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TAPS II Combustor Final Report

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TAPS II Combustor Final Report ( taps-ii-combustor-final-report )

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5.2 Development Through Certification The TAPS II demonstration was performed on a smaller LEAP core engine. The product design is a larger core so the combustion chamber will be scaled up and the number of fuel nozzles increased. Because of these changes sector and full annular testing will be completed as part of the product development. Flame tube testing is not required because the mixer down select was completed in the technology program. Combustor operability will continue to be developed as part of the certification effort. Improvements will be made in air start capability. Durability of the combustor liners will be improved by cooling optimization. This will be worked through analysis and full annular rig testing. Fuel nozzle durability will also be worked through heat shielding and geometry optimization. Again analysis, full annular rig and coking tests will be the primary tools. The main mixer flow may be reduced in the product design to better balance cruise efficiency and LTO NOx as described in section 4.2. Trade studies and additional full annular testing is planned to assess this in the product design. After conceptual, preliminary and detailed design and analysis and the associated component testing, the product development program will move into engine testing – both for engineering data and certification. 5.3 Introduction to the Field An objective of the CLEEN program was to work technology development with the potential for near term field introduction and impact commercial fleets. The TAPS II combustion system meets that requirement as it is planned for introduction in the LEAP engine family in 2016. The aircraft applications are shown in Figure 12. The TAPS design on the GEnx wide-body application has been in service for over 1 year. Introduction of TAPS II to narrow-body applications will greatly increase the fleet impact. Page 20

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