Compliant Metal Enhanced Convection Cooled Reverse-Flow Annular Combustor
Abstract
A joint Army/NASA program was conducted to design, fabricate, and test an advanced, reverse-flow, small gas turbine combustor using a compliant metal enhanced (CME) convection wall cooling concept. The objectives of this effort were to develop a design method (basic design data base and analysis) for the CME cooling technique and then demonstrate its application to an advanced cycle, small, reverse-flow combustor with 3000 deg F (1922 K) burner outlet temperature (BOT). The CME 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 burner outlet temperature pattern in addition to the benefits of improved efficiency, reduced emissions, and smoke levels. Rig test results demonstrated the benefits and viability of the CME concept meeting or exceeding the aerothermal performance and liner wall temperature characteristics of similar lower temperature-rise combustors, achieving 0.15 pattern factor at 3000 deg F (1922 K) BOT, while utilizing approximately 80% less cooling air than conventional, film-cooled combustion systems
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1994
- Accession Number
- ADA283533
Entities
People
- Marc D. Paskin
- Waldo A. Acosta
Organizations
- National Aeronautics and Space Administration