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Chamber pressure

About: Chamber pressure is a research topic. Over the lifetime, 2988 publications have been published within this topic receiving 30725 citations.


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Journal ArticleDOI
TL;DR: In this article, a combined buoyancy and inertia driven vortex flow in an air jet impinging onto a heated circular plate confined in a cylindrical chamber simulating that in a vertical single-wafer rapid thermal processor for semiconductor manufacturing is investigated experimentally by flow visualization.

15 citations

Journal ArticleDOI
TL;DR: In this article, the initial transient leading to stationary conditions in unsteady combustion simulations is investigated by considering flow establishment in model combustors, and the duration of the transient is shown to be dependent on the characteristic turnover time for recirculation zones and the time for the chamber pressure to reach steady conditions.

15 citations

Journal ArticleDOI
20 Aug 2010-Vacuum
TL;DR: In this paper, the nucleation and growth of nanoparticles in the context of a supersonically expanded thermal plasma assisted process, using the Nodal General Dynamic Equations (NGDE) model, was numerically investigated.

15 citations

Journal ArticleDOI
Abstract: Length scales provide some understanding of the injection of cryogenic propellants in rocket chambers on mixing efficiency, which translates to burning efficiency and performance. This project uses supercritical cryogenic nitrogen to look at high-density core flows such as those of coaxial injectors used in rocket engines. The investigation considers test conditions from 4.0 to 6.0 MPa chamber pressure at two injection velocities and temperatures. Experimental data taken by using shadowgraph images provides a means of characterizing turbulent flow structures using a two-point correlation method to determine length scales and structure shapes. The experimental results are compared to computational models.

15 citations

Journal ArticleDOI
TL;DR: In this article, the experimental data are presented showing heat-flux distributions measured calorimetrically with several liquid-propellant rocket thrust-chamber configurations with Enzian-type and axial-stream showerhead propellant injectors.
Abstract: Experimental data are presented showing heat-flux distributions measured calorimetrically with several liquid-propellant rocket thrust-chamber configurations. Thrust levels of the experimental chambers were from 300 to 5000 lb. Enzian-type and axial-stream showerhead propellant injectors were utilized with hydrazine (N2 H4 ) and nitrogen tetroxide (N2 O4 ) propellants. Nozzle-contraction-area ratios of 8 to 1, 4 to 1, and 1.64 to 1 were tested, each having a 5-in. inlet diameter. Characteristic chamber lengths ranged from 16.95 to 62.8 in. The comparison between the experimental heat flux and the analytical heat flux using the method of Bartz [1] was found to be closest in the nozzle-expansion region. The experimental heat-flux measurements ranged between 80 per cent above and 45 per cent below the analytical estimates at the nozzle throat, however. These differences were dependent upon thrust-chamber configuration, injector type, and chamber pressure, and apparently resulted from nonideal combustion and flow characteristics. It is concluded that a priori determination of heat-flux distribution along the thrust-chamber length was possible only to a first approximation for the conditions of these tests.

15 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202322
202257
202167
202086
201991
201882