A Method for designing transonic compressor blade propiles
IR@NAL: CSIR-National Aerospace Laboratories, Bangalore
View Archive Info| Field | Value | |
| Title |
A Method for designing transonic compressor blade propiles
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| Creator |
Anbarasu, M
Pai, BR |
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| Subject |
Aircraft Propulsion and Power
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| Description |
A computer code is developed for rapid design of
profiles suitable for transonic, highly loaded axial
flow compressors . Analysis of the profiles derived from
the procedure using viscous flow codes suggest that the
blades sections should yield efficient performance, characteristic of controlled diffusion aerofoils being introduced in modern gas turbines. Design for stators using
the method for validations studies in NAL experimental
compressor facility and for a contemporary design are
suggested.
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| Publisher |
National Aerospace Laboratories
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| Date |
1990
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| Type |
Proj.Doc/Technical Report
NonPeerReviewed |
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| Format |
application/pdf
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| Identifier |
http://nal-ir.nal.res.in/11401/1/PD_PR_9016.pdf
Anbarasu, M and Pai, BR (1990) A Method for designing transonic compressor blade propiles. Project Report. National Aerospace Laboratories, Bangalore. |
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| Relation |
http://nal-ir.nal.res.in/11401/
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