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An experimental comparison of nonswirling and swirling flow in a circular-to-rectangular transition ductCircular-to-rectangular transition ducts are used as exhaust system components of aircraft with rectangular exhaust nozzles. Often, the incoming flow of these transition ducts includes a swirling velocity component remaining from the gas turbine engine. Previous transition duct studies have either not included inlet swirl or when inlet swirl was considered, only overall performance parameters were evaluated. Circular-to-rectangular transition duct flows with and without inlet swirl were explored in order to understand the effect of inlet swirl on the transition duct flow field and to provide detailed duct flow data for comparison with numerical code predictions. A method was devised to create a swirling, solid body rotational flow with minimal associated disturbances. Coefficients based on velocities and total and static pressures measured incross stream planes at four axial locations within the transition duct, along with surface static pressure measurements and surface oil film visualization, are presented for both nonswirling and swirling incoming flow. In both cases the inlet centerline Mach number was 0.35. The Reynolds number based on the inlet centerline velocity and duct inlet diameter was 1,547,000 for nonswirling and 1,366,000 for swirling flow. The maximum swirl angle was 15.6 deg. Two pair of counter-rotating side wall vortices appeared in the duct flow without inlet swirl. These vortices were absent in the swirling incoming flow cases.
Document ID
19910011802
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Reichert, B. A. (NASA Lewis Research Center Cleveland, OH., United States)
Hingst, W. R. (NASA Lewis Research Center Cleveland, OH., United States)
Okiishi, T. H. (Iowa State Univ. of Science and Technology Ames., United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-0342
NASA-TM-104359
E-6149
NAS 1.15:104359
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: Reno, NV
Country: United States
Start Date: January 7, 1991
End Date: January 10, 1991
Sponsors: AIAA
Accession Number
91N21115
Funding Number(s)
PROJECT: RTOP 505-62-91
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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