Ejectors are known to be beneficial to vapor compression cycle performance as they can recover the kinetic energy released during the expansion instead of dissipating it in a throttling process. It is desirable to introduce an adjustable feature to the ejector so that ejector cycle performance can be optimized under different working conditions, which could make ejector technology more suitable...

Abstract This paper studies the influence of nozzle structure and process parameters on solid propellant 3D printing process, so as to better guide optimization improvement, realize continuous extrusion molding propellant. Four characteristic such diameter, shrinkage angle, temperature, wall slip coefficient are selected, these four speed pressure slurry in is discussed by using orthogonal test...

The sewage diffusion effect under deep water was carried out between different diffuser design parameters based on the hydraulic model test. According to test of length, riser spacing, number, nozzle horizontal azimuth angle and jet angle, specific need be determined comprehensively considering surface field, degree, project cost, etc. We used a coastal marine disposal in China as an example. a...

In this paper, the authors investigated the various factors, which can affect the performance of a turbofan engine. For this, the various subunits of a turbofan engine like inlet duct, compressor, combustion chamber, liner, turbine, exhaust nozzle etc. are investigated to find its various reliability characteristics through Markov process and supplementary variable technique (SVT). The main adv...

We establish the existence and stability of multidimensional transonic flows with transonic shocks through an infinite nozzle of arbitrary cross-sections, including a slowly varying de Lavel nozzle. The transonic flow is governed by the inviscid steady potential flow equation with supersonic upstream flow at the entrance, uniform subsonic downstream flow at the infinite exit, and the slip bound...

A three-Dimensional computational model is used to simulate flow in a non-axisymmetric, convergent-divergent nozzle incorporating porous cavities for shockboundary layer interaction control. The nozzle has an expansion ratio (exit area/throat area) of 1.797 and a design nozzle pressure ratio of 8.78. Flow fields for the baseline nozzle (no porosity) and for the nozzle with porous surfaces of 10...

Fuel after inflaming burns at high (till 15-20 МПа and more) pressure, thus is formed gaseous combustion products with temperature 3000-4500 K, which effuse to the ambient space through the nozzle. On length of the nozzle the temperature and pressure of them decrease, and the velocity increases, passing through a sound velocity in minimum (critical) cross-section of the nozzle and reaching 2700...

The compressible jet plume emerging from a planar convergent–divergent nozzle containing a separation shock is investigated experimentally and numerically. The investigation encompasses exit-to-throat area ratios (Ae=At) from 1.0 to 1.8 and nozzle pressure ratios from 1.2 to 1.8. Experiments were conducted in a variable-geometry nozzle facility, and computations solved the Reynolds-averaged Nav...

A theoretical study analyzing three-dimensional combustion acoustic instabilities in a liquid propellant rocket engine combustor has been conducted. A linear theory based on Crocco’s pressure sensitive time lag model is used. To apply this theory the combustor is divided into two main components, including the combustion chamber and the converging part of the nozzle. The assumption of concentra...