Propulsion and Power Commons^™

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

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

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

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

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

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.

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.

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.

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.

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 ...

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

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 ...

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 ...

A Numerical Optimization Study Of A Novel Electrospray Emitter Design, Joshua H. Howell

Masters Theses

The low thrust and high specific impulse of electric propulsion has been brought to the forefront for CubeSat and small spacecraft applications. Electrospray thrusters, which operate via electrostatic principles, have seen much research, development, and application in recent years. The small sizes of the spacecraft that utilize electrospray thrusters has focused development into the miniaturization of this technology to the micro-scale. Miniaturization introduces design challenges that must be addressed, including power supply mass and footprint requirements. This consequence requires investigation into the effects of design choices on the thruster onset voltage, defined as the voltage at which ion emission begins ...

Understanding The Nonlinear Dynamics Governing Vertical-Lift Vehicles With Variable-Speed, Fixed Rotors, Stephanie Vavra, Micah Busboom, Aleea Stanford, Keegan Moore

UNL Student Research Days Posters, Undergraduate

Problem: Traffic significantly limits travel in urban areas. • The NASA Urban Air Mobility Project is developing an air taxi as an alternative mean of transportation (Fig. 1).

Challenge: Operating rotors at different frequencies may cause the cabin to vibrate at high amplitudes. Such effects are currently unknown.

Objective: Understand the effect of variable speed rotors on passenger comfort.

From the reduced-order modeling simulations, it can be assumed that counteracting the rotor speed in-balances can reduce the displacement and vibrations experienced at the center of the wing. In other words, should a rotor not maintain its optimal operation speed, reducing the ...

Cfd Simulation Of Varying Fuel Jet Placement Of Mach 2 Flow (Paper), Sara Broad

Honors Capstone Projects

Supersonic flow is a concept that has been researched heavily for the past twenty years. It has many applications, with the most notable one being for the defense industry. This project specifically is based off a model that is being currently used for Air Force research. With supersonic flow, where the Mach number is larger than one, there has been continual research specifically on flameholders. Flameholders involve the discussion of the mixing, ignition, and combustion of the fuel that is released into the lower cavity of the scramjet. There is a current standard for the placement of fuel jets, but ...

Large, Complex Housing, Alyssa Carnicella

Williams Honors College, Honors Research Projects

The purpose of this capstone project was to develop a design for a High Voltage Direct Current (HVDC) generator housing with built-in passageways for oil to flow through and cool the machine. The machine should be made using advanced manufacturing. A 3D model concept was designed with the use of SolidWorks. The appropriate hand calculations were completed to ensure that the generator housing would contain the components within itself under various environmental conditions.. The model was then 3D printed to produce a prototype that displays the design features within the housing. The next stage of the project will include completing ...

Liquid Engine External Pressurizer (Leep), Emily Armbrust

Williams Honors College, Honors Research Projects

The purpose of this project is to take the current liquid rocket engine test stand design and implement an external pressurant instead of utilizing the 2-phase oxidizer vapor to pressurize itself and the fuel. The purpose behind the design is because the team is limited with the current design concerning burn time due to the amount of propellant they can put in the tanks and the pressure it can reach. The initial pressure is currently not held since there is no external input of mass into the tanks, as the propellant is leaving. Adding an external pressurant allow for the ...

Investigation Of The Low-Temperature Combustion Phenomena Of A Fischer-Tropsch Synthetic Aerospace Fuel In A Constant Volume Combustion Chamber For Greenhouse Gas Reduction, Lily H. Parker

Honors College Theses

Greenhouse gases (GHG) have a harmful effect on our environment as they trap heat in the atmosphere accelerating climate change. As such, the Federal Aviation Administration’s 2025 strategic plan to reduce GHG emissions from air transportation. This call to action for a more environmentally friendly option highlights the importance of synthetic fuels as they are more sustainable compared to traditional fossil fuels. An investigation was conducted into the thermal-physical properties of Synthetic Fischer-Tropsch (F-T) Sustainable Aviation Fuels (SAF) and the Low Temperature Combustion (LTC). LTC is composed of the Low Temperature Heat Release (LTHR) and Negative Temperature Coefficient (NTC ...

Computational Comparison Of Dual Bell, Expansion-Deflection, And Aerospike Nozzles, Manuel R. Abadie Ardon

Honors College Theses

In the search for a Single-Stage-to-Orbit rocket, Altitude Compensating Nozzles concepts (ACNs) have been proposed since the 1950s, but research has stalled despite the modern analysis tools available. These nozzle concepts offer optimum performance at two or more altitude settings. This research chose three of these concepts, these being the Dual Bell, Expansion-Deflection, and Aerospike, which were designed and analyzed at various pressure ratios (NPR=10,15,30,36,30,45) using Computational Fluid Dynamics (CFD) software FLUENT. Simulations generated pressure distributions along the nozzle wall, which allowed to calculate data values such as thrust coefficients. Nozzle efficiency is calculated ...