Combustion steady

Much interesting material on this problem is contained in the article by Andreev [15]. Thus, according to his observations, at atmospheric pressure and room temperature nitroglycerin does not yield steady combustion. Steady combustion may be observed at a pressure lowered to 230-380 mm where the boiling temperature decreases to 210-225° C instead of 245° C at 760 mm. 

A steady-state rocket-type combustion spray unit has been developed, called high velocity oxy fuel (HVOF), that creates a steady state, continuous, supersonic spray stream (1.2—3 mm dia) resembling a rocket motor exhaust. The portable device injects and accelerates the particles inside a barrel (rocket nozzle). It produces coating quaHty and particle velocities equal to the D-gun at 5—10 times the spray rate with significantly reduced coating costs. 

Most theories of droplet combustion assume a spherical, symmetrical droplet surrounded by a spherical flame, for which the radii of the droplet and the flame are denoted by and respectively. The flame is supported by the fuel diffusing from the droplet surface and the oxidant from the outside. The heat produced in the combustion zone ensures evaporation of the droplet and consequently the fuel supply. Other assumptions that further restrict the model include (/) the rate of chemical reaction is much higher than the rate of diffusion and hence the reaction is completed in a flame front of infinitesimal thickness (2) the droplet is made up of pure Hquid fuel (J) the composition of the ambient atmosphere far away from the droplet is constant and does not depend on the combustion process (4) combustion occurs under steady-state conditions (5) the surface temperature of the droplet is close or equal to the boiling point of the Hquid and (6) the effects of radiation, thermodiffusion, and radial pressure changes are negligible. 

In addition to supplying transportation fuels and chemicals, products from coal liquefaction and extraction have been used m the past as pitches for binders and feedstocks for cokes [12]. Indeed, the majority of organic chemicals and carbonaceous materials prior to World War II were based on coal technologies. Unfortunately, this technology was supplanted when inexpensive petroleum became available dunng the 1940s. Nevertheless, despite a steady decline of coal use for non-combustion purposes over the past several decades, coal tars still remain an important commodity in North America. 

A major cause of pulsing in flare systems is flow surging in the water seal drum. One of several reasons why it is important to eliminate pulsing is to reduce flare noise. Combustion flare noise has been shown to increase as the steam rate increases. Since the amount of steam required to suppress smoke in a flare is set by the flaring rate, flow surges will require a higher steam rate than for a steady flow. 

The heat supply to the cyclic gas turbine power plant of Fig. 1.2 comes from the control surface Z. Within this second control surface, a steady-flow heating device is supplied with reactants (fuel and air) and it discharges the products of combustion. We may define a second efficiency for the heating device (or boiler) efficiency. 

The first equation may be applied to a control volume CV surrounding a gas turbine power plant, receiving reactants at state Rg = Ro and discharging products at state Py = P4. As for the combustion process, we may subtract the steady flow availability function for the equilibrium product state (Gpo) from each side of Eq. (2.47) to give... 

In the simplified a/s analysis of Section 4.2 we assumed identical and constant specific heats for the two streams. Now we assume semi-perfect gases with specific heats as functions of temperature but we must also allow for the difference in gas properties between the cooling air and the mainstream gas (combustion products). Between entry states (mainstream gas 3g, and cooling air, 2c) and exit state 5m (mixed out), the steady flow energy equation, for the flow through control surfaces (A + B) and C, yields, for a stationary blade row,... 

But if combustion is adiabatic, then the steady flow energy equation for the open-circuit gas turbine (with exhaust of enthalpy (//p)s leaving the HRSG and entering the exhaust stack with a temperature Ts greater than that of the atmosphere. To) is... 

Kuhl, A. L., M. M. Kamel, and A. K. Oppenheim. 1973. Pressure waves generated by steady flames. 14th Symp. (Int.) on Combustion, pp. 1201-1214, The Combustion Institute, Pittsburgh, PA. 

Temperature gradients within the porous catalyst could not be very large, due to the low concentration of combustibles in the exhaust gas. Assuming a concentration of 5% CO, a diffusion coefficient in the porous structure of 0.01 cms/sec, and a thermal conductivity of 4 X 10-4 caI/sec°C cm, one can calculate a Prater temperature of 1.0°C—the maximum possible temperature gradient in the porous structure (107). The simultaneous heat and mass diffusion is not likely to lead to multiple steady states and instability, since the value of the 0 parameter in the Weisz and Hicks theory would be much less than 0.02 (108). 

R.S. Brown et al, AdvanChemEng 7, 1—69 (1968) CA 72, 11368 (1970) The topics reviewed include types of solid proplnts, sohd-proplnt rocket motors, ignition, steady-state combustion, and combustion instability and termination... 

During the third phase, the motor chamber continues to fill with propellant combustion products until the steady-state pressure has been reached. The chamber-pressure transient during this phase is described by... 

The results of the studies.discussed in Section II,C permit calculations to be made of the time required for the flame to spread to the entire propellant surface. Once this phase of the motor-ignition process has been completed, the time required to fill the combustion chamber and establish the steady-state operating conditions must be computed. This can be done by the formal solution of Eq. (7). Because this equation is a Bernoulli type of nonlinear equation, the formal solution becomes... 

Ciepluch (C3) was the first to demonstrate that solid propellants could be extinguished by the rapid venting of gases from the combustion chamber. This was accomplished by suddenly opening a secondary nozzle to achieve the needed venting rate. If the depressurization rate was above a critical value, extinguishment could be achieved if below it, the pressure would seek a new steady state determined by the new chamber ballistics. 

When pressure-decay rates less than critical are employed, the gas-phase combustion zone is removed from the propellant surface and extinguished, but not the ignition from within the condensed phase. Therefore, the temperature of the surface material will be above the autoignition temperature, and steady-state combustion will eventually be initiated. This mechanism is consistent with the observation that the luminosity of the combustion zone can vanish without combustion having been completely terminated. 

In actual fact, both approaches have considerable merit, and it would appear that the two schools are describing the actual physical mechanism from two different points of view. Certainly, a steady-state condition exists in which the rate of heat generation does not exceed the rate of heat loss from the combustion zone. There are also purely dynamic conditions related to the creation of the same imbalance between heat generation and heat loss. These purely static and purely dynamic conditions can be considered as the end points for a whole range of combined static (i.e., minimum-pressure) and dynamic (depressurization) conditions by which termination can be achieved. L -termination is probably one of these intermediate conditions. 

B3. Barrere, M., Williams, F. A., Analytical and Experimental Studies of the Steady State Combustion Mechanism of Solid Propellants, 1965. 

Church s equations, 176-177 Combustion instability, 52-57 bulk-coupled, 56-57 pressure-coupled, 52-55 velocity-coupled, 55-56 steady-state, 29-51 prediction, 30 pressure plateaus, 34 propellants, 31-50 termination, 57-64 depressurization, 58-62 fluid-injection, 63-64 L, 62-63... 

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