NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Transition mixing studyA computer model capable of analyzing the flow field in the transition liner of small gas turbine engines is developed. A FORTRAN code has been assembled from existing codes and physical submodels and used to predict the flow in several test geometries which contain characteristics similar to transition liners, and for which experimental data was available. Comparisons between the predictions and measurements indicate that the code produces qualitative results but that the turbulence models, both K-E and algebraic Reynolds Stress, underestimate the cross-stream diffusion. The code has also been used to perform a numerical experiment to examine the effect of a variety of parameters on the mixing process in transition liners. Comparisons illustrate that geometries with significant curvature show a drift of the jet trajectory toward the convex wall and weaker wake region vortices and decreased penetration for jets located on the convex wall of the liner, when compared to jets located on concave walls. Also shown were the approximate equivalency of angled slots and round holes and a technique by which jet mixing correlations developed for rectangular channels can be used for can geometries.
Document ID
19870007397
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Reynolds, R.
(Garrett Turbine Engine Co. Phoenix, AZ, United States)
White, C.
(Garrett Turbine Engine Co. Phoenix, AZ, United States)
Date Acquired
September 5, 2013
Publication Date
October 1, 1986
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NAS 1.26:175062
GARRETT-21-5723
NASA-CR-175062
Accession Number
87N16830
Funding Number(s)
CONTRACT_GRANT: NAS3-24340
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available