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A Dynamic Simulation-Based Feasibility Assessment Of High-Pressure, Direct Injection Of Hydrogen In Slow-Speed Marine Diesel Engines, Gurupraad Shetty 2022 World Maritime University

A Dynamic Simulation-Based Feasibility Assessment Of High-Pressure, Direct Injection Of Hydrogen In Slow-Speed Marine Diesel Engines, Gurupraad Shetty

World Maritime University Dissertations

No abstract provided.


A Comparative Performance Analysis Of The Novel Turboaux Engine With A Turbojet Engine, And A Low-Bypass Ratio Turbofan Engine With An Afterburner, Kaleab Fetahi, Sharanabasaweshwara A. Asundi, Arthur C. Taylor 2022 Old Dominion University

A Comparative Performance Analysis Of The Novel Turboaux Engine With A Turbojet Engine, And A Low-Bypass Ratio Turbofan Engine With An Afterburner, Kaleab Fetahi, Sharanabasaweshwara A. Asundi, Arthur C. Taylor

Mechanical & Aerospace Engineering Faculty Publications

Presented herein is a comparative performance analysis of a novel turbofan engine with an auxiliary combustion chamber, nicknamed the TurboAux engine, against a turbojet engine, and a low bypass ratio turbofan engine with an afterburner is presented. The TurboAux engine is an adaption of the low-bypass ratio turbofan engine, but with secondary combustion in an auxiliary bypass annular combustion chamber for thrust augmentation. The TurboAux engine is envisioned with the desire to facilitate clean secondary burning of fuel at temperatures higher than in the main combustion chamber with air exiting the low-pressure compressor. The comparative study starts by analyzing the ...


Controller Platform Design And Demonstration For An Electric Aircraft Propulsion Driv, Rosten Sweeting 2022 University of Arkansas, Fayetteville

Controller Platform Design And Demonstration For An Electric Aircraft Propulsion Driv, Rosten Sweeting

Graduate Theses and Dissertations

With the growth in the aerospace industry there has been a trend to optimize the performance of an aircraft by reducing fuel consumption and operational cost. Recent advancements in the field of power electronics have pushed towards the concepts of hybrid electric aircraft also known as more electrical aircrafts. In this work, a custom controller board for an electric aircraft propulsion drive was designed to drive a permanent magnet synchronous motor. Design of the controller board required knowledge of the topology selection and power module selections. Simulations of the system were performed using MATLAB/Simulink to analyze the overall performance ...


Film Cooling In Gas Turbine And Nozzle, Manideep Uduta Engineer-Graduate Aerospace, Vaibhav Naiknavre Engineer-Graduate Aerospace 2022 Sandip University, Maharashtra, Nashik, INDIA

Film Cooling In Gas Turbine And Nozzle, Manideep Uduta Engineer-Graduate Aerospace, Vaibhav Naiknavre Engineer-Graduate Aerospace

Graduate Research in Engineering and Technology (GRET)

A gas turbine is a rotating engine that generates its power through the flow of combustion gases. With either an axial or centrifugal compressor, air from the surrounding environment is drawn into the engine intake, where it is compressed and heated before being sent to combustion chamber. Every gas turbine engine has a nozzle as a standard part. Among its many responsibilities include propelling the engine forward, returning exhaust gases to the free stream, and regulating mass flow through the engine. When the power turbine's exhaust exits, the nozzle is directly in the direction of the fumes. Simply put ...


Experimental And Computational Investigation Of Divergent Thrust Losses In Rocket Nozzles, Vaibhav Arya Graduate Engineer, Anushka Sunil Kapse Post Graduate Student 2022 Sandip University, MH, INDIA

Experimental And Computational Investigation Of Divergent Thrust Losses In Rocket Nozzles, Vaibhav Arya Graduate Engineer, Anushka Sunil Kapse Post Graduate Student

Graduate Research in Engineering and Technology (GRET)

The nozzle is a critical component of any rocket engine because it transforms high pressure and high temperature (with sluggish net velocity) within the combustion chamber into high velocity but low pressure. Individually, the molecules in the mixed propellants have rapid velocity in the combustion chamber, but directions are randomly pointing in all directions. A convergent-divergent nozzle, also known as a CD nozzle, is fashioned like a tube with two bulging ends and a thin part in the center. This structure/design provides the nozzle with a balanced shape. By turning the flow's heat energy into kinetic energy, the ...


A Study On Concepts De-Laval Nozzle Using Cfd Tool, Krishna Yadav Graduate Engineer, Digambar Daware Mr., Vedant Akolkar, Pallavi Padalwar 2022 Department of Aerospace Engineering Sandip University

A Study On Concepts De-Laval Nozzle Using Cfd Tool, Krishna Yadav Graduate Engineer, Digambar Daware Mr., Vedant Akolkar, Pallavi Padalwar

Graduate Research in Engineering and Technology (GRET)

A device that is used to control the characteristics of fluid is known as a nozzle. Its primary function is to increase the fluid's rate of motion. A traditional De-Laval nozzle will have three distinct parts: a throat, a converging section, and a diverging part. This paper will attempt to detail the bulk of the nozzle concepts developed by De Laval. This paper provides a comprehensive analysis of the nozzle's operational philosophy. In addition, theoretical flow analysis is carried out at a number of locations along the length of the nozzle. The dynamic changes in flow parameters such ...


Two Dimensional Cfd Analysis On Different Rocket Nozzles, Yogesh Bhawarker Mr., Digambar Daware Mr., Krishna Yadav, Vedant Akolkar, Pallavi Padalwar, Prakash Katdare 2022 Department of Aerospace Engineering, Sandip University, SOET, NASHIK, MH

Two Dimensional Cfd Analysis On Different Rocket Nozzles, Yogesh Bhawarker Mr., Digambar Daware Mr., Krishna Yadav, Vedant Akolkar, Pallavi Padalwar, Prakash Katdare

Graduate Research in Engineering and Technology (GRET)

The reduction of Earth-to-orbit launch costs in conjunction with an increase in launcher reliability and operational Efficiency is the key demands on future space transportation systems, like single-stage-to-orbit vehicles (SSTO). The realization of these vehicles strongly depends on the performance of the engines, which should deliver high performance with low system complexity. Performance data for rocket engines are practically always lower than the theoretically attainable values because of imperfections in the mixing, combustion, and expansion of the propellants. The main part of the project addresses different nozzle concepts with improvements in performance as compared to conventional nozzles achieved by Different ...


Cfd Analysis Of Nozzle Flow With Sudden Expansion In Aerospace Engineering, Yogesh Bhawarker Mr., Ritik Patidar, Prakash Katdare 2022 Department of Aerospace Engineering, Sandip University, SOET, NASHIK, MH

Cfd Analysis Of Nozzle Flow With Sudden Expansion In Aerospace Engineering, Yogesh Bhawarker Mr., Ritik Patidar, Prakash Katdare

Graduate Research in Engineering and Technology (GRET)

As the need for missiles and rockets has increased exponentially, the challenges associated with the gas dynamics of these vehicles continues to be a concern. The pressure in the downstream is sub atmospheric whenever there is a sudden expansion. This low pressure in the recirculation zone causes significant drag, accounting for almost two-thirds of the net drag of the aerospace vehicles. Hence, the purpose of this paper is to deliver a Computational Fluid Dynamic (CFD) analysis of the impact geometry and flow parameters have on the thrust force generated by the flow from convergent divergent nozzles to a suddenly expanded ...


Hybrid Rocket Propulsion Development And Application, AKSHAY GHARAT Assistant Professor, VINAYAK HASTAK Graduate Engineer 2022 SOET, Sandip University, MH, INDIA

Hybrid Rocket Propulsion Development And Application, Akshay Gharat Assistant Professor, Vinayak Hastak Graduate Engineer

Graduate Research in Engineering and Technology (GRET)

Satellite technology is advancing. Satellite propulsion requires several desired rocket properties. This is necessary for 1 kg of payload. Launch vehicles no longer need rocket engines. Application includes satellite movement, orbit transfer, and probe and lander propulsion. Space travel is inventive and exciting.

Research, production, and use costs must be decreased to make space transportation systems generally available. Security shouldn't be affected. Rocket propellants must be high-performing, non-toxic, and safe. Rocket engines have other parts. Restarting and throttling are crucial. These are inaccessible to solid rocket motors. Developing a liquid rocket engine is hard and expensive, but it can ...


Engine Performance On Atomization Of Fuel Injector: A Review, Ankit Patil Er., Akshay C. Bedke Er., Vedant A. Deshmukh Er., Pratiksha Y. Shevare Er. 2022 Department of Aerospace Engineering, SOET, Sandip University, Nashik, INDIA

Engine Performance On Atomization Of Fuel Injector: A Review, Ankit Patil Er., Akshay C. Bedke Er., Vedant A. Deshmukh Er., Pratiksha Y. Shevare Er.

Graduate Research in Engineering and Technology (GRET)

The impact of the fuel injection of fuel atoms on engine performance has been investigated to improve fuel efficiency and waste disposal features. The fuel swirl method for injection atomization was evaluated both by the analysis of the fuel flow and the sample test. The goal of the paper is to establish good fuel atomization over the range of engine performance. As a result of our studies, it has been concluded that the desired atomization can be achieved when gasoline is thrown into a circular motion. Fuel spray and atomization features play an important role in the performance of internal ...


Thrust Generation By Ion Propulsion Technology, Vishal Kaushik Prof., Raghav M. Katwale Mr., Dhiraj N. Sakore Mr. 2022 Assistant Professor Department of Aeronautical Engineering, Priyadarshini College of Engineering, Nagpur, Maharashtra

Thrust Generation By Ion Propulsion Technology, Vishal Kaushik Prof., Raghav M. Katwale Mr., Dhiraj N. Sakore Mr.

Graduate Research in Engineering and Technology (GRET)

Electric propulsion system proven to be a suitable and efficient alternative for conventional propulsion systems .Ion thrusters is one of the electric propulsion systems. It has very high specific impulse generation (Isp) and consumes very low amount of fuel. Ion thrusters can easily compete with chemical rockets propulsion, even if the thrust produce is very low compares to chemical propulsion. Ion propulsion system can be used for various space missions like orbit station keeping for geostationary satellite, orbit and altitude controlling, multi-goal missions. Ion thrusters are more compatible for deep space missions as they are tested for endurance test where ...


Film Cooling Method In Liquid Rocket Engine, Pradnya Cherkupalli Engineer Graduate, Juluru Sandeep Prof. 2022 Department of Aerospace Engineering, Sandip University, Nashik, Maharashtra, INDIA

Film Cooling Method In Liquid Rocket Engine, Pradnya Cherkupalli Engineer Graduate, Juluru Sandeep Prof.

Graduate Research in Engineering and Technology (GRET)

Design Criteria, Experimental Studies of Supersonic Shock Wave Interaction with Film Cooling, and High-Pressure Subscale Combustion Chamber of Film Cooling Liquid-Propellant Rocket Engines are all covered in this review study. Using earth-storable, space-storable, and cryogenic propellant combinations, the study establishes the applicability of film cooling to rocket engines in the high thrust range. The study's findings are given in this publication. Additionally, data from studies mixing different types of propellant were used to evaluate the analytical model's accuracy. Tests employing supersonic film cooling were done in the wind tunnel to investigate the impact of external shock waves on ...


Engine Use In Hybrid Rocket - A Review, Shantanu. U. Bayaskar Er., Vaibhav Arya Graduate Engineer, Shiva Prasad U Prof. 2022 Sandip University

Engine Use In Hybrid Rocket - A Review, Shantanu. U. Bayaskar Er., Vaibhav Arya Graduate Engineer, Shiva Prasad U Prof.

Graduate Research in Engineering and Technology (GRET)

Despite all the other rocket motors on the market such as solid and liquid. A historically failed motor was in the market which was handicapped in performance but now with technological development in the previous years, hybrid rocket motor is the most influential talk in the market.

Deeper in the paper we will discuss the hybrid motor focusing on the fuel used in Hybrid rocket engines and the performance depending on the design. Furthermore, this review paper will help us to study the different materials for the betterment of the engine performance. We will also be focusing on the methods ...


Performance Study Of Post-Processed Additively Manufactured Low Thrust Nozzles, Tyler W. Gerhold 2022 Air Force Institute of Technology

Performance Study Of Post-Processed Additively Manufactured Low Thrust Nozzles, Tyler W. Gerhold

Theses and Dissertations

This research explores metal post-processing techniques to effectively reduce the large anomalous protrusions found in small additively manufactured low thrust rocket nozzles. Research has found that nozzles of this kind can experience losses in thrust of over 40%. Analytic theory of adiabatic nozzle flow with viscous losses for additively manufactured nozzles does not align with what has been found when tested experimentally. Compressible flow losses, such as shock wave formation inside the nozzle diverging cone, are likely the leading causes of such loss. Reduction in nozzle irregularities can likely yield results seen in analytic theory with similar performance to traditional ...


Method And Simulation Of On-Orbit Sub-Microthrust Evaluation, Jonathan Hood 2022 California Polytechnic State University, San Luis Obispo

Method And Simulation Of On-Orbit Sub-Microthrust Evaluation, Jonathan Hood

Master's Theses

With the advent of smaller satellites, along with the need for less than 0.1 μN precision attitude control for interferometry and imaging missions, finer micro- to sub-micro- thrusters have become an area of high interest. As thrusters are developed and ground-tested, it is necessary to evaluate their thrust performance on-orbit. On-orbit measurements offer actual thrust performance in mission conditions, free from ground facility vibrations and miniaturization restraints, and allow a thruster system to achieve a NASA Technology Readiness Level (TRL) of 7-8. A review is conducted of existing and proposed ground and on-orbit thrust measurement techniques. Experimental gaps and ...


Direct Simulation And Reduced-Order Modeling Of Premixed Flame Response To Acoustic Modulation, Zheng Qiao 2022 Mississippi State University

Direct Simulation And Reduced-Order Modeling Of Premixed Flame Response To Acoustic Modulation, Zheng Qiao

Theses and Dissertations

This dissertation introduces a general, predictive and cost-efficient reduced-order modeling (ROM) technique for characterization of flame response under acoustic modulation. The model is built upon the kinematic flame model–G-equation to describe the flame topology and dynamics, and the novelties of the ROM lie in i) a procedure to create the compatible base flow that can reproduce the correct flame geometry and ii) the use of a physically-consistent acoustic modulation field for the characterization of flame response. This ROM addresses the significant limitations of the classical kinematic model, which is only applicable to simple flame configurations and relies on ad-hoc ...


Nuclear Thermal Rocket Engine Control Autonomy Via Embedded Decision, David Sikorski 2022 University of Tennessee, Knoxville

Nuclear Thermal Rocket Engine Control Autonomy Via Embedded Decision, David Sikorski

Doctoral Dissertations

This doctoral dissertation presents an investigation of embedded decision capabilities as a means for developing nuclear reactor autonomous control. Nuclear thermal propulsion (NTP) is identified as a high priority technology for development, and is the focus of this research. First, a background investigation is presented on the state of the art in nuclear thermal rocket (NTR) engine control and modeling practices, resulting in the development of a low order NTR engine dynamic model based on the literature. The engine model was used to perform the following investigation, and is intended to serve as a research platform for the future development ...


Performance Variability In Solid Rocket Motors, Manvith Amara 2022 University of Alabama in Huntsville

Performance Variability In Solid Rocket Motors, Manvith Amara

Honors Capstone Projects and Theses

No abstract provided.


Using An Ultrasonic Technique To Determine Burning Rate Law, Brennan Hatton Haralson 2022 University of Alabama in Huntsville

Using An Ultrasonic Technique To Determine Burning Rate Law, Brennan Hatton Haralson

Honors Capstone Projects and Theses

No abstract provided.


Quasi-One-Dimensional Flow Method For Nuclear Thermal Propulsion Simulator Design, Ethan M. Long 2022 University of Tennessee Space Institute

Quasi-One-Dimensional Flow Method For Nuclear Thermal Propulsion Simulator Design, Ethan M. Long

Masters Theses

Quasi-One-Dimensional flow methods are commonly used to solve flow situations that have multiple driving influences, i.e. heat transfer, area change, and friction. They hold advantages over other computational fluid dynamics methods due to their much lower computational costs and overall simplicity. Typically, these methods are limited in their ability to solve flows due to the simplifying assumptions used. In this model, a simple heat transfer calculation is combined with NASA’s Chemical Equilibrium with Applications to constantly update chemical properties within the simulation. In this thesis, a quasi-one-dimensional model including these additions is developed and applied to a NTP ...


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