TURBOJET ENGINES - Storming Media

AMC's Hydrogen Future: Sustainable Air Mobility

Jun-2009

116 pages

Authors: Adam D Reiman; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT

The full text of this report is available for sale.

The purpose of this research is to compare the costs associated with the transition to hydrogen aircraft for Air Mobility Command (AMC) to the costs of continuing using JP-8. Using current technology, air mobility aircraft can be designed to use liquid hydrogen instead of JP-8. This transformation will be capital intensive. A model was built that converted current AMC JP-8 usage to liquid hydrogen usage and calculated the costs of ...

Development and Qualification of a Specialized Gas Turbine Test Stand to Research the Potential Benefits of Nanocatalyst Fuel Additives

DEC 2007

87 pages

Authors: Nathan A. Kraemer; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Due to the wide use of gas turbine engines, any performance improvements would yield significant impacts to many military and civilian programs. While hardware upgrades require costly replacements to existing equipment, fuel performance enhancement could provide a near term cost effective solution. This thesis research focused on the development and qualification of a suitable test stand system to provide bench testing of nanocatalyst additives for jet fuels on a full-scale ...

Engine Test Cell Aeroacoustics and Recommendations

OCT 2007

115 pages

Authors: Christopher Tam; FLORIDA STATE UNIV TALLAHASSEE DEPT OF MATHEMATICS

Ground testing of turbojet engines in test cells necessarily involves very high acoustic amplitudes, often enough and severe enough that testing is interrupted and facility hardware and test articles are damaged. The acoustic response of test cells containing energetic jets is poorly understood and generally unpredictable. Nevertheless, there is a clear need to be able to predict deleterious acoustic events in advance of facility entry. A predictive capability would permit ...

Design of a Coaxial Split Flow Pulse Detonation Engine

JUN 2006

59 pages

Authors: Philip D. Hall; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Future Navy Capabilities indicate the need for a supersonic cruise missile. Thus the need exists for a low cost light-weight and efficient means of supersonic propulsion. NPS has been developing the Pulse Detonation Engine. which in theory has a thermodynamic efficiency greater than 50% as compared to 35% for state of the art constant-pressure cycles currently in use in gas turbines/ramjets/scramjets. Nonetheless, there are two major problems in the development ...

Scramjet Flow Field Control Using Magnetogasdynamics

APR 2006

102 pages

Authors: Richard J. McMullan; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Sustained hypersonic fight using scramjet propulsion is the key technology bridging the gap between turbojets and the exoatmospheric environment where a rocket is required. Recent efforts have focused on electromagnetic (EM) flow control to mitigate the problems of high thermomechanical loads and low propulsion efficiencies associated with scramjet propulsion. Numerical simulations were employed to determine how EM flow control can improve scramjet performance. The research effort focused on applying both ...

Assessing the Potential for Improved Scramjet Performance Through Application of Electromagnetic Flow Control

23 MAR 2006

176 pages

Authors: Martin F. Lindsey; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT

Hypersonic flight using scramjet propulsion bridges the gap between turbojets and rockets. Recent efforts focus on magnetogasdynamic (MGD) flow control to mitigate the problems of high thermomechanical loads and low efficiencies associated with scramjets. This research is the first flight-scale, three-dimensional computational analysis of a realistic scramjet to assess how MGD flow control improves scramjet performance. Developing a quasi-one dimensional design tool culminated in the first open source scramjet geometry. ...

Performance Study of Staging Variables on Two-Stage-to-Orbit Reusable Launch Vehicles

MAR 2005

65 pages

Authors: James K. Nilsen; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT

The purpose of this research is to investigate the effects of staging variables on Two-Stage-To-Orbit reusable launch vehicles, specifically, the question of what measurable factors play important roles in staging performance. Three different configurations (Rocket-Rocket, Turbojet-Rocket and Turbine Based Combined Cycle-Rocket) were considered. The software, Program to Optimize Simulated Trajectories (POST), was used to analyze these configurations. Vehicle coasting time, staging dynamic pressure and staging Mach number were all varied ...

Performance Study of Two-Stage-To-Orbit Reusable Launch Vehicle Propulsion Alternatives

MAR 2004

110 pages

Authors: Marc A. Brock; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS

This study investigated the performance of five Two-Stage-To-Orbit reusable launch vehicles (RLV), with stages propelled by rocket engines, turbojet engines and Rocket Based Combined Cycle (RBCC) engines. Horizontal versus vertical takeoff launch and direct versus lifting ascent trajectories were also studied. A method was conceived using a 3 degree of freedom optimization program, stage inert mass fractions, and a fixed gross takeoff weight (GTOW) of 1,000,000 lbf to determine each ...

Design and Operation of a Device for Evaluating Shaft Seals in Dynamic Applications

DEC 2003

108 pages

Authors: James E. Johnson; Edwin A. Frame; Clifford A. Moses; SOUTHWEST RESEARCH INST SAN ANTONIO TXTARDEC FUELS AND LUBRICANTS RESEARCH FACILITY

This document covers the design and operation of a testing device for evaluating elastomeric seals under dynamic conditions at temperatures ranging from 15 degrees to 300 degrees F. Turbojet engine fuel control systems employ sealing surfaces that move or slide over an elastomer sealing material. These seals are generally referred to as dynamic seals, and the usual configuration is an O-ring. Testing of seals under dynamic conditions is generally required ...

An Alternate Air System Concept for Application in a High Pressure Turbine

MAR 2003

11 pages

Authors: Dieter Peitsch; Winfried-Hagen Friedl; BMW ROLLS-ROYCE GMBH DAHLEWITZ (GERMANY)

In 1995, the German government initiated an aerospace research program in order to support the capabilities of german companies in the more and more challenging environment of aerospace business. Engine 3E is the research part of this overall program concentrating on jet engines. It's aim was to develop technologies to reduce the impact of turbojet engines onto the environment, where 3E stands for Efficiency, Economy and Environment. In this research ...

Prediction the Jet Near-Field Noise of Combat Aircraft

FEB 2003

Authors: M. Harper-Bourne; QINETIQ LTD FARNBOROUGH (UNITED KINGDOM)

The full text of this report is not available and therefore is not for sale. This information is provided for reference purposes only.

QinetiQ (previously DERA) is currently undertaking on behalf of the UK MOD an integrated programme of applied research to develop improved prediction methods for acoustic fatigue assessment on next generation combat aircraft. This paper describes ongoing work to develop practical methods of predicting the near-field noise of the high-speed exhausts of military jet engines, for use at an engineering level. The study encompasses both jet mixing noise and broadband shock ...

AFRL Missile Propulsion Technology

19 JUL 2002

5 pages

Authors: Amy Shertzer; AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE WEST

Material for Maj. Gen. Nielsen's missile technology presentation at the 5th annual Space and Missile Defense Conference in Huntsville, AL, 21 August 2002.

JANNAF Airbreathing Propulsion Subcommittee Meeting (26th) Held in Bayside Inn, The Sandestin Resort, Eglin Air Force Base, Destin, Florida on 8-12 April 2002. Volume I

APR 2002

Authors: Ronald S. Fry; Mary T. Gannaway; CHEMICAL PROPULSION INFORMATION AGENCY COLUMBIA MD

This volume, the first of four volumes, is a collection of 28 unclassified/unlimited-distribution papers which were presented at the Joint Army-Navy-NASA-Air Force (JANNAF) 26th Airbreathing Propulsion Subcommittee (APS) was held jointly with the 38th Combustion Subcommittee (CS), 20th Propulsion Systems Hazards Subcommittee (PSHS), and 2nd Modeling and Simulation Subcommittee. The meeting was held 8-12 April 2002 at the Bayside Inn at The Sandestin Golf & Beach Resort and Eglin Air ...

Active Control Symposium for Power Systems and Propulsion

JUN 2001

6 pages

Authors: Richard M. Murray; CALIFORNIA INST OF TECH PASADENA DIV OF ENGINEERING AND APPLIED SCIENCE

The major themes in the symposium were compression system instabilities and combustion system instabilities both important limiting factors of gas turbine performance. Results were presented in the area of active control of combustion instabilities demonstrating effectiveness across scales from laboratory rigs to full scale engines and a good understanding of the modeling and control issues. The status of compression systems is somewhat behind this primarily lacking in successful demonstrations on ...

Analysis of the Application of a Triggered Isomer Heat Exchanger as a Replacement for the Combustion Chamber in an Off-the-Shelf Turbojet

MAR 2001

92 pages

Authors: Carl R. Hartsfield; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING

The objective of this research was to evaluate the feasibility of using the triggered decay of a radioactive isomer in a solid-state heat exchanger to power a gas turbine engine. Primary performance measures were stagnation temperature increase and stagnation pressure drop across the heat exchanger. Analysis was performed using commercial software, and explored three types of heat exchanger: concentric tubes, radial fins with constant spacing, and radial fins with constant ...

Testing and Development of a Shrouded Gas Turbine Engine in a Freejet Facility

DEC 2000

87 pages

Authors: Hector Garcia; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Testing and analysis of a shrouded turbojet engine with possible application for high speed propulsion on low cost Unmanned Combat Aerial Vehicles (UCAV), Unmanned Aerial Vehicles (UAV) and missiles. The possibility of a turbojet providing thrust at subsonic conditions and the ramjet section providing the thrust in the supersonic regime exists. The combined cycle engine (CCE) could be incorporated into a variety of applications. The building of a new freejet ...

Advances in Turbo Engine Real-Time Simulation for Modern Control System Development

SEP 2000

10 pages

Authors: A. Kreiner; S. Kopp; A. Preiss; W. Erhard; H. Rick; TECHNICAL UNIV MUNICH (GERMANY)

Due to the growing available computational power, real-time simulations of dynamic turbo engine behavior can be carried out using performance analysis modeling. This partly removes the need for state space or function generator modeling and facilitates one common engine model to be used during engine design, engine control system design, and hardware-in-the-loop verifications, allowing faster design changes. Even if state space modeling is needed, for example during the control design ...

NASA'S Ultra-Efficient Engine Technology (UEET) Program/Aeropropulsion Technology Leadership for the 21st Century

SEP 2000

12 pages

Authors: Robert J. Shaw; NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH GLENN RESEARCH CENTER

One of NASA's four main product lines is developing and transferring to U.S. industry enabling technologies required for next-generation aerospace vehicles as part of the Aerospace Technology Enterprise. This paper overviews the Ultra Efficient Engine Technology (UEET) Program, NASA's focused aerospace propulsion technology program. The UEET Program emphasizes technology development in six selected areas: low emissions combustion, highly loaded turbomachinery, high temperature materials and structures, intelligent propulsion controls, propulsion-airframe integration, ...

Application of Low-Cost Turbo-Jet Powered Interceptors for Cruise Missile Defense

2000

10 pages

Authors: Gary T. Jimmerson; Hans J. Dall; ARMY AVIATION AND MISSILE COMMAND REDSTONE ARSENAL AL

With the proliferation of highly accurate long-range cruise missiles and the demonstrated capabilities of this type of weapon, defense against this threat is becoming an essential military requirement. Furthermore, the inherent characteristics of evolving cruise missiles, such as low cost, long range, payload mix and numerous launch options, are making cruise missiles a weapon of choice for many military planners. As a result, potential adversaries could soon possess sufficiently large ...

High-Cycle Fatigue and Time-Dependent Failure in Metallic Alloys for Propulsion Systems

01 SEP 1999

48 pages

Authors: Robert O. Ritchie; Subra Suresh; John W. Hutchinson; Walter W. Milligan; Anthony W. Thompson; CALIFORNIA UNIV BERKELEY

This program is focused on the definition, microstructural characterization and mechanism-based modeling of the limiting states of damage associated with the onset of high-cycle fatigue failure in titanium and nickel- base alloys for propulsion systems. Both experimental and theoretical studies are aimed at three areas, namely HCF/LCF interactions, the role of notches and foreign object damage, and fretting fatigue. The approach is to combine new experimental techniques for characterizing microstructural ...

Thrust Augmentation for a Small Turbojet Engine

MAR 1999

90 pages

Authors: Gary L. Hackaday; NAVAL POSTGRADUATE SCHOOL MONTEREY CA

A Sophia J450 (nine pounds of thrust) gas turbine engine was used first to examine the thrust augmentation generated using an ejector shroud. Experimental results obtained with and without the ejector were compared with performance predicted using an engine code and a one-dimensional ejector analysis. The engine code was revised to incorporate a radial turbine and the correct compressor map. Thrust augmentation of 3-10% was measured and the trends were ...

Design Principles and Methods for Aircraft Gas Turbine Engines Les Principes et Methodes de Conception des Turbomoteurs

FEB 1999

Authors: NATO RESEARCH AND TECHNOLOGY ORGANIZATION NEUILLY-SUR-SEINE (FRANCE)

The symposium dealt with design approaches for military aircraft propulsion systems to provide enhanced operational flexibility, longer range, better fuel efficiency and improved affordability. All classes of gas turbines were addressed in nine sessions as follows: Engine Design and Analysis (Part 1) (5 papers); Mechanical Systems (6 papers); Controls (4 papers); Combustors/ Augmentors (4 papers); Compressor Systems (Part I) (5 papers); Compressor Systems (Part II) (3 papers); Turbines (Part I) ...

Design and Testing of a Long Range Tele-Operated Missile System

1998

11 pages

Authors: George M. Landingham; George A. Sanders; ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING CENTER REDSTONE ARSENAL AL

The Missile, Research, Development and Engineering Center, MRDEC, of the U.S. Army Aviation and Missile Command, AMCOM is developing and demonstrating teleoperated missile systems that provide many of the capabilities that the Army has stated it needs. These capabilities include flexible mission planning, improved identification friend or foe, minimum collateral damage, and precision hit. The Multimode Airframe Technology (MAT) program will be completed in December 1999 and will demonstrate in ...

EXPLOITATION OF THE METAL MATRIX COMPOSITES CONCEPT.

1998

Authors: E. A. Feest

Institute of Metals : United Kingdom

Optical Instrument to Measure the Mass Concentration and Size Distribution of Smoke Particles

DEC 1997

32 pages

Authors: Cecil F. Hess; Stefan R. Martin; Jerry Seitzman; METROLASER IRVINE CA

This proposal describes the development of a system to measure in- situ and in real-time, the size distribution and mass concentration of soot particles in turbojet exhausts. The proposed system will work in-situ in highly turbulent environments. The total signal will yield soot mass concentration while the time-resolved signal will yield particle size. Its potentially compact size and large dynamic measurement range will give the system ...

Technology and the Air Force: A Retrospective Assessment

1997

341 pages

Authors: Jacob Neufeld; Jr. Watson George M.; David Chenoweth; AIR FORCE HISTORICAL STUDIES OFFICE BOLLING AFB DC

The history of the United States Air Force is inextricably bound up in the history of aerospace technology. Major revolutions have influenced the evolution of Air Force capabilities and systems, most notably those of atomic weaponry, the turbojet revolution, supersonic flight, avionics, aerial refueling, space flight, precision weaponry, electronic flying controls, composite materials, and stealth. It is worthwhile to take a retrospective look at some of the aerospace challenges and ...

Loss Mechanisms and Unsteady Flows in Turbomachines (Les Mechanismes des Pertes et Les Ecoulements Instationnaires dans Les Turbomachines)

JAN 96

Authors: ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRAN CE)

THERMAL AND GRINDING INDUCED RESIDUAL STRESSES IN A SILICON CARBIDE PARTICLE-REINFORCED ALUMINIUM METAL MATRIX COMPOSITE.

01 JAN 1995

Authors: R. S. Lee; G. A. Chen; Bing H. Hwang

Elsevier Science Limited : Great Britain

MELT EXTRACTION AND PROPERTIES OF ZRO2-AL2O3-BASED FIBERS.

01 JAN 1995

Authors: M. Allahverdi; R. A. Drew; J. STROM-OLSEN

Proceedings of the 19th Annual Conference on Composites, Advanced Ceramics, Materials, and Structures-B; Held Jan 1995, Cocoa Beach, Florida; Edited by John B. Wachtman; American Chemical Society : Westerville, Ohio

AL2O3(ZRO2) CELLULAR FIBERS.

01 JAN 1995

Authors: S. C. Farmer; A. Sayir

JOINING ADVANCED MATERIALS.

01 JAN 1995

Authors: Robert W. Messler Jr.

ASM International : Materials Park, Ohio

MACHINABILITY OF CAST AND POWDER-FORMED ALUMINUM ALLOYS REINFORCED WITH SIC PARTICLES.

01 JAN 1995

Authors: N. P. Hung; F. Y. C. Boey; K. A. Khor

Elsevier Science B.V. : The Netherlands

DYNAMIC COMPACTION OF AL-LI ALLOY COMPOSITES USING PREFORM.