SU1616952A1 - Method of producing aircraft fuel - Google Patents

Abstract

The invention relates to the production of fuels, in particular the production of aviation fuels, which can be used in oil refining. In order to increase the yield and quality of the target product, a step separation with interstage heating of the liquid flows is carried out using a wide fraction of light hydrocarbons as a raw material with obtaining gas and liquid flows at each step. In this case, the gas flows of the third and fourth stages are combined, cooled and plunged into additional separation to produce liquid and gas flows and mixing the liquid with the liquid flow from the second separation stage, and the gas flow is mixed with the first and second gas flows, followed by expansion in a turboexpander and by feeding this cold gas stream to cool the combined third and fourth stage gas stream before it is further separated. Under these conditions, stabilization occurs with increasing temperature and constant pressure (at a known constant temperature and decreasing pressure), which allows for more intensive removal of light hydrocarbons (methane, ethane and partially propane) from the liquid phase. The resulting fuel meets the requirements of Spec. 39-1215-87 for saturated vapor pressure and is obtained in a better yield (up to 70%). 1 dw., 4 tab.

Description

The invention relates to a method for producing aviation fuel from a wide fraction of hydrocarbons and can be used in the oil refining industry.

The purpose of the invention is to improve the quality of the target product and increase its yield.

The drawing shows a schematic flow diagram of the method.

The wide fraction of hydrocarbons through the heat exchanger 1 is directed to the first stage of the battery stabilizer 2. The separated liquid by pump 3 through the heat exchanger 4 is directed to the second stage of the battery stabilizer 5 o The separated liquid by the pump 6 through the heat exchanger 7 is directed to the third stage of the battery stabilizer 8, from where pump 9 through the heat exchanger 10, the liquid is sent to the last about the fourth stage of the battery stabilizer 11, from which the condensed aviation fuel is released.

The gas evolved in the first and second stages of the battery stabilizer is directed to the common collector, expanding it, with external work done in the expander 12, and the mixture of gas from the Third and Fourth Stables of the Mogo batteries is cooled with a cold gas stream. 5zator in the heat sink | 3. iviee. This mixture of Gs13ov is cooled) by heat exchangers 4 and 1 and directing jpT to the separator 14, from which liquid 15 is pumped to the inlet of the compressor by the heat exchanger 7 of the third step- and battery stabilizer, and the gas from the separator is mixed with the gas and the second stage of stabilization. The cooled gas stream after the expander 12 and the heat exchanger 13 is compressed in the compressor 16,

Example. A wide fraction of hydrocarbons (. Grade A) of the following hydrocarbon composition, wt.%:

the amount of hydrocarbons

SNF and GjH g fie more than 3

hydrocarbons

SzI (

amount of carbon deposits

 5 12 hydrocarbons

At least 15

Not less than 45

 higher 1

Not more than 11 kg is heated from

in quantity

| -14 to O C and treated in the first stage of the battery stabilization jropa, whereby 0.014 kg of gas is separated, and the liquid in the amount of 0.986 kg is heated to 25 ° C and sent to the second stabilization stage, in which 0.0516 kg Gas, separated liquid in the amount of 0.9344 kg with a broad fraction of hydrocarbons from the gas separator in the amount of 0.3917 kg. The resulting mixture in the amount of 1.3261 kg is heated to and added to the third stabilization stage, where 0.331 kg of gas is decanted, and 0.9951 kg of liquid is then reheated to 45 ° C and in the last stage after separation of the gas, the condensed aviation is obtained. fuel in the amount of 0.6474 kg, and the gas that was added in the fourth stabilization stage in the amount of 0.2608 kg is combined with the third stabilization gas and in the amount of 0.5915 kg is sent to a heat exchanger in which the gas is cooled to 20 ° C Separated, separating 0.3917 kg of liquid, which is then

0

five

0

five

0

five

0

five

after the second stabilization stage, the liquid from the separator in the amount of 0.1970 kg is combined with the first and second gas, expanded in the expander from 0 to 45 MPa, while cooling to a temperature of 18 Cs. This gas cools the total the gas flow in the heat exchanger is then compressed to a pressure of 0.3 1 ° C, with which the gas is directed to the output of the main compressor stations.

The results are summarized in tabl1-3, the quality of the obtained fuel is given in Table 4.

It follows from these tables that carrying out the stabilization process with increasing temperature at constant pressure as compared with the known method, in which the process proceeds at constant temperature with decreasing pressure, contributes to a more intensive removal of light hydrocarbons (methane, ethane and partially propane) from the liquid phase The obtained fuel meets the requirements for pressure of suspended vapors.

In addition, cooling, partial condensation of gas mixtures of the III and IV stages of separation and return of the condensed part to the liquid line before step III means that the most heavy part of the specified mixture re-stabilizes that. leads to an increase in the yield of the finished product in relation to the original NGL up to 70 wt%.

formula of invention

The method of obtaining a: navigation fuel, including the step separation of a broad fraction of light hydrocarbons to produce gas and liquid flows at each stage, so that, in order to improve the quality and yield of the target product, the separation conducts with interstage heating of the fluid flows, the third and fourth gas flows, the separation steps are combined, cooled, subjected to additional separation to obtain gas and liquid flows, the latter is mixed with the second separation liquid flow, and mixed with gas flows of the first and second stages, expanded into turbo-extensions of half an hour516169526

Hbni cold gas streaming gas of the third and fourth stages

to cool the combined stream

before its additional separation

before additional separation,

table 2

ashod of the original mixture, 1 kg per 1 kg

leave, may. shares of nitrogen methane

carbon dioxide ethane propane isobutane n-butane isopentane n-pentane hexane heptane octane nonane

Average molar mass, kg / kmol

one

0,000113 0,007510 0,000457 0.021686 0.214598 0.113117 0.285801 0.116694 0.146483 0.056832 0.016451 0.022931 0.007327

56,894

cha

Not more than 0.03 0.26 0.5

Not less than 645 Not more than 650 Not less than 585 Not more than 595

45144

-ten

Table 3

0,6974

0.000008 0.000004 0.001517 0.104567 0.109215 0.315836 0.150270 0.192086 0.076627 0.022325 0.017575 0.009970

3.192

0.3026

0,000426 0.028232 0.001709 0.077391 0.518496 0.123894 0.202846 0.023965 0.020533 0.002167 0.000220 0.000095 0.000026

44,082

Table 4

0.0279

0.254

0.498

649

585

48964

-9.7

HoMSffmop

Heat carrier

-i

Claims (1)

Claim A method of producing aviation fuel, including stepwise separation of a wide fraction of light hydrocarbons with obtaining gas and liquid flows at each stage, which differs in that, in order to improve the quality and yield of the target product, the separation is carried out with interstage heating of the liquid flows gas flows of the third and fourth stages of separation are combined, cooled, subjected to additional separation to obtain gas and liquid flows, the latter is mixed with the liquid stream of the second separation stage, and the mixing stream gas flows out with the first and second stages, expanded in a turboexpander and the cold gas poluchen5 ny gas stream is directed third and fourth steps of cooling the combined stream prior to its further separation Table 1 Parameters First stage fluid Gas from the first stage Second stage fluid Gas from the second stage Entrance to the third step Third Stage IE Gas from the third stage .Pressure, MPa 0.5 0.5 0.5 0.5 0.5 0.5 0.5 Temperature ° C 0 0 20 20 35 35 35 The flow rate of the initial mixture, ί kg per 1 kg 0.9860 ο, οι4ο 0.9344 0,0516 0.3261 0,9951 0.3310 Composition, ma.doli Azo! · 0.000032 0.005857 0.000004 0,000536 0.000002 __ 0.000010 Methane 0,004398 0.226787 0,001331 0,059905 0,000996 0.000090 0,003715 Carbon dioxide 0,000363 0,007080 0,000183 0,003614 0.000147 0.000026 0,000510 Ethane 0.019923 0.146128 0.014623 0.115853 0.013536 0,004789 0,039813 Propane 0.212283 0.377074 0,199016 0.452563 0.229962 0.162750 0.431885 Out shod 0.113659 0,074902 0.113993 0.107629 0.127520 0.121979 0.144173 n-butane 0.188080 0.125274 0.293397 0.191819 0.311138 0.32419 0.277240 Isopentane 0.118096 0.018094 0.122826 0,032467 0.109867 0.130188 0,048799 n-pentane 0.148329 0.016649 0.154814 0,030895 0,132323 0,160908 0.046422 Hexane 0.057613 0,001931 0,060566 0.004141 0,046256 0,059530 0,006429 Heptane 0.016681 0.000169 0.017579 0,000410 0.012788 0.016818 0,000682 Octane 0.013112 0,000047 0.013827 0.000143 0,009906 0.013114 0,000268 Nonan 0,007431 0.000008 0,007841 0.000025 0,005559 0.007389 0.000054 The average molar mass, kg / kmol 57.559. 31.373 58.305 41.600 57.373 60.355 49.955 table 2 Gas from the fourth Gas mixture Liquid Gas from Parameters steps third and from sep— separately fourth rator 14 ra 14 steps Pressure, MPa Temperature, ° C Consumption of the initial mixture ·, 1 kg per 0.5 45 0.5 39 0.5 20 0.45 20 1 kg 0.2608. 0.5915 0.3917 0.1970 Composition, May „shares nitrogen - 0.000007 - 0,000021 methane 0,000322 0,002317 0.000198 0.007105 carbonic gas 0.000086 0,000336 0,000059 0,000961 ethane 0.014005 0,029276 0,010949 0,070722 propane 0.326708 0.385142 0.303589 0.569532 isobutane 0.157946 0.149258 0.159731 0.125578 n-butane 0,340967 0.304512 0.353379 0.194020 isopentane 0,073597 . 0,060212 0,079013 0.017704 n-pentane 0,073049 0.058775 0,078711 0.013564 hexane 0.011353 0,008718 0.012240 0,000757 heptane 0.001304 0,000970 0,001385 0.000030 .octane 0,000546 0,000395 0,000567 0.000006 nonan 0.000117 0,000082 0.000118 - Average molar weight kg / kmol 53,576 51,459 54,228 46.132 Table 3 Parameters ShFLU Aviation fuel Gas stabilization at the exit of the installation Pressure, MPa 0.55 0.45 0.3 Temperature ° C -14.2 • 45 60 Original consumption mixture, 1 kg per 1 kg 1 0.6974 0.3026 Composition, May. share nitrogen 0.000113 - 0,000426 methane 0,007510 0.000008 0,028232 carbon dioxide 0,000457 0.000004 0.001709 ethane '0.021686 0,001517 0,077391 propane 0.214598 0,104567 0,518496 isobutane 0,113117 0,109215 0.123894 n-butane 0.285801 0.315836 0.202846 isopentane 0,116694 0,150270 0,023965 n-pentane 0.146483 0.192086 0,020533 hexane 0.056832 0,076627 0.002167 heptane 0.016451 0,022325 0,000220 octane 0.012931 0.017575 0,000095 nonan 0,007327 0,009970 0.000026 Average molar weight kg / kmol 56,894 63,192 44,082 Table 4 Way Indicator Famous Proposed Saturated steam pressure, MPa, at, ° C No more -4.0 0,03 . 0,0279 20 0.26 0.254 45 0.5 0.498 Density, kg / m ⁵ , at, ⁰ С -40 Not less than 645 No more than 650 649 20 Not less than 585 No more than 595 585 Heat of combustion lower net kJ / kg, not- her 45144 48964 Start temperature la no boiling lower, ⁰ C -10 -9.7 Collector