Accession Number:

ADA242628

Title:

A Generalized One Dimensional Computer Code for Turbomachinery Cooling Passage Flow Calculations

Descriptive Note:

Technical rept.,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CENTER

Report Date:

1989-07-12

Pagination or Media Count:

14.0

Abstract:

A generalized one-dimensional computer code for analyzing the flow and heat transfer in turbomachinery cooling passages has been developed. This code is capable of handling rotating cooling passages with turbulators inline, staggered, or inclined, 180 deg. turns both sharp and gradual turns, with and without turbulators, pin fins, finned passages, by-pass flows, tip cap impingement flows, and flow branching. The code is an extension of a one- dimensional code developed by P. Meitner. In the subject code, correlations for both heat transfer coefficient and pressure loss computations have been developed to model each of the above types of coolant passages. The code is capable of independently computing the friction factor and heat coefficient on each side of a rectangular passage. Either the mass flow at inlet to the channel or the exit plane pressure can be specified. For a specified inlet total temperature, inlet total pressure and exit static pressure, the code computes flow rates through the main branch and the subbranches if any, flow through tip cap for impingement cooling if any, in addition to computing the coolant pressure, temperature and heat transfer coefficient distribution in each coolant flow branch. Predictions from the subject code for both nonrotating and rotating passages agree well with experimental data. The code was used to analyze the coolant passage of a research cooled radial rotor.

Subject Categories:

  • Air Conditioning, Heating, Lighting and Ventilating
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE