scholarly journals Flow Analysis of Hybrid Rocket Nozzle Exhaust and its Effects on Launch Pad and Guide Stand

2019 ◽  
Vol 8 (3) ◽  
pp. 7453-7459
Keyword(s):  
High Temperature ◽  
Mach Number ◽  
Computational Analysis ◽  
Flow Analysis ◽  
Flow Characteristics ◽  
Hybrid Rocket ◽  
Ansys Fluent ◽  
Rocket Nozzle ◽  
Time Period ◽  
Very High

The exhaust from the nozzle will be at very high temperature and the high temperature exhausts effect the launch pad and guide stand. In this research, the computational analysis is done on Hybrid Rocket Nozzle Exhaust and Its Effects on Launch Pad and Guide Stand. The flow characteristics such as pressure, temperature, velocity and Mach number at different time period have been studied for various exit geometries using ANSYS Fluent solver. Exhaust speeds vary, depending on the expansion proportion of the nozzle. The rocket nozzle along with guide stand is modelled. The aeroacoustics effects from the nozzle on Launch Pad and Guide Stand have been studied separately using acoustics mode

Design and Analysis of a High Pitch to Chord Ratio Cascade Representative of Ducted Propfans

1991 ◽  
Author(s):  
A. Weber ◽  
W. Steinert ◽  
H. Starken
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Flow Analysis ◽  
High Pitch ◽  
Integral Boundary ◽  
Pressure Loss Coefficient ◽  
Distribution Boundary ◽  
Very High

Efforts to reduce the specific fuel consumption of a modern aero engine focus in particular on increasing the by-pass ratio beyond the current level of around 5. One concept is the counterrotating shrouded propfan operating at low overall pressure ratio and having only very few fan blades of extremely high pitch/chord ratios. The relative inlet Mach numbers cover a range from 0.7 at the hub to 1.1 at the tip section of the first rotor. A propfan cascade was designed by taking into account two characteristic features of a propfan blade-blade section: • a very high pitch/chord ratio of s/c = 2.25 • an inlet Mach number of M1 = 0.90 which leads to transonic flow conditions inside the blade passage In the design process a profile generator and a quasi-3D Euler solver were used iteratively to optimize the profile Mach number distribution. Boundary layer behavior was checked with an integral boundary layer code. The cascade design was verified experimentally in the transonic cascade wind tunnel of DLR at Cologne. The extensive experimental results confirm the design goal of roughly 5 degree flow turning. A total pressure loss coefficient of less than 1.5% was measured at design conditions. This validates the very high efficiency level the propfan concept is calling for. A 2D Navier-Stokes flow analysis code yields good results in comparison to the experimental ones.

Numerical Simulation of Cavitating Flow Over 2D Hydrofoil Using OpenFOAM Adapted for Debian Operating System With LXDE Based in Kernel GNU/Linux

2014 ◽  
Author(s):  
Victor Hugo Hidalgo Diaz ◽  
XianWu Luo ◽  
RenFang Huang ◽  
Edgar Cando
Keyword(s):  
Operating System ◽  
Open Source ◽  
Open Source Software ◽  
Flow Analysis ◽  
Flow Characteristics ◽  
Cavitating Flow ◽  
Cavitating Flows ◽  
Ansys Fluent ◽  
Flow Features ◽  
Free Open Source

Though commercial CFD codes are widely used in flow analysis, but there are free/open source programs which have been applying for computational fluid dynamics. An open source software makes it possible to customize the solver according to the flow features. In the present paper, cavitating flows over 2D NACA66 hydrofoil were simulated based on open source software, where SALOME is used for mesh generation, OpenFOAM for flow solution under Debian GNU/Linux operating system. The results show the simulated cavitating flow characteristics such as cavity revolution, vortex shedding, cavitation induced pressure vibrations, etc. are validated by experiments and results obtained from proprietary software as Ansys Fluent. Thus, the proposed numerical methods based on open source platform are suitable for flow simulations, even for depicting the complicated physics of cavitation.

Numerical Simulation of Rocket Nozzle

2014 ◽  
Vol 984-985 ◽  
pp. 1210-1213
Author(s):  
G. Srinivas ◽  
Srinivasa Rao Potti
Keyword(s):  
Mach Number ◽  
Pressure Ratio ◽  
Divergence Angle ◽  
Performance Parameters ◽  
Ansys Fluent ◽  
Rocket Nozzle ◽  
The Public ◽  
Pressure Distributions ◽  
Fluent Software ◽  
Computational Fluid Dynamics Cfd

The vent or opening is called nozzle. The objectives are to measure the flow rates and pressure distributions within the converging and diverging nozzle under different exit and inlet pressure ratios. Analytic results will be used to contrast the measurements for the pressure and normal shock locations. In this paper computational Fluid Dynamics (CFD) Analysis of various performance parameters like static pressure, the Mach number, intensity of turbulence, the area ratio are studied in detail for a rocket nozzle from Inlet to exit by using Ansys Fluent software. From the public literature survey the geometry co-ordinates are taken. The throat diameter and exit and diameter are same for all nozzles. After the simulation the results revealed that the divergence angle varies the mach number and other performance parameters also varies. For smaller nozzle angle the discharge coefficient increases with increasing pressure ratio until the choked condition is reached for varying the divergence angle.

scholarly journals A Study on the Supersonic Jet Nozzle to Improve of the Operating Efficiency of the Converter Process

2020 ◽  
Vol 58 (8) ◽  
pp. 550-559
Author(s):  
Jae-Hong Kwon ◽  
Ji-A Lee ◽  
Kyeng-Uk Lee ◽  
Jeong-Whan Han
Keyword(s):  
Flow Rate ◽  
Oxygen Supply ◽  
Flow Analysis ◽  
Supersonic Jet ◽  
Flow Characteristics ◽  
Operating Efficiency ◽  
Ansys Fluent ◽  
Inlet Flow Rate ◽  
Nozzle Shape ◽  
Abnormal Expansion

Recently, various worldwide studies have been conducted to improve converter operation by modifying the lance nozzle. In this study, a numerical analysis of the lance nozzle was conducted to improve the dephosphorization efficiency, and to reduce blowing time. The lance nozzle was designed in the form of an abnormal expansion type nozzle capable of increasing the oxygen supply rate. ANSYS FLUENT, a commercial flow analysis program, was used to verify the flow characteristics of the supersonic jet. The nozzle shape was designed according to the ratio of exit diameter to throat diameter, and an analysis was carried out based on the change in inlet flow rate, to confirm the influence of the oxygen supply flow rate. The velocity of the oxygen jet was the fastest for the normal expansion type nozzle and decreased with the abnormal expansion type nozzle. In addition, the oxygen jet velocity tended to increase with the oxygen flow rate.

Design and Numerical Simulation of Convergent Divergent Nozzle

2016 ◽  
Vol 852 ◽  
pp. 617-624
Author(s):  
V. Ramji ◽  
Raju Mukesh ◽  
Inamul Hasan
Keyword(s):  
Mach Number ◽  
Computational Analysis ◽  
Turbulence Modeling ◽  
Pressure Ratio ◽  
Minimum Length ◽  
Ansys Fluent ◽  
Exit Pressure ◽  
Constant Height ◽  
Mach Numbers ◽  
Exit Mach Number

This works centers on the design of a De Laval (convergent - Divergent) nozzle to accelerate the flow to supersonic or hypersonic speeds and computational analysis of the same. An initial design of the nozzle is made from the method of characteristics. The coding was done in Matlab to obtain the contour of the divergent section for seven different exit Mach numbers viz. 2.5,3,3.5,4,4.5,5 and 5.5.To quantify variation in the minimum length of the nozzle divergent section with respect to the exit mach number, a throat of constant height (0.005m) and width (0.05m) was chosen for all the design. The area exit required for each mach no varying from 1 to 5.5 was plotted using isentropic relations and was also used to verify the exit area of the nozzle for each of those mach numbers. An estimate of the exit pressure ratio is obtained by using isentropic and normal shock relations. With this exit pressure ratio, a more refined verification is done by computational analysis using ANSYS Fluent software for a contour nozzle with exit Mach number 5.5. The spalart Allmaras and k-epsilon model were used for turbulence modeling.

Use of LaB6 for a High Quality, Small Energy Spread Beam in an Electron Velocity Spectrometer

1976 ◽  
Vol 34 ◽  
pp. 534-535 ◽  
Author(s):  
P. E. Batson ◽  
C. H. Chen ◽  
J. Silcox
Keyword(s):  
High Temperature ◽  
Energy Resolution ◽  
Electron Velocity ◽  
Electronic Excitations ◽  
Small Energy ◽  
Small Intensity ◽  
Good Energy ◽  
Spectrometer System ◽  
Electron Energy Loss ◽  
Very High

Electron energy loss experiments combined with microscopy have proven to be a valuable tool for the exploration of the structure of electronic excitations in materials. These types of excitations, however, are difficult to measure because of their small intensity. In a usual situation, the filament of the microscope is run at a very high temperature in order to present as much intensity as possible at the specimen. This results in a degradation of the ultimate energy resolution of the instrument due to thermal broadening of the electron beam.We report here observations and measurements on a new LaB filament in a microscope-velocity spectrometer system. We have found that, in general, we may retain a good energy resolution with intensities comparable to or greater than those available with the very high temperature tungsten filament. We have also explored the energy distribution of this filament.

TEM study of boron additions to cobalt aluminide

1988 ◽  
Vol 46 ◽  
pp. 546-547
Author(s):  
Gerald B. Feldewerth
Keyword(s):  
High Temperature ◽  
Turbine Engines ◽  
Major Drawback ◽  
University Of Missouri ◽  
Specific Strength ◽  
Aerospace Applications ◽  
Wide Range ◽  
Ordered Alloys ◽  
The University ◽  
Very High

In recent years an increasing emphasis has been placed on the study of high temperature intermetallic compounds for possible aerospace applications. One group of interest is the B2 aiuminides. This group of intermetaliics has a very high melting temperature, good high temperature, and excellent specific strength. These qualities make it a candidate for applications such as turbine engines. The B2 aiuminides exist over a wide range of compositions and also have a large solubility for third element substitutional additions, which may allow alloying additions to overcome their major drawback, their brittle nature.One B2 aluminide currently being studied is cobalt aluminide. Optical microscopy of CoAl alloys produced at the University of Missouri-Rolla showed a dramatic decrease in the grain size which affects the yield strength and flow stress of long range ordered alloys, and a change in the grain shape with the addition of 0.5 % boron.

WIELAND-K88

Alloy Digest ◽  
2005 ◽  
Vol 54 (12) ◽  
Keyword(s):  
Thermal Conductivity ◽  
Corrosion Resistance ◽  
High Temperature ◽  
Stress Relaxation ◽  
Copper Alloy ◽  
Elevated Temperatures ◽  
Heat Treating ◽  
Relaxation Resistance ◽  
Temperature Performance ◽  
Very High

Abstract Wieland K-88 is a copper alloy with very high electrical and thermal conductivity, good strength, and excellent stress relaxation resistance at elevated temperatures. This datasheet provides information on composition, physical properties, hardness, elasticity, and tensile properties. It also includes information on high temperature performance and corrosion resistance as well as forming, heat treating, machining, joining, and surface treatment. Filing Code: CU-738. Producer or source: Wieland Metals Inc.

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