Propulsion Efficiency Considerations for Combined Cycle Propulsion Systems

2015 ◽  
Author(s):  
John A. Bossard
Keyword(s):  
Combined Cycle ◽  
Propulsion Systems ◽  
Propulsion Efficiency

Aerothermodynamic analysis of combined cycle propulsion systems

1990 ◽  
Author(s):  
A. GANJI ◽  
M. KHADEM ◽  
S. KHANDANI
Keyword(s):  
Combined Cycle ◽  
Propulsion Systems

One Variant of Manned Mission to Mars with a Nuclear Electric Propulsion

2011 ◽  
Vol 1 (2) ◽  
pp. 1-17 ◽  
Author(s):  
M. S. Konstantinov ◽  
H. W. Loeb ◽  
V. G. Petukhov ◽  
G. A. Popov
Keyword(s):  
Electric Propulsion ◽  
Space Mission ◽  
Optimization Criterion ◽  
Low Earth Orbit ◽  
Problem Definition ◽  
Specific Mass ◽  
Propulsion Systems ◽  
Propulsion Efficiency ◽  
Mass Minimization ◽  
Low Mass

In this paper, one possible way for implementing a manned mission to Mars is examined. Typical peculiarities of the mission are as follows: the nuclear electric propulsion; relatively low mass of the spacecraft at a low Earth orbit (200 tons) and the crew time in flight is high (900-1000 days). Space mission analysis of the chosen variant is performed. As an optimization criterion, the authors chose the fuel mass required for the flight. Under examined problem definition such mass minimization is equivalent to maximal final mass of the spacecraft and maximal permissible total mass of power and electric propulsion systems. The authors show that to implement the examined manned mission, it is necessary to create the nuclear electric power and electric propulsion systems with a specific mass lower than 12.5 kg/kW under propulsion efficiency of 0.8, specific mass of the system for propellant storage of 0.05 and manned spacecraft complex mass of 52.1 tons. Under propulsion efficiency of 0.7, specific mass of power-propulsion should be lower than 10.9 kg/kW.

scholarly journals Ramjet Compression System for a Hypersonic Air Transportation Vehicle Combined Cycle Engine

Energies ◽  
2018 ◽  
Vol 11 (10) ◽  
pp. 2558 ◽  
Author(s):  
Sasha Veeran ◽  
Apostolos Pesyridis ◽  
Lionel Ganippa
Keyword(s):  
Flow Characteristics ◽  
Air Transportation ◽  
Combined Cycle ◽  
Propulsion Systems ◽  
Compression System ◽  
Ramjet Combustor ◽  
Start Up ◽  
Flight Profile ◽  
Self Powered ◽  
Transportation Vehicle

This report assesses the performance characteristics of a ramjet compression system in the application of a hypersonic vehicle. The vehicle is required to be self-powered and perform a complete flight profile using a combination of turbojet, ramjet and scramjet propulsion systems. The ramjet has been designed to operate between Mach 2.5 to Mach 5 conditions, allowing for start-up of the scramjet engine. Multiple designs, including varying ramp configurations and turbo-ramjet combinations, were investigated to evaluate their merits and limitations. Challenges arose with attempting to maintain sufficient pressure recoveries and favourable flow characteristics into the ramjet combustor. The results provide an engine inlet design capable of propelling the vehicle between the turbojet and scramjet phase of flight, allowing for the completion of its mission profile. Compromises in the design, however, had to be made in order to allow for optimisation of other propulsion systems including the scramjet nozzle and aerodynamics of the vehicle; it was concluded that these compromises were justified as the vehicle uses the ramjet engine for a minority of the flight profile as it transitions between low supersonic to hypersonic conditions.

Aerothermodynamic analysis of combined-cycle propulsion systems

1993 ◽  
Vol 9 (1) ◽  
pp. 153-155 ◽  
Author(s):  
A. R. Ganji ◽  
M. Khadem ◽  
S. M. H. Khandani
Keyword(s):  
Combined Cycle ◽  
Propulsion Systems

Integrated Thermal Management System Design for Advanced Propulsion System

2012 ◽  
Vol 232 ◽  
pp. 723-729
Author(s):  
De Cang Lou ◽  
Wen Guo ◽  
Zhi Guo Wang ◽  
Yong Hong Wang
Keyword(s):  
Thermal Management ◽  
Management System ◽  
Flow System ◽  
Combined Cycle ◽  
Propulsion System ◽  
Propulsion Systems ◽  
Key Technology ◽  
Hypersonic Propulsion ◽  
Thermal Management System ◽  
Aero Engines

Thermal management system (TMS) design is considered to be a key technology for advanced aero engines and supersonic or hypersonic propulsion systems. In this paper, the concepts of coupling flow and thermodynamic networks are proposed for TMS design. In this method, the propulsion system is considered to be a zero-dimensional flow system. Components, subsystems and hence the entire engine system can be modelled using some basic flow and thermodynamics networks. The platform for TMS design, ThermalM, is developed based on this model. As an example, modelling for a Turbine Based Combined Cycle (TBCC) thermal management system is described. Performance of the fuel heat exchanger in the network is discussed in detail. With the TMS design technology, performance of the advanced propulsion system can be analysed.

Preliminary research of terminal shock motion in tandem configuration turbine-based combined cycle inlet

2017 ◽  
Vol 121 (1237) ◽  
pp. 416-432
Author(s):  
J. Liu ◽  
H. Yuan ◽  
Z. Hua ◽  
W. Chen ◽  
N. Ge
Keyword(s):  
Pressure Oscillation ◽  
Combined Cycle ◽  
Navier Stokes ◽  
Small Range ◽  
Propulsion Systems ◽  
Tandem Configuration ◽  
The Third ◽  
Oscillatory Pattern ◽  
Shock Motion ◽  
Shock Oscillation

ABSTRACTThe pressure oscillation and terminal shock motion in a two dimensional inlet, which was designed for tandem configuration turbine-based combined cycle propulsion systems was investigated experimentally and numerically, respectively. The inlet was characterised by a bleed cavity upstream the inlet throat, an S-shape rectangular-to-circular diffuser and flowpaths for a turbine and a ramjet engine. The terminal shock motion was calculated through a second-order unsteady Reynolds-averaged Navier-Stokes scheme. The pressure and the terminal shock were unsteady when the combined cycle inlet operated at different conditions. With the terminal shock located in the throat and at the shoulder of the third ramp of the TBCC inlet, the pressure oscillation was significant and the shock exhibited unsteady streamwise motion with an oscillatory pattern. The amplitude of shock oscillation at these two conditions was 6mm and 12mm, respectively. When the shock was located downstream of the throat and upstream of the cowl lip, it oscillated in a small range. We defined this motion as the “shake” of the shock. This unsteady behaviour of the shock was caused by flow separation in the combined cycle inlet diffuser.

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