Preliminary Design Code for an Axial Stage Compressor

Abstract

Current two dimensional preliminary design codes use structured programming, which is rigid and does not allow the user to vary parameters easily. This study uses object-oriented programming to allow the user to vary all selectable parameters in a familiar Windows operating environment. The programmed design is based on the assumptions of axial and free-vortex flow between blade rows, simple radial equilibrium, and a thermally and calorically perfect gas. The program allows a fan or core stage design and uses an open architecture to facilitate upgrades and extensions. Using the Naval Postgraduate School's (NPS) transonic compressor design as input, the preliminary design code output was compared to the detailed throughflow design of the transonic compressor. The results agreed reasonably well with detailed throughflow design. With some minor improvements this code can easily be used to develop a preliminary design that can be optimized to the user's requirements.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2001
Accession Number
ADA397395

Entities

People

  • Rizwan R. Ramakdawala

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Aspect Ratio
  • Axial Flow
  • Axial Flow Compressors
  • Basic Programming Language
  • Compressors
  • Computer Programming
  • Computer Programs
  • Computers
  • Equations
  • Flow
  • Geometry
  • Mach Number
  • Mass Flow
  • Operating Systems
  • Programming Languages
  • Secondary Flow
  • Turbines

Readers

  • Computer Programming and Software Development.
  • Fluid Dynamics.
  • Software Engineering