Accession Number : ADA589967


Title :   Design, Test, and Evaluation of a Transonic Axial Compressor Rotor with Splitter Blades


Descriptive Note : Doctoral thesis


Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA


Personal Author(s) : Drayton, Scott


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a589967.pdf


Report Date : Sep 2013


Pagination or Media Count : 99


Abstract : A new design procedure was developed and documented that uses commercial-off-the-shelf software (MATLAB, SolidWorks, and ANSYS-CFX) for the geometric rendering and analysis of a transonic axial compressor rotor with splitter blades. Predictive numerical simulations were conducted and experimental data were collected at the NPS TPL utilizing the Transonic Compressor Rig. This study advanced the understanding of splitter blade geometry, placement, and performance benefits. In particular, it was determined that moving the splitter blade forward in the passage between the main blades, which was a departure from the trends demonstrated in the few available previous transonic axial compressor splitter blade studies, increased the mass flow range with no loss in overall performance. With a large 0.91 mm (0.036 in) tip clearance, to preserve the integrity of the rotor, the experimentally measured peak total-to-total pressure ratio was 1.69 and the peak total-to-total isentropic efficiency was 72 percent at 100 percent design speed. Additionally, a higher than predicted 7.5 percent mass flow rate range was experimentally measured, which would make for easier engine control if this concept were to be included in an actual gas turbine engine.


Descriptors :   *AXIAL FLOW COMPRESSORS , *BLADES , *COMPRESSOR ROTORS , COMMERCIAL EQUIPMENT , COMPUTER PROGRAMS , EXPERIMENTAL DATA , GAS TURBINES , NUMERICAL ANALYSIS , OFF THE SHELF EQUIPMENT


Subject Categories : Reciprocating and Rotating Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE