Development of Tools for Thermodynamic Calculation of Rocket Engine Characteristics using the Julia Programming Language

2021 ◽  
pp. 80-93
Author(s):  
G.V. Belov
Keyword(s):  
Thermodynamic Properties ◽  
Cross Section ◽  
Process Model ◽  
Gas Flow ◽  
Rocket Engine ◽  
Combustion Products ◽  
Flow Speed ◽  
Critical Cross Section ◽  
Chemical Calculation ◽  
Product Flow

The experience in developing an algorithm and a program for the thermal-chemical calculation of the characteristics of a rocket engine is presented. The program is written in Julia. To calculate the equilibrium composition of combustion products the freely distributed library Ipopt is used. The program is interfaced to the database on thermodynamic properties of individual substances IVTANTERMO. For the convenience of processing, the information on thermodynamic properties is stored in two text files of a special form. The program has been developed using the simplest working process model according to which the flow is one-dimensional, the product flow is adiabatic, there are no friction losses, the product flow is equilibrium, and the speed of condensed particles is equal to the gas flow speed. Ratios for calculating the derivatives of composition, as well as equilibrium values of heat capacity and sound velocity are given. The text of the program can be used in the study process and can easily be adapted to more complex models of the rocket engine workflow. The calculation results obtained using the developed program are in good agreement with the results of TERRA calculations. The execution time of one calculation for a four-element fuel, which includes the determination of the combustion products characteristics in the chamber, the critical cross section and at the nozzle cross section, varies in the range of 3--5 s

Numerical simulations of temperature fields in the uncooled nozzle of a short-range anti-aircraft rocket engine with an insert in the critical section made of various materials

2021 ◽  
Vol 70 (1) ◽  
pp. 15-30
Author(s):  
Mateusz Zieliński ◽  
Piotr Koniorczyk ◽  
Janusz Zmywaczyk ◽  
Marek Preiskorn
Keyword(s):  
Numerical Simulations ◽  
Cross Section ◽  
Heat Flux Density ◽  
Short Range ◽  
Rocket Engine ◽  
Transient Heat Conduction ◽  
Critical Section ◽  
Temperature Fields ◽  
Critical Cross Section ◽  
Calculation Results

Abstract. The paper presents numerical simulations of transient heat conduction in the uncooled nozzle of a short-range anti-aircraft rocket engine. The calculations were made for the configuration of the nozzle with an insert in the critical section made of various materials. The inserts used were: POCO graphite, Al2O3 ceramics, ZrO2-3Y2O3 ceramics. For comparison, numerical simulations of the heat transfer in a nozzle made entirely of St 45 steel, the melting point of which is 1700K, were also carried out. The engine's working time was in the order of 3 s. Numerical simulations were performed using the COMSOL program. The calculation results are given in the form of temperature dependence and heat flux density as a function of time in the critical cross-section. Keywords: non-cooled nozzle, rocket engine, temperature field

A discussion on advanced methods of energy conversion- Magnetohydrodynamic power generation - Wave growth in m .h.d. generators

1967 ◽  
Vol 261 (1123) ◽  
pp. 461-470 ◽  
Keyword(s):  
Thermodynamic Properties ◽  
Acoustic Waves ◽  
Subsonic Flow ◽  
Flow Direction ◽  
Noble Gas ◽  
Travelling Waves ◽  
Combustion Products ◽  
Stationary Waves ◽  
Ohmic Dissipation ◽  
Steady Current

It has been shown that in an m.h.d. generator, acoustic waves can grow due to the coupling of fluctuations in electrical conductivity, Hall parameter and thermodynamic properties of the gas, with the ohmic dissipation and electromagnetic body forces. A new analysis of this phenomenon is presented in which waves travelling at an arbitrary angle to the flow direction in a plane perpendicular to the magnetic field are considered. In contrast to McCune’s (1964) treatment the thermodynamic properties are not restricted to perfect gas laws; and the condition for spatially and temporally growing waves is examined using a general dispersion relation which includes both these types of wave. We consider in detail (i) stationary waves in supersonic flow, and (ii) travelling waves in the subsonic flow found in the G.E.G.B. 200 MW thermal input generator being built at Marchwood, and a possible power station m.h.d. generator. It is found that the waves in the 200 MW rig which burns kerosene in oxygen will be damped. But in an oil-air combustion products generator for Hall parameters of order 3 or greater, it is found that stationary waves which grow rapidly may occur at Mach numbers greater than about 1-7; and in subsonic flow waves propagating antiparallel to the steady current vector may be amplified, though the growth rate is not excessive. In noble gas m.h.d. generators these waves are more unstable than in the oil, air combustion products generator.

scholarly journals Temperature-compensated fiber-optic gas flow speed sensor based on the ‘Hot-wire’ principle

Optik ◽  
2020 ◽  
pp. 166118
Author(s):  
Zhen Li ◽  
Jiqiang Wang ◽  
Xiaoxing Zhong ◽  
Tongyu Liu ◽  
Yanong Ning ◽  
...  
Keyword(s):  
Gas Flow ◽  
Fiber Optic ◽  
Flow Speed ◽  
Hot Wire ◽  
Speed Sensor

scholarly journals Two Efficient Methods for Gas Distributive Network Calculation

2018 ◽  
Author(s):  
Dejan Brkić
Keyword(s):  
Pressure Drop ◽  
Thermodynamic Properties ◽  
Gas Flow ◽  
Flow Distribution ◽  
Gas Pipeline ◽  
Gas Flow Rate ◽  
Closed Loops ◽  
Loop Method ◽  
Hardy Cross ◽  
Flow Through

Today, two very efficient methods for calculation of flow distribution per branches of a looped gas pipeline are available. Most common is improved Hardy Cross method, while the second one is so-called unified node-loop method. For gas pipeline, gas flow rate through a pipe can be determined using Colebrook equation modified by AGA (American Gas Association) for calculation of friction factor accompanied with Darcy-Weisbach equation for pressure drop and second approach is using Renouard equation adopted for gas pipeline calculation. For the development of Renouard equation for gas pipelines some additional thermodynamic properties are involved in comparisons with Colebrook and Darcy-Weisbach model. These differences will be explained. Both equations, the Colebrook’s (accompanied with Darcy-Weisbach scheme) and Renouard’s will be used for calculation of flow through the pipes of one gas pipeline with eight closed loops which are formed by pipes. Consequently four different cases will be examined because the network is calculated using improved Hardy Cross method and unified node-loop method. Some remarks on optimization in this area of engineering also will be mentioned.

Effect of Precursor Supply on (100) and (001) Orientations of α-Al2O3 Film Prepared by Laser CVD

2012 ◽  
Vol 508 ◽  
pp. 3-6 ◽  
Author(s):  
Kadokura Hokuto ◽  
Akihiko Ito ◽  
Teiichi Kimura ◽  
Takashi Goto
Keyword(s):  
Cross Section ◽  
Vapor Deposition ◽  
Gas Flow ◽  
Chemical Vapor ◽  
Gas Flow Rate ◽  
Laser Chemical Vapor Deposition ◽  
Evaporation Temperature ◽  
Oxygen Gas ◽  
Laser Cvd ◽  
Precursor Supply

Α-Al2O3 Films Were Prepared by Laser Chemical Vapor Deposition and the Effects of Precursor Evaporation Temperature (Tvap) and Oxygen Gas Flow Rate (FRo) on Phase and Orientation of Al2o3 Films Were Investigated. at Tvap = 413 K, (100)-Oriented α-Al2O3 and θ-Al2O3 Were Codeposited. the Amount of θ-Al2O3 Increased with Increasing FRo. at Tvap = 433–443 K, α-Al2O3 Films Showed a (001) Orientation. (100)- and (001)-Oriented α-Al2O3 Films Had a Rectangular- and Hexagonal-Shaped Grains, Respectively, and Showed a Columnar in Cross Section. Grain Size of (100)- and (001)-Oriented α-Al2O3 Films Decreased from 10 to 2 μm with Increasing FRo from 0.085 to 0.85 Pa m3 s−1. Deposition Rate Increased from 100 to 300 μm h−1 with Increasing Tvap from 413 to 443 K.

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