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The 3-D numerical study of airflow in the compressor/combustor prediffuser and dump diffuser of an industrial gas turbine

Author
Yang, Tah-Teh
Published
Nov 1, 1993.
Physical Description
1 electronic document
Additional Creators
Agrawal, Ajay K.
Online Version

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Summary
This paper describes the 3D computations of a flow field in the compressor/combustor diffusers of an industrial gas turbine. The geometry considered includes components such as the combustor support strut, the transition piece and the impingement sleeve with discrete cooling air holes on its surface. Because the geometry was complex and 3D, the airflow path was divided into two computational domains sharing an interface region. The body-fitted grid was generated independently in each of the two domains. The governing equations for incompressible Navier-Stokes equations were solved using the finite volume approach. The results show that the flow in the prediffuser is strongly coupled with the flow in the dump diffuser and vice versa. The computations also revealed that the flow in the dump diffuser is highly nonuniform.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19940019187.
Accession ID: 94N23660.
NASA. Lewis Research Center, The Fifth Annual Thermal and Fluids Analysis Workshop; p 395-409.
Terms of Use and Reproduction
No Copyright.
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