Calculations for axial compressor blading with uniform inlet enthalpy and radial enthalpy gradient
By: b[by] W. Schlachter
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1981
Place of publication: Monterey, California
Language: eng
Number of pages: 34
Subjects: Gas-turbines; Jet engines; Fluid mechanics; Enthalpy
Description: A computer program was used to calculate the radial distribution of flow parameters in an axial compressor stage designed to have a symmetrical velocity diagram at the mean radius and particular variations of reaction from hub to tip. Uniform energy addition was assumed to occur in the rotor. Both cases of uniform enthalpy and uniform radial enthalpy gradient at the entrance to the stage were considered. Advantages were found in the selection of fully symmetric blading and in the use of the inlet enthalpy gradient as a design parameter. (Author)
Notes: Title from cover.

"Prepared for: Naval Air Systems Command"--Cover.

"May 1981"--Cover.

"NPS67-81-008"--Cover.

DTIC Identifiers: Blade tips, PE61153N.

Author(s) key words: Axial compressor blading, radial equilibrium.

Includes bibliographical references (p. 9).

"Approved for public release; distribution unlimited"--Cover.

Technical report; 1981.

kmc/kmc 10/23/09.