Inside-out rotary ramjet turbogenerator (original) (raw)

Design and Fabrication of a Ramjet Engine

In this report, the design and fabrication of the inlet to a ramjet engine is described. The inlet utilizes a single ramp and single sided three shock internal compression to slow the airflow from supersonic to subsonic speeds while providing maximum stagnation pressure to the combustor. The optimum angle for the inlet ramp is calculated to be 10° and it decelerates the airflow from Mach 3.3019 to Mach 0.5438. The stagnation pressure increases from 150 psi to 4.67 ksi. The material of the inlet is composed primarily of low carbon mild steel to accommodate the high pressure of the inlet.

IRJET- DESIGN AND ANALYSIS OF COMBUSTION CHAMBER IN RAMJET ENGINE

IRJET, 2021

Today's aircraft are powered by a variety of engines that generate thrust depending on the application. Each aircraft jet engine has its own collection of benefits and drawbacks. Each aircraft has a different type of engine depending on its intended use. One of the most important sources of supersonic flight power is the ramjet. In the near future, missiles powered by Ramjets, rockets powered by Ramjets, and supersonic fighters supported by Ramjets will lead the aviation market. Ramjet combustion has a variety of issues, including combustion instability and enhanced fuel mixing. The modeling, software analysis, and fabrication of a subsonic ramjet engine are all part of this project. The existence of a ventilated disc after the diffuser is a novel concept for ensuring proper fuel and air mixing. The diffuser, ventilated disc, combustion chamber, ignition system, and nozzle of the subsonic ramjet engine were all modeled and analysed in software before being manufactured according to our specification. The measurement programme tests and calculates temperature, velocity, and pressure distribution along the engine's longitudinal axis.

Integrated Combined Cycle Turbine-Ramjet-Scramjet-Rocket Engine

Alex Gardner, 2023

The Trident Engine is an innovative integrated propulsion system (U-TRSR) that combines turbine, ramjet, scramjet, and rocket engine technologies into a single, cohesive engine system. This advanced system enables aerospace vehicles to seamlessly transition across propulsion modes in various speed regimes and altitudes. The Trident Engine features primarily additively manufactured components, facilitating the production of integrated parts with intricate cooling geometries essential for diverse engine operations. The engine also incorporates a unique transitional nozzle geometry, which utilizes hydraulic systems to actuate single-piece nozzles during mode transitions. Additionally, the Trident Engine presents a novel variable combustion chamber with interlocking plates forming a mechanical iris atop the rocket engine combustion chamber. This groundbreaking engine system empowers runway takeoff, supersonic, hypersonic, and exo-atmospheric flight capabilities, representing a significant leap forward in aerospace technology.

Study of Innovative Subsonic Ramjet

Experimental and Computational Investigations in Engineering

Subsonic ramjets, due to its simplicity, nowadays could be very attractive for expendable unmanned applications. However, due to very low efficiency at low Mach numbers, practically there isn't any important application at subsonic speed. In 50's subsonic ramjet was used for tip jet applications. Later in 70's there was a study of Fan Augmented Ramjet (FARJ) where a fan was intended to be powered by a piston engine, both in subsonic and supersonic regimes. Almost at the same time it was analyzed ejector augmented subsonic ramjet. Both of these studies did not find real application of such engines. Finally, there was an attempt for the use of an Electric Ducted Fan, used in RC models, with a combustor but exit fan pressure was almost at atmospheric pressure which results in very low efficiency. This paper presents a study of propulsion system which consists of a pitot intake, electrically powered compressor/fan, combustor and nozzle (Electrically Fan Augmented Ram Jet, EFARJ). The electric motor connection to the compressor/fan is direct, without gearbox, which implies usage of a high-speed brushless motor. Such propulsion system is compared to pure ramjet and finally it is compared to performances of small expendable turbojet. Comparison is made regarding costs, weight and thrust/consumption. The study shows that the proposed propulsion system could be competitive for expendable, low speed and short duration applications.

Design Fabrication And Performance Analysis Of Subsonic RAMJET Engine

The aviation industry, in the past few decades, is interested in the supersonic flight. The defense sector of almost all the nations are involved in the design of modern supersonic fighter aircraft, ICBMs and innovations in faster air transport. Even most of the space agencies are interested in finding out the newer technologies of launching the satellites. In brief, Aeronautics has stepped into the next generation of explorations and innovations. Ramjet is one of the main sources of power for supersonic flight. Ramjet powered missiles, Ram Rocket, Ramjet assisted supersonic fighter will lead the aviation sector in the near future.In this project we are going to study the performance analysis of the Ramjet engine using different types of fuel and also using compressor and blower. Temperature, velocity and pressure distribution, along the longitudinal axis of the engine are measured using the Thermal sensor and Pitot-static tube.

Preliminary Design of a Ramjet Engine: An Analytical Approach

Journal of Thermal and Fluid Science, 2022

This work is based on preliminary design of Ramjet engine. Ramjet engine is simplest type of gas turbine engine used, which consists of non-moving parts for its operation. It is mainly used for power generation at supersonic speeds. This type of engine is mostly used in missiles, with a few applications in aircrafts. The present approach to preliminary design was based on mathematical equations considering ideal conditions. For the design, aero-thermodynamic equations were used starting with intake and followed by diffuser, combustor and nozzle. For the design purpose, initially Mach 2 and thrust of 10 kN was selected as desired condition. Subsequently, it was analyzed for the varying Mach numbers starting from Mach 1.5 to Mach 4 at desired thrust of 10 kN. Also, the design was analyzed for varying thrust from 6 kN to 22 kN at desired Mach number of 2. The results obtained have been reported and effects of variation of parameters have been represented graphically. The graphs were obtained using GNU Octave 6.4.0. The design achieved could be used for further steps of CAD model generation and subsequent analysis for the required purpose. It can serve as a base for detailed design of the engine.

TOWARDS LES OF MIXING PROCESSES INSIDE A RESEARCH RAMJET COMBUSTOR

Abstract In 1995, ONERA initiated a research,program,on,ramjet developments,with,the,support,of the,French,“Délégation,Générale,de l’Armement” (DGA/SPNuM, Ministry of Defense).,The,targeted,final objective,of,this,program,was,to improve,the,ramjet,combustion chamber,design,by,using,both experiments,and,validated,CFD codes. Among,the,various,mechanisms

Design, manufacturing and operation of a small turbojet-engine for research purposes

Applied Energy, 2007

A research project is on going, at the University of Padova, to develop a 200 N static-thrust engine to be used for both didactic and research activities. This paper describes in detail all the phases required to setup such an engine, including design, manufacturing and operation. The jet engine features a single-stage centrifugal compressor developing 2.66:1 compression ratio at 60,000 rpm, a direct-flow annular combustion chamber and a single-stage axial turbine with 950 K turbine-inlet temperature (TIT). All the design and manufacturing details are provided, as well as the operation procedure together with experimental results.

COMPUTATIONAL STUDY ON PERFORMANCE OF RAMJET ENGINE FOR VARIOUS MACH NUMBERS

Transstellar Journal , 2019

This research focuses on the modelling and simulation of combustion dynamics in lean premixed 2-D axisymmetric Ramjet engine for Mach number 3, 3.5, 4 and 4.5. Current research is to establish proper premixing of flow with fuel and generate proper conditions for combustions. Intake design is the primary objective for generating proper shock waves to reduce, and it enters the ramjet during supersonic speeds. Study includes proper combustion by reducing supersonic flow to subsonic before the combustor, and also proper mixture of air and fuel. Different air fuel ratios are considered and concluded by most efficient Air fuel mixture ratio. Meanwhile, aerodynamic properties such as pressure and temperature lead us to study the flow mixture.