1. Introduction 2. Theoretical background 3. High temperature gas dynamics and hypersonic effects 4. Cycle analyses and energy management 5. Inlets and nozzles 6. Supersonic combustion processes and characteristics 7. Testing methods and wind-tunnels 8. Computational fluid dynamics methods and solutions for high speed reacting flows.

The Scramjet Engine: Processes and Characteristics

The Scramjet Engine: List of Acronyms

A review of rocket-airbreathing combined-cycle propulsion systems for Earth-to-orbit applications is presented. Rocket-based combined-cycle (RBCC) engines take advantage of the synergistic interactions between the rocket and the airbreathing elements of the engine and the use of high-specie c impulse cycles to yield a mission-averaged specie c impulse that is higher than all-rocket technology can provide. An overview of the multimode operation is given, along with a review of both experimental and modeling work that has been done on this class of engines. Selected issues involved with these engines are discussed. These include engine/vehicle integration, e ow-path design for multimode operation, fuel selection, mixing enhancement and afterburning in rocket-ejector mode, thermal choking, and e ameholding. RBCC propulsion is becoming recognized as a promising technology for achieving a signie cant reduction in the cost of delivering payload to orbit.

Combined Rocket and Airbreathing Propulsion Systems for Space-Launch Applications

Rocket propellant and propulsion technology improvements can be used to reduce the development time and operational costs of new space-vehicle programs Advanced propellant technologies can make the space vehicles safer, more operable, and better performing Five technology areas are described: monopropellants, alternative hydrocarbons, gelled hydrogen, metalized gelled propellants, and high-energy density materials The benee ts of these propellants for future vehicles are outlined using mission study results and the technologies are briee y discussed

Propellant technologies : far-reaching benefits for aeronautical and space-vehicle propulsion

Effects of bypass air on boron combustion in solid fuel ramjets

A new concept of combined cycle propulsion system is proposed. In the proposed system, a turbojet (or turbofan) type engine provides compressed air as part or the whole oxidizer to the rocket engine at takeoff and part of the acceleration and climb. At the same time, the turbo-engine provides a portion of the thrust. The system performance shows little sensitivity to rocket chamber pressure, shows comparable performance to turbojet, and is capable to shifting to pure rocket mode at any desired point in the flight trajectory.

Turbo/air-augmented rocket - A combined cycle propulsion system

Transient response of gas turbine engines depends on several parameters including engine type, components’ characteristics, and operational condition. This paper briefly describes the general methodology and approach for transient sensitivity analysis of various gas turbine engines, and the results of a computer program for analysis of the transient behavior of a single spool turbojet. Based on the method of intercomponent volumes, the general methodology applicable to transient analysis of any gas turbine based system has been developed. The method results in a set of stiff, time dependent non-linear ordinary differential equations (ODE) which can be solved by an appropriate ODE solver. The coefficients of the differential equations depend on the design and operational condition of the components represented by the component maps. The initial conditions of the ODE can be any steady state operating point of the engine. A steady state engine model provides these initial conditions. The program has the capability to match the components, and obtain a steady state operating point for the engine, accept a fuel protocol and predict the transient behavior of the engine. The program has produced satisfactory results for step, ramp and sinusoidal fuel inputs, as well as ramp variation in nozzle exit area.Copyright © 1993 by ASME

S. M. H. Khandani

Papers

Turbo/air-augmented rocket - A combined cycle propulsion system

Transient Dynamics of Gas Turbine Engines

Aerothermodynamic analysis of combined-cycle propulsion systems

Aerothermodynamic analysis of combined cycle propulsion systems

Turbo/air augmented rocket - A combined cycle propulsion system