Scientific and Technical Aerospace Reports Volume 39 April 6, 2001
Scientific and Technical Aerospace Reports Volume 39 April 6, 2001
Scientific and Technical Aerospace Reports Volume 39 April 6, 2001
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10<br />
07<br />
AIRCRAFT PROPULSION AND POWER<br />
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<strong>2001</strong>0025065 Naval Postgraduate School, Monterey, CA USA<br />
Experimental <strong>and</strong> Computational Investigation of the Endwall Flow in a Cascade of Compressor Blades<br />
Carlson, James R., II; Sep. 2000; 123p; In English<br />
Report No.(s): AD-A384642; No Copyright; Avail: CASI; A06, Hardcopy; A02, Microfiche<br />
An investigation of the three-dimensional flow in a cascade of second-generation controlled-diffusion blades, which was as<br />
a result of the interaction of the endwall boundary layers with the blade profiles, is reported. Five-hole probe wake surveys were<br />
performed at various spanwise locations to determine the total pressure loss distribution. Downstream velocity vector information<br />
was also obtained from the five-hole probe surveys. Two-component laser-Doppler velocimetry (LDV) was used to characterize<br />
the flow in the inlet <strong>and</strong> wake regions. A numerical investigation of the flowfield was conducted using SWIFT, a computational<br />
fluid dynamics code developed by Dr. Roderick Chima of NASA Glenn Research Center. Experimental blade-surface pressure<br />
coefficients were compared with values predicted using SWIFT. Overall, good correlation between the five-hole probe <strong>and</strong> LDV<br />
measurement techniques was obtained; however, the CFD predictions did not match well with the experimental results, particularly<br />
at the midspan location of the blade where separation of the suction surface boundary layer occurred.<br />
DTIC<br />
Computational Fluid Dynamics; Compressor Blades; Laser Doppler Velocimeters; Flow Distribution<br />
<strong>2001</strong>0025773 Brystin Research <strong>and</strong> Development, Inc., Waynesville, OH USA<br />
Advanced Materials Test Methods for Improved Life Prediction of Turbine Engine Components Final Report, 2 Apr. - 30<br />
Dec. 2000<br />
Stubbs, Jack B.; Hartman, George; Oct. 23, 2000; 42p; In English; Original contains color plates<br />
Contract(s)/Grant(s): F33615-00-C-5515<br />
Report No.(s): AD-A385388; No Copyright; Avail: CASI; A01, Microfiche; A03, Hardcopy<br />
Phase I final report developed under SBIR contract for Topic # AF00-149, ”Durability of Turbine Engine Materials/Advanced Material<br />
Test Methods for Improved Use Prediction of Turbine Engine Components”. All tasks were completed which included: 1) Customer Needs<br />
analysis 2) Develop <strong>and</strong> demonstrate a functional DCPD software module of WinMATE 2000, including all support system modules. 3)<br />
Demonstrate WEB based training method <strong>and</strong> features for WinMATE training tools. 4) Develop a commercialization strategy <strong>and</strong> alliances.<br />
The WinMATE DCPD software module was demonstrated as well as all of the supporting modules required to set up test parameters. communicate<br />
with data channels, display real-time data, <strong>and</strong> store configurations <strong>and</strong> data for later retrieval. The training requirements have<br />
been studied <strong>and</strong> a functional, web-based example of the learning tool was constructed <strong>and</strong> demonstrated. The work completed during Phase<br />
I of this effort has culminated in a strategic plan to meet the Phase II project objectives. We have demonstrated the technical feasibility of<br />
creating full-scale versions of the WinMATE software <strong>and</strong> learning tools. We have demonstrated the commercial feasibility of the Win-<br />
MATE technology <strong>and</strong> developed commercial alliances market entry.<br />
DTIC<br />
Life (Durability); Predictions; Turbine Engines; Software Engineering; Engine Parts<br />
08<br />
AIRCRAFT STABILITY AND CONTROL<br />
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<strong>2001</strong>0022236 NASA Langley Research Center, Hampton, VA USA<br />
MAVRIC Flutter Model Transonic Limit Cycle Oscillation Test<br />
Edwards, John W., NASA Langley Research Center, USA; Schuster, David M., NASA Langley Research Center, USA; Spain,<br />
Charles V., NASA Langley Research Center, USA; Keller, Donald F., NASA Langley Research Center, USA; Moses, Robert W.,<br />
NASA Langley Research Center, USA; [<strong>2001</strong>]; 18p; In English; 42nd; Structures, Structural Dynamics <strong>and</strong> Materials Conference,<br />
16-19 Apr. <strong>2001</strong>, Seattle, WA, USA; Sponsored by American Inst. of Aeronautics <strong>and</strong> Astronautics, USA<br />
Report No.(s): AIAA Paper <strong>2001</strong>-1291; No Copyright; Avail: CASI; A03, Hardcopy; A01, Microfiche
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