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).

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

1992 ◽  
Author(s):  
B. Zellner ◽  
W. Sterr ◽  
O. Herrmann
Keyword(s):  
Combined Cycle ◽  
Propulsion System ◽  
Hypersonic Vehicles ◽  
Extended Study ◽  
Hypersonic Aircraft ◽  
High Speeds ◽  
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.

scholarly journals A Method of Sizing Multi-Cycle Engines for Hypersonic Aircraft

1990 ◽  
Vol 112 (2) ◽  
pp. 217-222
Author(s):  
J. J. Kolden
Keyword(s):  
Iterative Procedure ◽  
Engine Performance ◽  
Computer Code ◽  
Propulsion System ◽  
Hypersonic Vehicles ◽  
Trade Off ◽  
Hypersonic Aircraft ◽  
Engine Size ◽  
Engine Cycle

A method of sizing multi-cycle engines for integration with hypersonic vehicles has been developed. The new procedure independently sizes the inlet, each engine cycle, and the nozzle during the vehicle sizing loop to optimize propulsion/aircraft integration. Using uninstalled engine performance for each cycle of a multi-cycle engine along with inlet and nozzle performance and an estimate of aircraft drag, an iterative procedure is utilized to size each component simultaneously. A propulsion system is defined that meets the aircraft thrust requirements at all mission points. The inlet is sized to provide airflow such that the maximum Mach cruise and/or combat thrust conditions are met. Each cycle is sized independently to meet all thrust requirements while minimizing either inlet drag or engine size. Nozzle sizing must trade off thrust, drag and nozzle weight. This methodology has been incorporated into a computer code entitled “Multi-Cycle Engine Sizing Program,” MCESP.

scholarly journals Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Energies ◽  
2019 ◽  
Vol 12 (2) ◽  
pp. 240
Author(s):  
Yiwei Dong ◽  
Ertai Wang ◽  
Yancheng You ◽  
Chunping Yin ◽  
Zongpu Wu
Keyword(s):  
Thermal Management ◽  
Thermal Protection ◽  
Combined Cycle ◽  
Propulsion System ◽  
Normal Operation ◽  
Hypersonic Aircraft ◽  
Thermal Management System ◽  
Barrier Coating ◽  
High Thermal Load

Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

scholarly journals A Method of Sizing Multi-Cycle Engines for Hypersonic Aircraft

1989 ◽  
Author(s):  
Jennifer J. Kolden
Keyword(s):  
Iterative Procedure ◽  
Engine Performance ◽  
Computer Code ◽  
Propulsion System ◽  
Hypersonic Vehicles ◽  
Trade Off ◽  
Hypersonic Aircraft ◽  
Engine Size ◽  
Engine Cycle

A method of sizing multi-cycle engines for integration with hypersonic vehicles has been developed. The new procedure independently sizes the inlet, each engine cycle, and the nozzle during the vehicle sizing loop to optimize propulsion/aircraft integration. Using uninstalled engine performance for each cycle of a multi-cycle engine along with inlet and nozzle performance and an estimate of aircraft drag, an iterative procedure is utilized to size each component simultaneously. A propulsion system is defined that meets the aircraft thrust requirements at all mission points. The inlet is sized to provide airflow such that the maximum Mach cruise and/or combat thrust conditions are met. Each cycle is sized independently to meet all thrust requirements while either minimizing inlet drag or engine size. Nozzle sizing must trade-off thrust, drag and nozzle weight. This methodology has been incorporated into a computer code entitled “Multi-Cycle Engine Sizing Program”, MCESP.

A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities

2005 ◽  
Vol 127 (1) ◽  
pp. 8-17 ◽  
Author(s):  
Milt Davis ◽  
Peter Montgomery
Keyword(s):  
System Performance ◽  
Engine Performance ◽  
Aircraft Engine ◽  
Flight Simulation ◽  
Propulsion System ◽  
Test Facility ◽  
Flight Testing ◽  
Test Environment ◽  
Ground Test ◽  
Aircraft System

Testing of a gas turbine engine for aircraft propulsion applications may be conducted in the actual aircraft or in a ground-test environment. Ground test facilities simulate flight conditions by providing airflow at pressures and temperatures experienced during flight. Flight-testing of the full aircraft system provides the best means of obtaining the exact environment that the propulsion system must operate in but must deal with limitations in the amount and type of instrumentation that can be put on-board the aircraft. Due to this limitation, engine performance may not be fully characterized. On the other hand, ground-test simulation provides the ability to enhance the instrumentation set such that engine performance can be fully quantified. However, the current ground-test methodology only simulates the flight environment thus placing limitations on obtaining system performance in the real environment. Generally, a combination of ground and flight tests is necessary to quantify the propulsion system performance over the entire envelop of aircraft operation. To alleviate some of the dependence on flight-testing to obtain engine performance during maneuvers or transients that are not currently done during ground testing, a planned enhancement to ground-test facilities was investigated and reported in this paper that will allow certain categories of flight maneuvers to be conducted. Ground-test facility performance is simulated via a numerical model that duplicates the current facility capabilities and with proper modifications represents planned improvements that allow certain aircraft maneuvers. The vision presented in this paper includes using an aircraft simulator that uses pilot inputs to maneuver the aircraft engine. The aircraft simulator then drives the facility to provide the correct engine environmental conditions represented by the flight maneuver.

Analog Study and Performance of the New 440-Ft Ferries for the State of Washington

1975 ◽  
Vol 12 (02) ◽  
pp. 146-162
Author(s):  
J. A. Beverley ◽  
R. L. Koch ◽  
E. C. Stewart ◽  
J. Weiks
Keyword(s):  
System Performance ◽  
The State ◽  
Design Tool ◽  
Propulsion System ◽  
Similar Data ◽  
Electrical System ◽  
And Performance ◽  
Analog Study ◽  
Walla Walla

This paper describes the ac-rectified dc propulsion system designed for the two ferry vessels, MV Spokane and MV Walla Walla, and reports the results of an analog study conducted as a design tool. Similar data are presented showing the results obtained by recording electrical system performance during builder's trials.

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