Heat capacity of rocket propellant (RP-1 fuel) at high temperatures and high pressures

被引：14

作者：

Abdulagatov, I. M. ^{[1
]}

Azizov, N. D. ^{[2
]}

机构：

[1] Russian Acad Sci, Dagestan Sci Ctr, Makhachkala, Dagestan, Russia

[2] Azerbaijan State Oil Acad, Baku 370601, Azerbaijan

来源：

FUEL | 2011年 / 90卷 / 02期

关键词：

Vacuum calorimeter; Heat capacity; Rocket propellant (RP-1); Thermal decomposition; THERMOPHYSICAL PROPERTIES; AVIATION;

D O I：

10.1016/j.fuel.2010.09.038

中图分类号：

TE [石油、天然气工业]; TK [能源与动力工程];

学科分类号：

0807 ; 0820 ;

摘要：

Isobaric heat capacity of rocket propellant (RP-1 fuel) has been measured with a vacuum adiabatic calorimeter immersed in a precision liquid thermostat. Measurements were made in the temperature range from 293 to 671 K and at pressures up to 60 MPa. The uncertainty of heat capacity, pressure, and temperature measurements were estimated to be 2-2.5%, 0.05%, and 15 mK, respectively. The measured values of heat capacity were compared with the values calculated from a surrogate mixture model (equation of state, EOS). The average absolute deviation (AAD) between the present data and the values calculated with EOS was 0.81%. (C) 2010 Elsevier Ltd. All rights reserved.

引用

页码：563 / 567

页数：5

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