Structural Analysis of a Vane for an Advanced Environmental Control System Rotary Vaned Compressor.
Abstract
The primary intent of this effort was to determine if the existing ROVAC vane could be improved from a total weight, operational bearing loads, and vane tip deflection point of view. To attain these improvements the use of advanced filamentary composite materials was suggested and studied. The analysis consisted of the generating of an automated vane modeling (AVM) computer program from which a NASTRAN finite element model of the ROVAC vane could be modeled. Through the use of the AVM program, then, 22 design variations and materials substitutions were set up and analyzed by means of NASTRAN. Specifically the analysis involved 10 runs in which 9 advanced composite layups were compared against the baseline ROVAC vane. Following this survey the ROVAC vane axles (FDL-1 design) and vane axles and boots (FDL-2 design) were removed for further design improvements. Overall, the results of the study were very positive. Bearing loads were reduced from 975 lbs to 801 and 676 lbs for the FDL-1 and FDL-2 designs, respectively. They were then further reduced to 328 lbs by thinning the vane down to 40% of its original thickness. For these same design changes, vane-tip deflections were reduced from 2.91 mils to .11 and 1.06 mils for the FDL-1 and FDL-2 carbon graphite designs, respectively. They were further reduced to .9 mils for the 40% thick design. In regard to actual vane weight the following improvements were noted: Basic ROVAC Vane = .942 lbs, FDL-1 - .772 lbs, FDL-2 = .608 lbs, and the DFL-2 (40% thick) = .323 lbs. In addition to the above, overall vane stresses were also reduced by 40% to 60% and vane-edge deflections were reduced by 70%.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1977
- Accession Number
- ADA045701
Entities
People
- Kenneth P. Schwartz
Organizations
- Flight Dynamics Laboratory