Cooling of Gas Turbines. 2. Effectiveness of Rim Cooling of Blades
Abstract
An analysis of rim cooling, which cools the blade by condition alone, was conducted. Gas temperatures ranged from 1300 degrees to 1900 degrees F and rim temperatures from 0 degrees to 1000 degrees F below gas temperatures. Results show that gas temperature increases up to 200 degrees F are permissible provided that the blades are cooled by 400 degrees to 500 degrees F below the gas temperature. Relatively small amounts of blade cooling, at constant gas temperature, give large increases in blade life. Dependence of rim cooling on heat-transfer coefficient, blade dimensions, and thermal conductivity is determined by a single parameter.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 20, 1945
- Accession Number
- ADA800637
Entities
People
- Gene L. Meyer
- John S. Mccarthy
- Lincoln Wolfenstein
Organizations
- National Aeronautics and Space Administration