Aerothermodynamics and Jet Propulsion

2021 ◽  
Author(s):  
Paul G. A. Cizmas
Keyword(s):  
Student Teaching ◽  
Undergraduate Students ◽  
First Principles ◽  
Rocket Engine ◽  
Governing Equations ◽  
Jet Engine ◽  
Jet Propulsion ◽  
Early Introduction ◽  
New Concepts ◽  
Engine Components

Get up to speed with this robust introduction to the aerothermodynamics principles underpinning jet propulsion, and learn how to apply these principles to jet engine components. Suitable for undergraduate students in aerospace and mechanical engineering, and for professional engineers working in jet propulsion, this textbook includes consistent emphasis on fundamental phenomena and key governing equations, providing students with a solid theoretical grounding on which to build practical understanding; clear derivations from first principles, enabling students to follow the reasoning behind key assumptions and decisions, and successfully apply these approaches to new problems; practical examples grounded in real-world jet propulsion scenarios illustrate new concepts throughout the book, giving students an early introduction to jet and rocket engine considerations; and online materials for course instructors, including solutions, figures, and software resources, to enhance student teaching.

FLYLITE ZRE-1

Alloy Digest ◽  
1952 ◽  
Vol 1 (2) ◽  
Keyword(s):  
Compressive Strength ◽  
High Temperature ◽  
Physical Properties ◽  
Tensile Properties ◽  
Base Alloy ◽  
Heat Treating ◽  
Jet Engine ◽  
Temperature Performance ◽  
Engine Components ◽  
Temperature Applications

Abstract Flylite ZRE-1 is a creep resistant magnesium-base alloy primarily designed for jet engine components and other high temperature applications. This datasheet provides information on composition, physical properties, hardness, elasticity, tensile properties, and compressive strength as well as creep. It also includes information on high temperature performance as well as casting, heat treating, machining, and joining. Filing Code: Mg-2. Producer or source: Howard Foundry Company.

Dimensional chains for ensuring that the assembled axisymmetric housing is inserted into the guide hole

2020 ◽  
pp. 380-383
Author(s):  
E.N. Rodionova ◽  
A.S. Yamnikov ◽  
I.A. Matveev
Keyword(s):  
Rocket Engine ◽  
Jet Engine ◽  
Launch Tube

Dimension chains were calculated using the example of a jet engine housing entering the launch tube. It was found that the method used does not take into account the actual values of losses and requires signifi cant reliability in the radical runout of the collected rocket engine case. A method for controlling radial runout in prisms is also considered.

Characterization of the Multiaxial States of Stress in an Uncooled Gas Turbine Blade

1987 ◽  
Author(s):  
A. Fischersworring ◽  
W. Koschel
Keyword(s):  
Turbine Blade ◽  
Elastic Stress ◽  
Primary Concern ◽  
Stress Strain ◽  
Jet Engine ◽  
Design Concepts ◽  
Engine Components ◽  
Damage Tolerant ◽  
Temperature Time

The assessment of fatigue-creep life of hot engine components either using conventional safe life design approach or damage tolerant design concepts require the computation and evaluation of the stress-strain-temperature-time cycles corresponding to the operational sequences. For typical jet engine operations the temperature and elastic stress-strain states for an uncooled turbine blade were calculated using finite elements. A primary concern was the aspect of multiaxiality and associated non-proportionality. The results are discussed in regard to multiaxial equivalent damage concepts.

Effects of Flow Distortions as They Occur in S-Duct Inlets on the Performance and Stability of a Jet Engine

2015 ◽  
Author(s):  
Rudolf. P. M. Rademakers ◽  
Stefan Bindl ◽  
Reinhard Niehuis
Keyword(s):  
Mesh Size ◽  
Experimental Investigations ◽  
Test Bed ◽  
Flow Distortion ◽  
Jet Engine ◽  
Jet Propulsion ◽  
Inlet Distortion ◽  
Flow Phenomena ◽  
The Impact ◽  
Duct Design

One of the research areas at the Institute of Jet Propulsion focuses on the design and optimization of s-shaped engine inlet configurations. The distortion being evoked within such inlet ducts should be limited to ensure an optimal performance, stability, and durability of the engine’s compression system. Computational Fluid Dynamics (CFD) play a major role in the design process of bent engine inlet ducts. The flow within such ducts can be computed, distortion patterns can be visualized, and related distortion coefficients are easily calculated. The impact of a distortion on flow phenomena within the compressor system can, however, only be computed with major computational efforts and thus the quality of an s-duct design in development is usually assessed by analyzing the evoked distortion with suitable distortion coefficients without a true knowledge of the duct’s influence on the downstream propulsion system. The influence of inlet distortion on both the performance and stability of the Larzac 04 jet engine was parameterized during experimental investigations at the engine test bed of the Institute of Jet Propulsion. Both pressure and swirl distortion patterns as they typically occur in s-duct inlet configurations were reproduced with distortion generators. Pressure distortion patterns were generated using seven types of distortion screens. The intensity of the distortion varies with the mesh size of the screen whereas the extension of the distortion is defined by the dimensions of the screen in radial and circumferential direction. A typical counter rotating twin-swirl was generated with a deltawing installed upstream of the compressor system. First, the development of flow distortion was analyzed for several engine operating points (EOPs). A linear relation between the total pressure loss in the engine inlet and the EOPs was found. Secondly, the flow within the compressor system with an inlet distortion was analyzed and unsteady flow phenomena were detected for severe inlet distortions. Finally, the effect of both pressure and swirl distortion on the performance and stability of the test vehicle was parameterized. A loss in engine performance with increasing inlet distortion is observable. The limiting inlet distortion with respect to engine stability was found and moreover it was shown that pressure distortion has a stronger influence on the stability of the compressor system compared to a counter rotating twin-swirl distortion. The presented parameterization is essential for the s-duct design, which is under development for an experimental set-up with the Larzac 04 jet engine.

Thrust Vectoring Design Project at Six Universities: Part I — Project Description and Final Designs

2013 ◽  
Author(s):  
Mark G. Turner ◽  
Markus P. Rumpfkeil ◽  
James T. VanKuren ◽  
Rory A. Roberts ◽  
Jeffrey Bons ◽  
...  
Keyword(s):  
Air Force ◽  
Undergraduate Students ◽  
Outreach Program ◽  
Thrust Vectoring ◽  
Jet Engine ◽  
Us Air Force ◽  
Project Description ◽  
The Us ◽  
Air Force Research Laboratory ◽  
Academic Year

An undergraduate student design and build project has been established by the US Air Force, Air Force Research Laboratory as part of an outreach program. During the 2011–2012 academic year, undergraduate students of six universities participated in designing a thrust vectoring system for a small (20 pound-thrust) jet engine. A description of the project parameters and student designs is given in this paper. It proved to be an extremely successful project, and other professors and students can learn from the different approaches taken by the six different teams and the project itself. Industry will also be interested in the depth and breadth of an undergraduate project that is being used to educate their future engineering workforce.

A COMPUTER-BASED, STUDENT-OPERATED ADVISING SYSTEM FOR EDUCATION MAJORS

1989 ◽  
Vol 9 (1) ◽  
pp. 25-32
Author(s):  
William D. Milheim ◽  
Nancy I. Bredemeier ◽  
Rebecca Clemente
Keyword(s):  
Student Teaching ◽  
Undergraduate Students ◽  
College Of Education ◽  
Preliminary Evaluation ◽  
Education Majors ◽  
State University ◽  
Education Students ◽  
Kent State University ◽  
Computer Based ◽  
Computer Controlled

The College of Education at Kent State University has recently implemented a computer-controlled advising system for use by undergraduate education students. This computer program provides information in a variety of different areas including descriptions of various education programs, deadlines and applications, student teaching, and other topics that may be helpful to these students. Preliminary evaluation shows that the system is easy to use and effectively able to answer the questions often asked by undergraduate students in the College.

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