Accession Number : ADA256434


Title :   An Experimental and Analytical Study of TIP Clearance Effects in Axial Flow Compressors


Descriptive Note : Doctoral thesis,


Corporate Author : EXOTECH INC FREMONT CA


Personal Author(s) : Moyle, Ian N


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a256434.pdf


Report Date : Dec 1991


Pagination or Media Count : 251


Abstract : An analytical and experimental study of the performance changes and flow effects of rotor tip clearance variation in axial flow compressors is presented. The analyses demonstrate that previously unrecognized loss characteristics and flow behavior trends can be identified in a wide range of published tests of clearance effects. The performance and flow data are correlated at constant power conditions or nondimensionally in terms of the test compressor's geometry and wall flow conditions to observe the trends. Flow field changes caused by increasing the tip seal clearance of a low speed, large scale axial compressor having a symmetric velocity diagram were examined experimentally. The measurements were made at several clearances for one rotational speed. Synchronized blade-to-blade measurements of case wall static pressure and skin friction under the rotor tip of the second stage were collected.


Descriptors :   *AIR BREATHING ENGINES , *FLOW FIELDS , *GAS TURBINE BLADES , *ROTOR BLADES , *AXIAL FLOW COMPRESSORS , *CLEARANCES , *TURBOMACHINERY , *ROTOR BLADES(TURBOMACHINERY) , TEST AND EVALUATION , VELOCITY , THESES , SCALE , PRESSURE , WALLS , LOSSES , AXIAL FLOW , DIAGRAMS , SKIN FRICTION , STATIC PRESSURE , FRICTION , ROTORS , COMPRESSORS , FLOW , BEHAVIOR , RADIAL FLOW , RADIAL STRESS , POWER , GEOMETRY , CONSTANTS , VARIATIONS , BLADES , MEASUREMENT , ANGLES


Subject Categories : Hydraulic and Pneumatic Equipment
      Fluid Mechanics
      Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE