Abstract
Semiempirical correlations calibrated with data from a wide variety of existing gas turbine combustors are rearranged and organized into a burner design methodology, yielding position and size of primary and secondary air penetration holes and swirler angle, as well as required atomization from both pilot and main fuel injectors at engine start and low power operating conditions. The methodology assumes the design fuel has been chosen and that combustor inlet conditions, overall length, and diameter (or annulus height) are known from mission and engine cycle analyses. Output parameters are based on quantitative specifications of maximum NO.X and CO emissions indices, maximum blowout fuel/air ratio at start and idle power, minimum combustion efficiency, and coldest fuel temperature at start (ground or at altitude). Insofar as possible, the methodology is verified with measurements for the three configurations of a can combustor developed for vehicular applications.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
