Test Results from an Analytically Designed Axial Compressor Stage of 1.65:1 Pressure Ratio Pratt and Whitney Aircraft of Canada Limited

Format:

Conference/Event

Author/Creator:

Yoshinaka, T., author.

Conference Name:

Turbine Powered Executive Aircraft Meeting (1980-04-09 : Scottsdale, Arizona, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1980

Summary:

A single stage axial compressor was designed for 1.53:1 pressure ratio using a quasi-three dimensional design method which consists of an iterative calculation between the radial equilibrium and blade-to-blade analyses including surface boundary layers.This stage was tested in place of the production first stage of a three stage axial combined with a single stage centrifugal (3A+1C) compressor in a research gas generator. Based on stator exit traverses, the research stage reached 87.8% adiabatic efficiency and 1.65:1 pressure ratio at the design speed. The overall compressor efficiency improved significantly at high speeds in comparison with the existing 3A+1C compressor, without any obvious performance deterioration at part speed.Some aspects of the design method are discussed and the test results are presented in this paper

Notes:

Vendor supplied data

Publisher Number:

800629

Access Restriction:

Restricted for use by site license