Accession Number:

ADA027784

Title:

Three-Dimensional Compressible Flow Through Highly Loaded Axial Compressor Blade Rows.

Descriptive Note:

Interim rept. 15 Nov 74-14 Nov 75,

Corporate Author:

MASSACHUSETTS INST OF TECH CAMBRIDGE GAS TURBINE LAB

Personal Author(s):

• McCune,James E.
• Hawthorne,William R.

Report Date:

1976-05-01

Pagination or Media Count:

25.0

Abstract:

Three-dimensional inviscid flows through axial compressor cascades have been analyzed both in rectilinear and annular geometry, using Beltrami flow concepts. Comparison has been made with experimental data available from the M.I.T. Blowdown Compressor Test Facility. Such comparison indicates strongly that certain three-dimensional effects included in this theory are actually present in the real flow and that these may be important in practical design and performance analyses. The new theory is linearized about the nonlinear mean flow, so that large, practical pressure ratios can be included in the analysis. Examples have been given to show that three-dimensional induced-velocity effects can be as important, in highly-loaded transonic ducted fans, as many other effects currently included in engine design codes. This quasi-linear theory also has important implications regarding transonic compressor noise spectra.

Descriptors:

• *COMPRESSIBLE FLOW
• *TURBOMACHINERY
• *AXIAL FLOW COMPRESSOR BLADES
• EXPERIMENTAL DATA
• COMPARISON
• THEORY
• AERODYNAMIC LOADING
• INVISCID FLOW
• THREE DIMENSIONAL FLOW
• TRANSONIC CHARACTERISTICS
• CASCADES(FLUID DYNAMICS)

Subject Categories:

• Hydraulic and Pneumatic Equipment
• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE