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bladecad: an interactive geometric design tool for turbomachinery bladesA new metthodology for interactive design of turbomachinery blades is presented. Software implementation of the meth- ods provides a user interface that is intuitive to aero-designers while operating with standardized geometric forms. The primary contribution is that blade sections may be defined with respect to general surfaces of revolution which may be defined to represent the path of fluid flow through the turbomachine. The completed blade design is represented as a non-uniform rational B-spline (NURBS) surface and is written to a standard IGES file which is portable to most design, analysis, and manufacturing applications.
Document ID
19960047133
Document Type
Technical Memorandum (TM)
Authors
Miller, Perry L., IV
(Iowa State Univ. of Science and Technology Ames, IA United States)
Oliver, James H.
(Iowa State Univ. of Science and Technology Ames, IA United States)
Miller, David P.
(NASA Lewis Research Center Cleveland, OH United States)
Tweedt, Daniel L.
(NASA Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1996
Subject Category
Aircraft Propulsion and Power
Report/Patent Number
NASA-TM-107262
E-10327
NAS 1.15:107262
Meeting Information
Gas Turbine and Aeroengine Congress(Birmingham)
Funding Number(s)
CONTRACT_GRANT: NAG3-1318
PROJECT: RTOP 505-62-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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