Aerodynamic Performance of a Transonic Low Aspect Ratio Turbine Nozzle

This paper presents detailed information on the three-dimensional flow field in a realistic turbine nozzle with an aspect ratio of 0.65 and a turning angle of 76 deg. The nozzle has been tested in a large-scale planar cascade over a range of exit Mach numbers from 0.3 to 1.3. The experimental result...

Full description

Saved in:
Bibliographic Details
Published in:Journal of turbomachinery 1993-07, Vol.115 (3), p.400-408
Main Authors: Moustapha, S. H, Carscallen, W. E, McGeachy, J. D
Format: Article
Language:English
Subjects:
330103 - Internal Combustion Engines- Turbine
ADVANCED PROPULSION SYSTEMS
AERODYNAMICS
Applied sciences
Continuous cycle engines: steam and gas turbines, jet engines
ENGINES
Engines and turbines
Exact sciences and technology
FLOW VISUALIZATION
FLUID MECHANICS
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
Mechanical engineering. Machine design
MECHANICS
NOZZLES
Citations: Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:This paper presents detailed information on the three-dimensional flow field in a realistic turbine nozzle with an aspect ratio of 0.65 and a turning angle of 76 deg. The nozzle has been tested in a large-scale planar cascade over a range of exit Mach numbers from 0.3 to 1.3. The experimental results are presented in the form of nozzle passage Mach number distributions and spanwise distribution of losses and exit flow angle. Details of the flow field inside the nozzle passage are examined by means of surface flow visualization and Schlieren pictures. The performance of the nozzle is compared to the data obtained for the same nozzle tested in an annular cascade and a stage environment. Excellent agreement is found between the measured pressure distribution and the prediction of a three-dimensional Euler flow solver.
ISSN:0889-504X
1528-8900
DOI:10.1115/1.2929267