Mechanical design analysis of several noncritical air-cooled turbine disks and a corrugated-insert air-cooled turbine rotor blade Page: 3 of 51
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2 a NACA RM E55E21
air-cooling on engine arrangemext, strength, weight, critical-material
content, and producibility. As a preliminary step in this phase of the
investigations, a design study was made based on using noncritical mate-
rials in the rotor blades and disks for application with current turbine-
inlet gas-temperature levels. An air-cooled blade configuration having
good cooling characteristics was selected for this study, and all the
turbines compared were identical with respect to shape, size, and number
of air-cooled turbine rotor blades.
Prior investigations (refs. I and 2) have been conducted on air-
cooled blades similar to the blade used herein. These-investigations ea
indicate that the corrugated-insert blade as well as the 10-tube blade
of reference 3 and the strut blade of reference 4 would be suitable for
one or more of the general purposes for utilizing cooled blades.
In addition to obtaining air-cooled blades that-have high cooling
effectiveness and acceptable stress levels, the problem of supplying the
cooling air to the blades has also been considered. Previous experimental
research on air-cooled turbine rotors (refs. 5 and 6) utilized a split-
disk construction, the cooling-air being introduced through the down-
stream face of the turbine disk. For this application, several other
types of construction that were considered are presented schematically in
reference 7. These alternate designs, however, were not evaluated in the
light of disk stress analysis and the resulting weight-comparison.
All the turbine designs considered herein utilize the corrugated-
insert air-cooled blade of reference 2 (configuration H; profile 2). The
profile of this blade was evolved in an effort to obtain good cooling
effectiveness and to simplify fabrication procedures. In so doing, the
specified profile was quite thick in the midchord region and the trailing-
edge section. A complete description of this blade design and the results
of a performance investigation in cold air of a small-scale model of the
turbine are presented in reference 8. The cooling characteristics of this
corrugated-insert blade are presented in the heat-transfer and cooling-air
flow analysis of reference 2.
The assumption is made for the design studies presented herein that
provision for turbine cooling would be incorporated into the original
layout of the engine. The mechanical design, stress analysis, and method
of fabrication of the corrugated-insert blade are discussed in the present
report; with consideration given to both tapered and untapered blade shells
and three types of root fastening. Five disk designs for use with this
blade are included to illustrate variations in methods of distribution
and introduction of Tooling air to the blades. Representative types of
configuration for introducing the cooling air into the turbine disks are
also shown. These designs indicate generally the requirements for incor-
porating turbine rotor and rotor blade cooling in an engine design. For
comparative value, all work was based on the same turbine tip diameter
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Moseson, Merland L.; Krasner, Morton H. & Ziemer, Robert R. Mechanical design analysis of several noncritical air-cooled turbine disks and a corrugated-insert air-cooled turbine rotor blade, report, July 22, 1953; (digital.library.unt.edu/ark:/67531/metadc59615/m1/3/: accessed January 17, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.