Accession Number:

ADA014261

Title:

Turbine Engine Exhaust Nozzle Performance with Nonuniform Inlet Flow

Descriptive Note:

Final rept. Jul 1973-Jun 1974

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1975-08-01

Pagination or Media Count:

60.0

Abstract:

The internal fluid dynamic performance of various turbine engine exhaust nozzle configurations was experimentally investigated. Nine fixed- geometry exhaust nozzle models representative of contemporary turbofans operating at various power levels were evaluated with uniform inlet conditions and with radial nonuniformities in total pressure and total temperature. The test conditions are representative of both low bypass turbofan and turbojet tailpipe flows. The effects of nozzle throat lip geometry on nozzle performance were evaluated. Also, the results obtained from the experimental phase were compared with the performance predicted from a numerical analysis developed at the Arnold Engineering Development Center. The major conclusion is that nozzle performance coefficients cannot be ascribed to a given nozzle configuration without some specification of the nozzle inlet flow conditions and coefficient referencing procedures.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE