Fundamental Analysis of a Combined Cycle Rocket-Ramjet Propulsion System

2008 ◽  
Author(s):  
Robert LeMoyne
Keyword(s):  
Combined Cycle ◽  
Propulsion System ◽  
Fundamental Analysis

scholarly journals Performance Analysis of Combined Cycle with Air Breathing Derivative Gas Turbine, Heat Recovery Steam Generator, and Steam Turbine as LNG Tanker Main Engine Propulsion System

2020 ◽  
Vol 8 (9) ◽  
pp. 726
Author(s):  
Wahyu Nirbito ◽  
Muhammad Arif Budiyanto ◽  
Robby Muliadi
Keyword(s):  
Performance Analysis ◽  
Steam Turbine ◽  
Gas Turbine ◽  
Steam Generator ◽  
Heat Recovery ◽  
Combined Cycle ◽  
Propulsion System ◽  
Heat Recovery Steam Generator ◽  
Main Engine ◽  
Ship Speed

This study explains the performance analysis of a propulsion system engine of an LNG tanker using a combined cycle whose components are gas turbine, steam turbine, and heat recovery steam generator. The researches are to determine the total resistance of an LNG tanker with a capacity of 125,000 m3 by using the Maxsurf Resistance 20 software, as well as to design the propulsion system to meet the required power from the resistance by using the Cycle-Tempo 5.0 software. The simulation results indicate a maximum power of the system of about 28,122.23 kW with a fuel consumption of about 1.173 kg/s and a system efficiency of about 48.49% in fully loaded conditions. The ship speed can reach up to 20.67 knots.

Turbo/air augmented rocket - A combined cycle propulsion system

1989 ◽  
Author(s):  
A. GANJI ◽  
M. KHADEM ◽  
S. KHANDANI
Keyword(s):  
Combined Cycle ◽  
Propulsion System

Integration of Turbo-Expander and Turbo-Ramjet Engines in Hypersonic Vehicles

1994 ◽  
Vol 116 (1) ◽  
pp. 90-97 ◽  
Author(s):  
B. Zellner ◽  
W. Sterr ◽  
O. Herrmann
Keyword(s):  
System Performance ◽  
Combined Cycle ◽  
Propulsion System ◽  
Hypersonic Vehicles ◽  
Performance Simulation ◽  
Hypersonic Aircraft ◽  
High Speeds ◽  
University Of Munich ◽  
Turbo Expander ◽  
Ramjet Engines

Turbo-expander-ramjet and turbo-ramjet are two engine concepts considered for hypersonic aircraft designs with a flight regime between Mach 0 and 7. To establish any performance or integration aspects for these two combined-cycle engine types, an extended study of a variety of influence parameters is necessary, because the interaction between aircraft and propulsion system is even stronger than on conventional aircraft. In fact, the propulsion system is very sensitive to intake and nozzle/afterbody design at these high speeds. This paper presents the engine configurations chosen for comparison and describes the computer program used for the propulsion system performance simulation, including all relevant integration aspects. Furthermore, some results of propulsion system performance for a generic hypersonic aircraft and a typical ascent profile will be compared to indicate the special characteristics of the engines. Finally, some thoughts concerning the suitability and relevant technological requirements of the two engine types—seen from an aircraft manufacturer’s view—are included. The paper includes the results of two diploma theses, written by W. Sterr [1] and B. Zellner [2] at the Technical University of Munich, supervised by Prof. H. Rick (LFA) and O. Herrmann (MBB).

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

1991 ◽  
Vol 7 (4) ◽  
pp. 650-653 ◽  
Author(s):  
A. R. Ganji ◽  
M. Khadem ◽  
S. M. Khandani
Keyword(s):  
Combined Cycle ◽  
Propulsion System
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