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Development of an Advanced Annular CombustorThe objective of the effort described in this report was to determine the structural durability of a full-scale advanced annular turbojet combustor using ASTM A-1 type fuel and operating at conditions typical of advanced supersonic aircraft. A full-scale annular combustor of the ram-induction type was fabricated and subjected to a 325-hour cyclic endurance test at conditions representative of operation in a Mach 3.0 aircraft. The combustor exhibited extensive cracking and scoop burning at the end of the test program. But these defects had no appreciable effect on combustor performance, as performance remained at a high level throughout the endurance program. Most performance goals were achieved with pressure loss values near 6% and 8%, and temperature rise variation ratio (deltaTVR) values near 1.25 and l.22 at takeoff and cruise conditions, respectively. Combustion efficiencies approached l004 and the exit radial temperature profiles were approximately as desired.
Document ID
19690018033
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Rusnak, J. P. (Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Shadowen, J. H. (Pratt and Whitney Aircraft West Palm Beach, FL, United States)
Date Acquired
August 5, 2013
Publication Date
May 30, 1969
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-72453
PWA FR-2832
Accession Number
69N27411
Funding Number(s)
CONTRACT_GRANT: NAS3-9403
Distribution Limits
Public
Copyright
Public Use Permitted.

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