DESIGN AND TEST OF TRANSPIRATION AIR COOLED TURBINE BLADES IN A FULL SCALE TURBOJET ENGINE
Abstract
The feasibility of achieving higher turbine inlet temperatures and increasing engine performance by the use of transpiration air cooled blades has been established. Compromises in the basic aerodynamic or mechanical design of the turbine are not necessary for the type of transpiration cooled blades developed. This transpiration air cooled turbine rotor blade can be fabricated by low cost, mass production techniques. Significant advances have been made in brazing of the porous material, but the brazing cycle is critical and requires additional research to broaden its time-temperature relationship.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 28, 1958
- Accession Number
- AD0481394
Entities
People
- D. Kump
- N. Lauziere