3 edition of Final technical report for aeroelastic analysis of turbomachinery for space propulsion found in the catalog.
Final technical report for aeroelastic analysis of turbomachinery for space propulsion
by Dept. of Mechanical, Industrial and Manufacturing Engineering, University of Toledo, National Aeronautics and Space Administration, National Technical Information Service, distributor in Toledo, Ohio, [Washington, DC, Springfield, Va
Written in English
|Other titles||Aeroelastic analysis of turbomachinery for space propulsion.|
|Statement||Theo G. Keith, Jr. & Durbha V. Murthy.|
|Series||[NASA contractor report] -- NASA-CR-202643., NASA contractor report -- NASA CR-202643.|
|Contributions||Murthy, Durbha V., 1960-, United States. National Aeronautics and Space Administration.|
|The Physical Object|
Bearing for Turbomachinery NASA/TM— March ARL–TR– U.S. ARMY • TECHNICAL PUBLICATION. Reports of completed research or a major significant contain extensive analysis. • CONTRACTOR REPORT. Scientific and technical findings by NASA-sponsored. Power loss due to the aeroelastic effect of the blade is becoming an important problem of large-scale blade design. Prior work has already employed the pretwisting method to deal with this problem and obtained some good results at reference wind speed. The aim of this study was to compensate for the power loss for all of the wind speeds by using the pretwisting method.
Presentations and publications Books and Book Chapters. Standard Handbook of Machine Design, Editors, Joseph E. Shigley and Charles R. Mischke, Chap "Journal Bearing Design," pp. to , published by McGraw-Hill Book Company, ; Bearings & Lubrication: Mechanical Designer's Workbook, Editors, Joseph E. Shigley and Charles R. Mischke, Chapter . The aeroelastic research program at NASA Glenn Research Center is focused on flutter (unstalled, stalled, and whirl), and forced response analyses of propulsion components. An overview of this research was presented in Ref. 1. -The review showed that a range of aerodynamic and structural models have been used to obtain the aeroelastic equations.
Journal of Propulsion and Power –] and explores its potential extension to the approximate unsteady throughflow analysis of multistage turbomachinery. The first study of nuclear propulsion for merchant vessels in Denmark made an economic comparison with turbine or diesel propulsion for a tanker of 65,tdw w shp and a speed of 17 knots. A pressurized water reactor with a capacity of 77 Mwt was the reactor type considered.
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Get this from a library. Final technical report for aeroelastic analysis of turbomachinery for space propulsion: NASA grant number NAG, grant duration--Janu to Febru [Theo G Keith; Durbha V Murthy; United States.
National Aeronautics and Space Administration.]. A MODAL AEROELASTIC ANALYSIS SCHEME FOR TURBOMACHINERY BLADING Todd E. Smith Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio ABSTRACT An aeroelastic analysis is developed which has general application to all types of axial-flow turbomachinery blades.
The approach is based on lin-ear modal analysis, where the blade's. Get this from a library. Final technical report for aeroelastic analysis of propulsion systems: NASA grant number NAG grant duration, Aug to December 9, [Theo G Keith; Aparajit Mahajan; United States.
National Aeronautics and Space Administration.]. Get this from a library. Sensitivity analysis for aeroacoustic and aeroelastic design of turbomachinery blades: final technical report. [Christopher B Lorence; Kenneth C Hall; United States.
National Aeronautics and Space Administration.]. Final Technical for Report Aeroelastic Analysis of Counter Rotation Fans NASA Grant Number NAG Aeroelastic problems in turbomachinery and propfans can be static or dynamic in nature. The analysis of static aeroelastic problems is involved primarily with Journal of Propulsion and Power, Vol.
7, No. 1, pp. Get this from a library. Final technical report for aeroelastic analysis of counter rotation fans: NASA grant number NAG ; grant duration, September 1, to Decem [Theo G Keith; Durbha V Murthy; United States. National Aeronautics and Space Administration.].
Volvo Aero Corporation, Space Propulsion Division, S Trollha¨ttan, Sweden Contributed by the International Gas Turbine Institute and presented at the International Gas Turbine and Aeroengine Congress and Exhibition, New Orleans, Louisiana, June 4–7, Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model These relate to rotor blade modal analysis, three-dimensional flight path definition, flight dynamics trim solution, aeroelasticity, and engine performance.
,” National Aeronautics and Space Administration, Technical Report No. Numerical Analysis of Typical Degradation Characteristics of a Transonic Fan,” German Aerospace Center (DLR), Cologne, Germany, Internal Report No.
DLR-IB A perturbation analysis of the linearized Navier–Stokes equations for real modes at low reduced frequency is presented and some conclusions are drawn. The first important result is that the loading of the airfoil plays an essential role in the trends of the phase and modulus of the unsteady pressure caused by the vibration of the airfoil.
A hybrid reduced-order model for the aeroelastic analysis of flexible subsonic wings with arbitrary planform is presented within a generalised quasi-analytical formulation, where a slender beam is considered as the linear structural dynamics model.
A modified strip theory is proposed for modelling the unsteady aerodynamics of the wing in incompressible flow, where thin aerofoil theory is. This book is, in essence, sixteen years in the making. First attempted to compile a history of the Soviet space program in author put together a rough chronology of the main events.
A decade later, while living on a couch in a college friend's apartment, he began writing what would be a short history of the Soviet lunar landing program. Department of Fluid Dynamics and Aerospace Propulsion, School of Aeronautics and Space, Universidad Politécnica de Madrid, Madrid Special Issue: 15th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachinery (ISUAAAT15) ,” Technical Rep Ecole Polytechnique Federale de Lausanne.
Aeroelasticity methods for turbomachinery. Description: A methodology for the coupled simulation of the fluid-structure turbomachinery problems with high-fidelity models will be given.
First, basic CFD methodologies using the ALE formulation, including turbulence modelling will be. 2. Numerical approaches to modelling fluid/structure interaction. In the most general sense, CAE can be considered a three-field problem requiring solutions of the discrete equations of structural dynamics, fluid dynamics, and the motion of the fluid and structure meshes (Farhat et al.
).The computational modelling of each of these problems is the focus of intense research and. Full text of "NASA Technical Reports Server (NTRS) Fluid mechanics, acoustics, and design of turbomachinery, part 2" See other formats. Technical Report.
Full-text available The forced response analysis of a turbomachinery component requires the transient pressure field over that component. This work is the final step of a. Program Objectives Aerospace Engineering is concerned with the engineering science governing flight and the design and construction of aircraft and spacecraft.
This includes the mechanisms behind flight and propulsion in the atmosphere and space including aerodynamics, lift and drag as well as the design and control of aircraft such as airplanes, helicopters, unmanned aerial vehicles (UAVs.
A hybrid reduced-order model (ROM) [22,23,24,25,26] for the aeroelastic analysis of subsonic wings in unsteady incompressible flow is presented here within a generalised quasi-analytical formulation.A modified strip theory (MST) is adopted for the aerodynamic load [27,28], tuned (TST) and standard (SST) strip theories being readily resumed for comparison .
the TURBO aeroelastic analysis code (Refs. 2 and 3). Such high-fidelity time-domain models require large numbers of computations and a long time for startup transients to decay before the final periodic solution is obtained.
A second approach is to use the periodicity in time of typical turbomachinery flows to represent each flow variable by a. Dep ar tment of Technical Mathematics, Center of Advanced Aerospace Technology, Technická Street 4, Prague 6, 07, Czech Republic e-mail: 1 @A review of recent aeroelastic analysis methods for propulsion at NASA Lewis Research Center [microform]  [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; [Springfield, Va.: National Technical Information Service, distributor], American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA