Combustion chamber pressurization

When the gas injection nozzle is in an unchoked condition, the pressure in the gas generator is equal to the combustion chamber pressure, i. e., pg = p The gas generation rate is determined by the pressure in the combustion chamber. When the gas injection nozzle is in a choked condition, the burning rate is determined by the gas injection nozzle area, A g, and then the pressure in the gas generator, pg, is determined by... 

Specific impulse, calculated by this technique, represents a 100% conversion of chemical energy to mechanical energy, and, therefore, is an upper limit to the performance available from a real rocket engine. However, regardless of the technique utilized, the theoretical Is of each of the systems are compared on a common basis (e.g.y at the same combustion chamber pressure, nozzle geometry, exit pressure, etc.) with the desired performance level dictated by the mission and engine system rquirements. 

Aleshin et al, Calculation of the Thermodynamic Characteristics of Hydroreacting Aluminum-Water Fuels , Fiz AerdispersnykhSist 17,74—78 (1978) CA 91,76312 (1979) [Reported are the thermodynamic calcns made for the hydroreacting Al-w mixt used as a rocket fuel at a combustion chamber pressure of 40kg/sq cm]... 

I noticed, with sinking heart, that the combustion chamber pressure was steadily rising. It rose from 2 to 12 psig, at which point the fuel gas tripped off as a result of the high pressure. The sulfur plant start-up was aborted But what had happened ... 

The relation between nozzle area ratio and pressure ratios for various combustion chamber pressures, Pc. Equilibrium hydrogen, Tc = 3000°K, equilibrium expansion, vacuum ambient conditions. 130... 

The programme EXPL05 was used to calculate the rocket propellant parameters for this compound in combination with ADN as the oxidizer while presuming a combustion chamber pressure of 45 bar (Tab. 4.11). 

Effect of ducting pressure drop and combustion chamber pressure drop... 

Effect of Ducting Pressure Drop and Combustion Chamber Pressure Drop... 

In an age of rockets and space travel, there is a constant demand for new and stronger propellants. These are classified into cryogenics and storable liquids and characterized by the specific impulse ( /J which is the thrust per unit mass flow of fuel and by convention reported in units of seconds (see Table 14.5). The thrust depends on the combustion temperature and the exhaust and combustion chamber pressures, Pe and Pc, respectively. 

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