Accession Number:

ADA439370

Title:

Computational Analysis of Flow Through a Transonic Compressor Rotor

Descriptive Note:

Master's thesis

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s):

Report Date:

2005-09-01

Pagination or Media Count:

71.0

Abstract:

As the United States Navy prepares to field a single engine jet, the F-35C Joint Strike Fighter, it is important that the causes of the pop-stall occurrence be understood. This problem arises as the jet engine ingests steam just prior to being released from the catapult. In examining this problem two Computational Fluid Dynamic CFD codes have been used by the Naval Postgraduate School to predict the performance of a transonic compressor rotor that is being tested with steam ingestion. Both codes, developed by NASA, provide a baseline that experimental results and new CFD codes can be compared with. Ansys Inc., a commercial Computer Aided Design CAD software company, has developed a new code that allows modeling of two phase flow. ICEM-CFD and CFX-5, both Anys Inc. programs that can model turbomachinery blade passages similar to that used by the NASA codes, were used in the present study. Comparisons were made with the experimental data and the predictions made by NASA codes as part of the initial modeling of the transonic compressor rotor flow field.

Subject Categories:

  • Attack and Fighter Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE