Abstract
Rockets with combustion chamber would reach 3500K to 3700K. For efficiency reasons and safe design of ejectors, after-cooler is interposed between the diffuser and ejector. This process is also operated at fairly high pressure 10 to 200 bar. Due to high temperature and pressure, thermal shocks generated are prevented by spraying water particles uniformly inside the gas cooler. In this paper, the significance of water spray characteristics is studied thoroughly. The water droplet evaporated into a flow of exhaust gases with a droplet size of 15 microns diameter increases the total surface area and is about 400 m2 . The spray cooler length is suggested as 7-9 m to reduce the component of unevaporated water for optimum mass flow rate of primary fluid. Water injection velocity and pressure are varied as using number of nozzles. The injection pressure is reduced 10 times (2.0 - 2.5 bar) by increasing the number of nozzles (about 2000) in quadruple. Keywords: Combustion chamber, Rocket, Injection pressure, Water spray
Highlights
A typical High Altitude Test facility primarily consists of droplets and water evaporates from the surface of the a vacuum chamber for testing large area ratio rocket drop and diffuses into the hot gas (Habib, 1973)
The large area ratio rocket motor converts the stored gases flow into the droplet, the heat and mass pressure energy of the fluid in to a high kinetic energy transfer are in the same direction towards the droplet
The unused water droplets along system through a series of oblique shocks, which with the condensed mass are removed through terminate with a normal shock
Summary
A typical High Altitude Test facility primarily consists of droplets and water evaporates from the surface of the a vacuum chamber for testing large area ratio rocket drop and diffuses into the hot gas (Habib, 1973). The unused water droplets along system through a series of oblique shocks, which with the condensed mass are removed through terminate with a normal shock. Evaporation of water particles depends process, the static temperature of the exhaust gas on various factors like droplet size, length of the gas increases across the normal shock close to the cooler, distribution of water mass, injection velocity, state stagnation temperature of the rocket motor. Spray coolers exhaust gases decreases drastically for a defined find extensive application in high altitude test facility for cooling high temperature rocket exhaust gases and to
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