Natasha Honcharik conducted experiments to determine how different model rocket engine designs affect maximum altitude and flame temperature. She found that engines with higher total impulse reached greater altitudes, and engines with the same impulse but higher average thrust did not necessarily have hotter flames. Specifically, Quest brand engines outperformed Estes brand engines in altitude reached and efficiency of converting fuel energy to thrust rather than heat. Nozzle design differences between brands helped explain performance variations.
Ijri te-03-009 thermal investigation (pressure distribution) on box type cyli...Ijripublishers Ijri
In this project, we chose Optimization method as Optimization by Material. Present most used material for cylinder head
is Cast Iron. We are replacing with different aluminum alloys as their densities are less than that of Cast Iron. Thereby
the weight of the cylinder head reduces when aluminum alloys are used. In this project we are going to vary the materials
LM6, LM24, LM25 different types of aluminum alloys. By varying above materials we are going to find out maximum
optimal convection rate. We are going to conduct thermal analysis as a FEA. By using thermal analysis result we are
going to conduct optimization analysis.
The parametric model is done in CATIA and analysis is done in ANSYS
Ijri te-03-009 thermal investigation (pressure distribution) on box type cyli...Ijripublishers Ijri
In this project, we chose Optimization method as Optimization by Material. Present most used material for cylinder head
is Cast Iron. We are replacing with different aluminum alloys as their densities are less than that of Cast Iron. Thereby
the weight of the cylinder head reduces when aluminum alloys are used. In this project we are going to vary the materials
LM6, LM24, LM25 different types of aluminum alloys. By varying above materials we are going to find out maximum
optimal convection rate. We are going to conduct thermal analysis as a FEA. By using thermal analysis result we are
going to conduct optimization analysis.
The parametric model is done in CATIA and analysis is done in ANSYS
Design and Analysis of Fin-X Technology Nitish Sharma
This document is all about Analysis on Fin-X Technology. Dr. Thomas Povey, an scientist working in Oxford University implemented this idea in Cookwares.
This presentation consists of a definition, different instabilities occur due to supersonic flame, Ignition and flame stabilization techniques, Fuel-air mixing enhancement, and problem.
Design With Solid works Software and Planning Calculation Analysis of Fire Tu...IJRES Journal
Steam boilers (boilers) is a closed vessel made of steel that is used to generate steam. In the modern era many industries such as household scale industries for the manufacture of oyster mushroom spawn to use aid as a supplier of steam boilers are used as a sterilization process baglog. Annually, the number of requests oyster mushroom spawn have been increases, so the boiler is very significant equipment to increase the number of baglog production as oyster mushroom growing media.To help to fulfill the small industryrequiremets for oyster mushroom nursery,plannedatype offire tubeboilerthatcanhelpthe availability ofsteam ina lowscalewithsteamoutputcapacity of70kg/ h, temperature120℃, pressure1.5barandusingmaterialsLPGfuelas a source ofheatenergy.From the results of this design, fire tube boiler have efficiency of 0.934 % . The kettle body is made from asphalt drums pertamina with the Cold Rolled Steel materials. Used asphalt drums because of its availability in the market more easier to obtained easily and the dimensions of asphalt drum capable of holding for temperature and pressure have been determined . As for the pipe material using Carbon Steel Tubing Boilers ASME SA - 178A GRADE A / SA - 214 (Plain Carbon).
Analysis of turbocharger performance for jet assisted vertical takeoff and la...Ijrdt Journal
This paper gives a brief analysis on the performance parameters of a Turbocharger, by fabricating a separate combustion chamber and mocking the working of a jet engine. Parameters such as variation of specific heat, dimensionless flow parameters, variation of turbulence, conductivity, thrust developed etc are studied using simulation of the model, and compared with the actual working of the prototype. It can be conveniently proposed from the experiment that turbocharger can be used effectively for developing vertical take-off assist.
As a part of course on Environments and Energy Materials, this was presented to explain the various areas (materials, manufacturing, testing) of advancement in turbines used for applications such as power generation and jet engines.
Design and Analysis of Fin-X Technology Nitish Sharma
This document is all about Analysis on Fin-X Technology. Dr. Thomas Povey, an scientist working in Oxford University implemented this idea in Cookwares.
This presentation consists of a definition, different instabilities occur due to supersonic flame, Ignition and flame stabilization techniques, Fuel-air mixing enhancement, and problem.
Design With Solid works Software and Planning Calculation Analysis of Fire Tu...IJRES Journal
Steam boilers (boilers) is a closed vessel made of steel that is used to generate steam. In the modern era many industries such as household scale industries for the manufacture of oyster mushroom spawn to use aid as a supplier of steam boilers are used as a sterilization process baglog. Annually, the number of requests oyster mushroom spawn have been increases, so the boiler is very significant equipment to increase the number of baglog production as oyster mushroom growing media.To help to fulfill the small industryrequiremets for oyster mushroom nursery,plannedatype offire tubeboilerthatcanhelpthe availability ofsteam ina lowscalewithsteamoutputcapacity of70kg/ h, temperature120℃, pressure1.5barandusingmaterialsLPGfuelas a source ofheatenergy.From the results of this design, fire tube boiler have efficiency of 0.934 % . The kettle body is made from asphalt drums pertamina with the Cold Rolled Steel materials. Used asphalt drums because of its availability in the market more easier to obtained easily and the dimensions of asphalt drum capable of holding for temperature and pressure have been determined . As for the pipe material using Carbon Steel Tubing Boilers ASME SA - 178A GRADE A / SA - 214 (Plain Carbon).
Analysis of turbocharger performance for jet assisted vertical takeoff and la...Ijrdt Journal
This paper gives a brief analysis on the performance parameters of a Turbocharger, by fabricating a separate combustion chamber and mocking the working of a jet engine. Parameters such as variation of specific heat, dimensionless flow parameters, variation of turbulence, conductivity, thrust developed etc are studied using simulation of the model, and compared with the actual working of the prototype. It can be conveniently proposed from the experiment that turbocharger can be used effectively for developing vertical take-off assist.
As a part of course on Environments and Energy Materials, this was presented to explain the various areas (materials, manufacturing, testing) of advancement in turbines used for applications such as power generation and jet engines.
DiversityMBA 2014 50 Out Front Companies for Diverse & Women ExecutivesChristopher Boulanger
Every year, Diversity MBA Magazine surveys companies to assess their commitment to diverse recruiting and retention. Here are the top companies in 2014's survey.
5 Ecommerce Navigation Enhancements for Customer Experience & SalesChristopher Boulanger
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International Journal of Engineering Research and Applications (IJERA) is a team of researchers not publication services or private publications running the journals for monetary benefits, we are association of scientists and academia who focus only on supporting authors who want to publish their work. The articles published in our journal can be accessed online, all the articles will be archived for real time access.
Our journal system primarily aims to bring out the research talent and the works done by sciaentists, academia, engineers, practitioners, scholars, post graduate students of engineering and science. This journal aims to cover the scientific research in a broader sense and not publishing a niche area of research facilitating researchers from various verticals to publish their papers. It is also aimed to provide a platform for the researchers to publish in a shorter of time, enabling them to continue further All articles published are freely available to scientific researchers in the Government agencies,educators and the general public. We are taking serious efforts to promote our journal across the globe in various ways, we are sure that our journal will act as a scientific platform for all researchers to publish their works online.
Design and experimental analysis of pipe in pipe heat exchangerIJMER
Pipe in pipe heat exchanger are used in industrial process to recover heat between two
process fluids. The project carried out design of pipe in pipe heat exchanger having tube with fin and
without fin. The fins were taken in the form of semi-circular type arranged in altenating way with
spacing of 50mm.The fins were only provided on the inner tube for creating turbulence of cold water.
The number of fin were 18 and its height and thickness 10 and 1.6mm respectively. Experiment were
performed for heat exchanger with fins and without fins. The experiment were performed for different
flow rates of hot and cold fluid Different parameters like Overall heat transfer,Nusselt
number,Convective heat transfer coefficient,Pressure drop,friction factor were obtained and compared
for simple inner tube and finned tube.
The blowoff limits and flashback limits for different diameter to length rati...Jameel Tawfiq
A 129 kWh swirl gas burner was used, where the effect of the burner geometry on the operation window was studied. Using LPG. The length of the burner edge was studied by taking three values of length (5 cm, 10 cm and 15 cm) which represent the ratio (1,2 and 3) to the diameter of the burner respectively. To enhance the combustion stability a swirl vane guide was used to obtain swirl flow and improve the flame structure. The result show that the increase in length of burner neck will decrease the swirl coherent structure and turn the flow to diffusion flow which increase the ability to have boundary layer flashback. However with the limit of burner used, increasing the length of burner neck gives a good result in blowoff side by bush it to leaner limits around ɸ=0.38 but in term of flashback it will bring it to leaner limits too, which is not preferable.. Although, this improvement is linked to the fuel type in first place but the flow structure has a significant impact on flame stability.
Steam Reformer Surveys - Techniques for Optimization of Primary Reformer Oper...Gerard B. Hawkins
Introduction
Background Radiation and Temperature Measurement
Reformer Survey Inputs
Other Troubleshooting Tools
Safety
Preparation
Onsite Data Collection
TWT Survey
Observation/Troubleshooting
Modelling and Analysis
Results/Outputs
Case Studies
Conclusions
Case Study 1
Case Study 2
Case Study 3
Conclusions
International Journal of Engineering Research and Applications (IJERA) is an open access online peer reviewed international journal that publishes research and review articles in the fields of Computer Science, Neural Networks, Electrical Engineering, Software Engineering, Information Technology, Mechanical Engineering, Chemical Engineering, Plastic Engineering, Food Technology, Textile Engineering, Nano Technology & science, Power Electronics, Electronics & Communication Engineering, Computational mathematics, Image processing, Civil Engineering, Structural Engineering, Environmental Engineering, VLSI Testing & Low Power VLSI Design etc.
THERMAL INVESTIGATION ON PROPELANT TANK MATERIAL BY USING FEM APPROACHIjripublishers Ijri
Rocket propellant tanks are pressure vessels where liquid fuels are stored prior to use. They have to store the propellant;
propellant combinations are used in rocket engines where the propellants spontaneously ignite when they come into
contact with each other. The two propellant components usually consist of a fuel (Unsymmetrical dimethyl hydrazine
(UDMH)) and an oxidizer (nitrogen tetroxide (N2O4)).
2. • My name is Natasha Honcharik and I am a Sophomore at
Wachusett Regional High School.
• I started my research in rocketry in September of 2011.
• My experiments were performed at home and in sports fields at
my school.
3. PURPOSE:
• The purpose of this experiment is to find out what factors in a
model rocket engine’s design affect the maximum altitude of the
rocket and the temperature of the engine’s flame.
4. BACKGROUND INFORMATION:
• Engines are designated with a letter and a number. The letter
indicates impulse, or total change in momentum, and the number
indicates average thrust in newtons. “A” engines have a 2.5 newton-
second impulse and “B” engines have a 5.0 newton-second impulse.
• Thrust * burn time = total impulse
• Factors affecting engine performance:
o Type/Amount of propellant
o Nozzle size
o Burn patterns
5. BACKGROUND INFORMATION:
Burn Patterns
Solid fuel only burns on the
surface, called the flame front.
Burn patterns are the way the
flame front changes.
A larger flame front at one
point in time means more fuel
burning at once and more
thrust.
The flame front (shown in
yellow) starts as a cone shape
corresponding with the initial
peak in these example thrust
curves.
6. HYPOTHESIS:
• If a rocket engine with a greater total impulse is used then the
rocket’s apogee (highest point reached) will be higher.
This was justified because impulse is equal to change in momentum. A
greater momentum would mean the rocket would reach a greater velocity
and thus a greater altitude.
• If a rocket engine with the same total impulse but a greater
average thrust is used then the flame will have a higher average
temperature.
This was justified because a higher thrust is caused by a larger flame front
where more fuel is burning at once. Because more fuel was burning at once,
it was hypothesized that the temperature from the flame would be hotter.
7. PROCEDURE (EXPERIMENT # 1):
• Independent variable: type of engine
• Dependent variable: altitude reached
• The rocket was remotely launched and recovered ten times with each of four
engine types (A6, A8, B4, and B6) and altitude data was recorded by an
electronic altimeter inside the rocket.
8. PROCEDURE (EXPERIMENT # 2):
• Independent variable: type of engine used
• Dependent variable: average flame temperature
• The engines were placed upside down in this apparatus and ignited remotely.
The average temperature was measured with a temperature probe.
• Average burn time was measured with a video camera and multiplied by the
average thrust given by the manufacturer to calculate total impulses.
Cylindrical Temperature
hole probe
Ignition
wire
Cement
slabs
9. PROCEDURE (EXTENSION):
• Independent variable: engine type
• Dependent variable: thrust produced
• The same apparatus was used with a force plate replacing the bottom concrete slab.
10. RESULTS (ALTITUDE):
This is a box and whisker graph of the altitude data recorded. Student t -tests
were performed and there was found to be a statistically significant difference
between each group. A8 engines reached the lowest altitude, followed by
A6, B4, and B6.
11. RESULTS (TEMPERATURE):
This is a box and whisker graph of the temperature data recorded.
Student t-tests were performed and there was found to be a statistically
significant difference between each group except between A6 and B6
engines which were also the lowest in temperature overall.
(note: temperature
is relative because
the probe could not
be placed directly
in the flame without
damage, so radiant
heat was
measured.)
12. RESULTS (extension):
This is an example graph of one of
the B4 engine’s thrust curves. Note
the initial spike and then leveling off.
This includes only the propellant
phase of the engine.
This curve was averaged and
multiplied by burn times to calculate
impulses which were found to be
close to but less than the given
impulses. These were then used to
roughly predict altitudes without air
resistance.
13. RESULTS (EXTENSION- PREDICTED ALTITUDE):
In these graphs of impulse and propellant mass vs. altitude, the blue represents the
actual average altitude of each engine type. The red is the predicted altitude without air
resistance using thrust and burn time data from the National Association of Rocketry, and
the green is the same calculated altitude using my measured data. Altitude increases
linearly with impulse and propellant mass, while the altitude without air resistance
increases exponentially because calculations for air resistance involve velocity squared.
14. CONCLUSIONS:
• An engine with a higher impulse does yield a higher altitude.
• However engines with the same impulse ranking do not always reach the same
altitudes because the rankings are maximums, not exact values.
• Temperature was not related to thrust as hypothesized. While both thrust and
temperature are affected by burn patterns and propellant formula, thrust is also
affected by nozzle design, causing it to differ.
15. CONCLUSIONS:
• Quest brand engines (A6 and B6) were more efficient than Estes brand (A8
and B4).
• They reached a higher altitude with approximately the same amount of
propellant.
• Quest engines also had an overall lower temperature. This shows that they
more efficiently converted their fuel’s chemical energy into thrust rather than
thermal energy.
• This may be due to Quest’s greater attention to nozzle design. Quest
engines were found to not only have smaller nozzles, but they also had
different nozzle sizes for different engines whereas Estes brand engines all
had the same size nozzle. Quest is a smaller, lesser known brand, so Estes
mass production might lead to less attention to individual detail and less
efficiency.
16. ACKNOWLEDGEMENTS:
• Thank you to my parents who bought me lots of rocket engines and
supervised my experiments.
• Thanks to Dr. Neil Ault for being my adviser at science seminar.
• Thank you to my physics teacher Mrs. Carol Sullivan for helping me every
step of the way and being the best teacher ever.
• Also thanks to my school, Wachusett, for lending equipment and facilities.
THANK YOU!!