvedin 1956. Last previous edition approved in 2001 as D 140501.This test method has been approved by the sponsoring committee an

15、d 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 ASTMStandards volume information, refer to the standards Document Summary page

16、 onthe ASTM website.3Withdrawn.1Copyright ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.D 2622 Test Method for Sulfur in Petroleum Products byWavelength Dispersive X-ray Fluorescence SpectrometryD 3120 Test Method for Trace Quantities of Sulf

17、ur 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 by Energy-Dispersive X-ray Fluorescence Spec-trometryD 4529 Test Method for Est

18、imation of Net Heat of Com-bustion of Aviation FuelsD 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

19、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-T-83133 Aviation Turbine Fuel, Grade JP-82.3 Directorate of Standardization, Ministry of Defence:5DEF STAN 9186 Avi

20、ation 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, Kerosene Type,Jet A-12.4 NATO Codes:5F-18 Aviation Gasoline

21、F-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 aniline point andAPIgravity. These relations, assuming the samp

22、le 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,Grades 100130 and115145Qp net!541.9557 10.00020543 A 3 G! (1)JP-4 Qp net!541.8145 10.00024563 A 3 G! (2)JP-5

23、Qp net!541.6680 10.00024563 A 3 G! (3)Kerosine Jet A or A-1 Qp net!541.6796 10.00025407 A 3 G! (4)where: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 heat of combustion has the dimensions J/kg,but for practical use

24、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 Standard.3.1.2 Where the net heat of combustion is required inin

25、ch-pound units or British Thermal Units (Btu per pound).Type Fuel EquationAviation gasoline,Grades 100130 and115145Qp net!518 037.7 10.0883 A 3 G! (5)JP-4 Qp net!517 977 10.1056 A 3 G! (6)JP-5 Qp net!517 9141 0.1056 A 3 G! (7)Kerosine Jet A or A-1 Qp net!517 919 10.10923 A 3 G! (8)where:Qp(net) = ne

26、t 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 net heat of combustion is required in SIunits (megajoules per kil

27、ogram):Q8 5 Qp net!31 2 0.01S!# 1 0.1016S! (9)where:Q8 = net heat of combustion, MJ/kg, of the samplecontaining S % sulfur,S = 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-

28、pound units or British Thermal Units (Btu per pound):Q8 5 Qp net!31 2 0.01S!# 1 43.7S! (10)where:Q8 = 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 empiri

29、cal linear Eq 1-4 and Eq 5-9 for the estimatednet heat of combustion 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 Sp

30、ecification D 1655, Jet A and A-1.4Available from Department of Defense Single Stock Point, 700 RobbinsAvenue, Building 4D, Philadelphia, PA 191115098.5Available from Directorate of Standardization, Stan Ops I, Room 1138,Kentigern House, 65 Brown Street, Glasgow, G2 8EX, U.K.6Cogliano, J. A., and Je

31、ssup, 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 of Standards andTechnology findings as reported by Armstrong, G. T., Jessup, R. S., and Mears, T.W., “Net Heat

32、of Combustion of Aviation Gasoline and its Correlations with OtherProperties,” Journal of Chemical and Engineering 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

33、Fuels,” Journal of Chemical and Engineering Data, National Institute ofStandards and Technology, Gaithersburg, MD. Vol 7, No. 1, January 1962, pp.107117.D 1405 01 (2006)24. Significance and Use4.1 This test method is intended for use as a guide in caseswhere an experimental determination of heat of

34、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 3The procedure for the experimental determination of the netheat of combustion is described in Test

35、 Methods D 240 and D 4809.5. 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 nearest0.1 API as described in Test Method D 287. Alternatively,determine the relative density by Test M

36、ethods D 941, D 1217,and D 4052 and correct the result to API gravity byGuide 1250.5.3 Determine the sulfur content of the sample to the nearest0.02 % sulfur as described in Test Methods D 129, D 1266,D 2622, D 3120, D 4294,orD 5453 depending upon thevolatility of the sample.6. Calculation6.1 Calcul

37、ate 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 the aniline-gravity products and within col-umns bracketing the sulfur content of the s

38、ample. Use the tableapplicable to the type of product being tested. Thus, use Table1 or Table 5 for Aviation Gasolines, Table 2 or Table 6 for JP-4jet-type fuels; Table 3 or Table 7 for JP-5 jet type fuels, andTable 4 or Table 8 for kerosene-type aviation turbine fuels(Specification D 1655, Jet A or

39、 A-1).6.3 From the values obtained in 6.2, make a linear interpo-lation for the sulfur content within the row for the calculatedaniline gravity constant.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

40、 Value:A 3 G product = 7508By interpolation from Table 2:A 3 G 0 % Sulfur 0.1 % Sulfur 0.2 % Sulfur74007508A760043.63243.659B43.68143.625C43.56543.592B43.614By interpolation from Table 6:A 3 G 0.0 % Sulfur 0.1 % Sulfur 0.2 % Sulfur74007508A760018 75818 769B18 77918 755C18 72918 740B18 750AValue calc

41、ulated from determined values.BFirst step interpolation between rows in columns bracketing the sulfur content.CSecond step interpolation within a row between columns.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 theneare

42、st 0.001 or British thermal units per pound to the nearestinteger as estimated Net Heat of Combustion, D 1405.8. Precision and Bias8.1 RepeatabilityThe difference between successive testresults obtained by the same operator with the apparatus underconstant operating conditions on identical test mate

43、rial (usinga second set of measured values for the aniline point tempera-ture, the relative density, and the sulfur content determined byTest Methods D611, D 1298, and D 129, respectively) wouldTABLE 1 Values of Q* for Aviation Gasolines Calculated from Eq1 and Eq 9Aniline-GravityProductNet Heat of

44、Combustion, MJ/kg0% Sulfur 0.1% Sulfur 0.2% Sulfur 0.3% Sulfur 0.4% Sulfur4 000 42.777 42.745 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

45、 42.884 42.8525 200 43.024 42.991 42.958 42.925 42.8925 400 43.065 43.032 42.999 42.966 42.9335 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

46、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 43.327 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

47、 43.499 43.4658 200 43.640 43.607 43.573 43.540 43.5068 400 43.681 43.648 43.614 43.581 43.5478 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

48、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 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

49、44.147 44.113 44.07911 200 44.257 44.222 44.188 44.154 44.12011 400 44.298 44.263 44.229 44.195 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 44.284D 1405 01 (2006)3in the long run, in the normal and correct operation of the testmethod, exceed the following value only in one case in twenty:Repeatability 5 0.012 MJ/kg or 5 Btu/lb (11)8.2 ReproducibilityThe difference between two single andindependent results obtained by different operators working indiffer