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A comprehensive method for preliminary design optimization of axial gas turbine stagesA method is presented that performs a rapid, reasonably accurate preliminary pitchline optimization of axial gas turbine annular flowpath geometry, as well as an initial estimate of blade profile shapes, given only a minimum of thermodynamic cycle requirements. No geometric parameters need be specified. The following preliminary design data are determined: (1) the optimum flowpath geometry, within mechanical stress limits; (2) initial estimates of cascade blade shapes; (3) predictions of expected turbine performance. The method uses an inverse calculation technique whereby blade profiles are generated by designing channels to yield a specified velocity distribution on the two walls. Velocity distributions are then used to calculate the cascade loss parameters. Calculated blade shapes are used primarily to determine whether the assumed velocity loadings are physically realistic. Model verification is accomplished by comparison of predicted turbine geometry and performance with four existing single stage turbines.
Document ID
19820051556
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jenkins, R. M.
(Tuskegee Institute Tuskegee, AL, United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1982
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-1264
Meeting Information
Meeting: Joint Propulsion Conference
Location: Cleveland, OH
Start Date: June 21, 1982
End Date: June 23, 1982
Sponsors: AIAA, SAE, and ASME
Accession Number
82A35091
Funding Number(s)
CONTRACT_GRANT: NSG-3295
Distribution Limits
Public
Copyright
Other

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