Design and development of the combustor inlet diffuser for the NASA/GE energy efficient engineResults of an experimental investigation of the aerodynamic performance of a split duct annular combustor inlet diffuser system are presented. Several diffuser configurations were investigated in 3X-scale water table tests and the preferred design was evaluated in full-scale annular airflow model tests. Pressure recovery and flow losses were determined as a function of prediffuser inlet velocity profile, flow extraction at the prediffuser exit, and distribution of flow in the combustor. Inlet velocity profile and turbulence levels were found to have a pronounced effect on system performance. Flow extraction at the prediffuser exit was found to have little influence on system performance. Generally, the annular split duct diffuser system was found to satisfy the performance objectives for the engine.
Document ID
19810045629
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sabla, P. E. (General Electric Co. Evendale, OH, United States)
Taylor, J. R. (General Electric Co. Evendale, Ohio, United States)
Gauntner, D. J. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1981
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
ASME PAPER 81-GT-129Report Number: ASME PAPER 81-GT-129
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: Houston, TX
Start Date: March 9, 1981
End Date: March 12, 1981
Sponsors: American Society of Mechanical Engineers