Rotor design of high tip speed low loading transonic fan

1972 ◽  
Author(s):  
J. ERWIN ◽  
N. VITALE
Keyword(s):  
Rotor Design ◽  
Transonic Fan

Sweep in a Transonic Fan Rotor: Part 2 — CFD and Stress Analyses

1998 ◽  
Author(s):  
Hazem F. Abdelhamid ◽  
Raymond P. Shreeve ◽  
Garth V. Hobson
Keyword(s):  
Finite Element ◽  
Navier Stokes ◽  
Finite Element Code ◽  
Data Set ◽  
Manufacturing Optimization ◽  
Rotor Design ◽  
Reference Design ◽  
And Performance ◽  
Transonic Fan ◽  
Transonic Rotor

Forward-swept and back-swept transonic rotor geometries were generated from a reference design using a new 3D surface representation for blade geometry. Flow fields and performance were calculated using a thin-layer Navier-Stokes code and rotational stresses were calculated using a finite-element code. Grid generation problems, due to interfacing with the new geometry package, were resolved to obtain a consistent data set that isolated the effect of sweep on rotor performance. The intent of the study was to exercise and demonstrate the new geometry package by introducing sweep into an existing rotor design. The package is intended for aero-structural-manufacturing optimization.

scholarly journals Novel rotor design for high-speed flux reversal motor

2020 ◽  
Vol 6 ◽  
pp. 1544-1549
Author(s):  
Vladimir Dmitrievskii ◽  
Vladimir Prakht ◽  
Vadim Kazakbaev
Keyword(s):  
High Speed ◽  
Flux Reversal ◽  
Rotor Design

Performance Analysis of the Test Results on a Two-Stage Transonic Fan

1983 ◽  
Vol 105 (1) ◽  
pp. 125-129
Author(s):  
Baoshi Chen ◽  
Tianyi Zhang
Keyword(s):  
Mach Number ◽  
Performance Analysis ◽  
Radial Distribution ◽  
Flow Separation ◽  
High Load ◽  
Test Results ◽  
Two Stage ◽  
Stall Margin ◽  
High Incidence ◽  
Transonic Fan

Test results obtained from a two-stage fan are analysed and the reasons that caused the design performance target not to be attained are presented in this paper. Addition of a partspan shroud on rotor 1 caused higher losses and changed radial distribution of parameters. Modification on the flowpath and chord length of stator 1 resulted in excessively high inlet Mach number and flow separation in the hub region. The high load and high incidence at the hub of rotor 2 caused higher losses and reduced stall margin of the fan.

Experimental Investigation During Stall and Surge in a Transonic Fan Stage and Rotor-Only Configuration

2006 ◽  
Author(s):  
A. J. Gannon ◽  
G. V. Hobson ◽  
R. P. Shreeve ◽  
I. J. Villescas
Keyword(s):  
High Speed ◽  
Fast Response ◽  
Pressure Measurements ◽  
Post Processing ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
The Difference ◽  
Data Signal ◽  
Transonic Fan ◽  
Casing Pressure

High-speed pressure measurements of a transonic compressor rotor-stator stage and rotor-only configuration during stall and surge are presented. Rotational speed data showed the difference between the rotor-only case and rotor-stator stage. The rotor-only case stalled and remained stalled until the control throttle was opened. In the rotor-stator stage the compressor surged entering a cyclical stalling and then un-stalling pattern. An array of pressure probes was mounted in the case wall over the rotor for both configurations of the machine. The fast response probes were sampled at 196 608 Hz as the rotor was driven into stall. Inspection of the raw data signal allowed the size and speed of the stall cell during its growth to be investigated. Post-processing of the simultaneous signals of the casing pressure showed the development of the stall cell from the point of inception and allowed the structure of the stall cell to be viewed.

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