Accession Number:

ADA280344

Title:

Composite Matrix Experimental Combustor

Descriptive Note:

Final rept.,

Corporate Author:

GENERAL MOTORS CORP INDIANAPOLIS IN ALLISON GAS TURBINE DIV

Personal Author(s):

Report Date:

1994-04-01

Pagination or Media Count:

185.0

Abstract:

A joint ArmyNASA program was conducted to design, fabricate, and test an advanced, reverse-flow, small gas turbine combustor utilizing a compliant metalceramic CMC wall cooling concept. The objectives of this effort were to develop a design method basic design data base and analysis for the CMC cooling technique and then demonstrate its application to an advanced cycle, small, reverse-flow combustor with 3000 deg F burner outlet temperature BOT. The CMC concept offers significant improvements in wall cooling effectiveness resulting in a large reduction in cooling air requirements. Therefore more air is available for control of BOT pattern in addition to the benefits of improved efficiency, reduced emissions, and smoke levels. Task 1 of the program defined component materials and localized design of the composite wall structure in conjunction with development of basic design models for the analysis of flow and heat transfer through the wall. Task 2 required implementation of the selected materials and validated design model during combustor preliminary design. Detail design of the selected combustor concept and its refinement with 3-D aerothermal analysis were completed in Task 3. Task 4 covered detail drawings, process development and fabrication, and a series of burner rig tests. Author

Subject Categories:

  • Coatings, Colorants and Finishes
  • Laminates and Composite Materials
  • Fluid Mechanics
  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE