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Numerical analysis of turbine blade tip treatmentsThree-dimensional solutions of the Navier-Stokes equations for a turbine blade with a turning angle of 180 degrees have been computed, including blade tip treatments involving cavities. The geometry approximates a preliminary design for the GGOT (Generic Gas Oxidizer Turbine). The data presented here will be compared with experimental data to be obtained from a linear cascade using original GGOT blades. Results have been computed for a blade with 1 percent clearance, based on chord, and three different cavity sizes. All tests were conducted at a Reynolds number of 4 x 10 exp 7. The grid contains 39,440 points with 10 spanwise planes in the tip clearance region of 5.008E-04 m. Streamline plots and velocity vectors together with velocity divergence plots reveal the general flow behavior in the clearance region. Blade tip temperature calculations suggest placement of a cavity close to the upstream side of the blade tip for reduction of overall blade tip temperature. The solutions do not account for the relative motion between the endwall and the turbine blade. The solutions obtained are generally consistent with previous work done in this area,
Document ID
19940035321
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gopalaswamy, Nath S.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Whitaker, Kevin W.
(Alabama Univ. Tuscaloosa, United States)
Date Acquired
August 16, 2013
Publication Date
October 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
SAE PAPER 921928
Meeting Information
Meeting: SAE, Aerotech ''92 Conference
Location: Anaheim, CA
Country: United States
Start Date: October 5, 1992
End Date: October 8, 1992
Sponsors: SAE
Accession Number
94A11976
Distribution Limits
Public
Copyright
Other

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