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Performance of annular prediffuser-combuster systemsResults of an experimental investigation of the aerodynamic performance of several annular prediffuser-combustor systems are presented. Three curved wall, dump prediffusers of different length, area ratio, and turning angle were tested with and without a simulated combustor located downstream of the prediffuser. Performance was significantly influenced by the presence of the combustor. Pressure recovery and flow losses were determined as a function of prediffuser inlet velocity profile, flow extraction at the prediffuser inlet, axial and radial location of the combustor front end, and distribution of the flow in the combustor. Axial location of the combustor was found to be the most significant parameter influencing system performance.
Document ID
19800057984
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wagner, W. B. (Pratt and Whitney Aircraft Group East Hartford, CT, United States)
Tanrikut, S. (United Technologies Corp. Pratt and Whitney Aircraft Group, East Hartford, Conn., United States)
Sokolowski, D. E. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 10, 2013
Publication Date
March 1, 1980
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
ASME PAPER 80-GT-15
Report Number: ASME PAPER 80-GT-15
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: New Orleans, LA
Start Date: March 10, 1980
End Date: March 13, 1980
Sponsors: American Society of Mechanical Engineers
Accession Number
80A42154
Distribution Limits
Public
Copyright
Other

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