Transonic Fan/Compressor Rotor Design Study. Volume 2

1982 ◽  
Author(s):  
D. E. Parker ◽  
M. R. Simonson
Keyword(s):  
Design Study ◽  
Compressor Rotor ◽  
Rotor Design ◽  
Transonic 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.

Aerodynamics of Compressor Casing Treatment: Part I—Experiment and Time-Accurate Numerical Simulation

2008 ◽  
Author(s):  
Fan Lin ◽  
Fangfei Ning ◽  
Huoxing Liu
Keyword(s):  
Axial Flow ◽  
Peak Efficiency ◽  
Flow Rates ◽  
Casing Treatment ◽  
Compressor Rotor ◽  
Rotor Design ◽  
Mass Flow Rates ◽  
Unsteady Rans ◽  
Flow Compressor ◽  
Operating Points

This paper presents both experimental and unsteady RANS investigations of a slot-type casing treatment at a transonic axial flow compressor rotor. Experimental results show that at 60% and 98% of rotor design wheel speeds, approximately 100% and 200% extra extensions of the rotor operation ranges are achieved, respectively. On the other hand, there are about 3.6% and 2.0% drops of efficiencies at 60% and 98% speeds respectively if comparisons are made at the same peak-efficiency mass flow rates of the solid casing case. If comparing the respective peak efficiencies for the solid casing case with those for the treated casing case, there are still about 3.4% and 0.7% drops at 60% and 98% speeds, respectively. As for the unsteady RANS study, an in-house unsteady RANS code has been used to study the casing treatment flow at several operating points, i.e., the peak efficiency and the near stall with regard to the solid casing case at 60% speed and 98% speed, respectively. It is shown that the interactions between the blade passage flow and the casing treatment flow exhibit different manner at two rotating speeds. The flow condition in which the rotor operates, i.e., either the subsonic condition at the 60% speed or the transonic condition with passage shock presented at the 98% speed, is one of the determinate factors that are responsible for the manner the casing treatment works. The loss production due to casing treatment is also particularly discussed.

Transonic Compressor Rotor Design Using Non-Monotonic Meanline Angle Distribution

2007 ◽  
Author(s):  
Zongjun Hu ◽  
Gecheng Zha ◽  
Matthew Montgomery ◽  
Thomas Roecken ◽  
John Orosa
Keyword(s):  
Mach Number ◽  
Rotor Blade ◽  
Angle Distribution ◽  
Stall Margin ◽  
Blade Passage ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
Rotor Design ◽  
Blade Section ◽  
Transonic Rotor

A non-monotonic meanline angle distribution technique with local negative camber is applied to a transonic rotor blade from the hub area to tip with the inlet Mach number varying from subsonic to low supersonic. The blade passage area is controlled by the non-monotonic meanline angle distribution, which results in reduced peak Mach number and weakened or removed shock wave. The negative camber is used downstream of the throat and hence it does not affect the flow passing capability of the blade section. The design point efficiency is significantly increased and the stall margin at part speed is also improved. Detailed results are given in the paper.

scholarly journals Numerical Simulation of Rotating Stall in Axial Compressor Blade Rows and Stages

1986 ◽  
Author(s):  
H. G. Neuhoff ◽  
K. G. Grahl
Keyword(s):  
Axial Compressor ◽  
Rotating Stall ◽  
Compressor Blade ◽  
Time Step ◽  
Time Constants ◽  
Compressor Rotor ◽  
Cascade Flow ◽  
Flow Through ◽  
Transonic Fan ◽  
Highly Loaded

Rotating stall is simulated by a time step integration procedure of the Euler equations. The prescribed compressors consist of finite inlet and outlet ducts, blade rows of finite chord lengths and a throttle without impedance. Due to this compressor model the net mass flow through the compressor remains constant during the transient to fully developed rotating stall. Results are presented for a highly loaded rotor and a transonic fan stage. Contrary to former nonlinear approaches, the presented theory indicates that the fully developed rotating stall in a single compressor rotor is not affected by the number of lobes of an initial circumferential disturbance. For a highly loaded stage the dependence of the stall parameters on the time constants of the cascade flow is demonstrated.

Numerical Analysis of Transonic Compressor Rotor Flow Near Stall Points

1997 ◽  
Author(s):  
Daisaku Masaki ◽  
Shojiro Kaji
Keyword(s):  
Numerical Analysis ◽  
Three Dimensional ◽  
Rotating Stall ◽  
Point Of View ◽  
Tip Clearance ◽  
Complex Flow ◽  
Transonic Compressor ◽  
Compressor Rotor ◽  
Design Speed ◽  
Transonic Fan

A three-dimensional Navier-Stokes solver based upon a high resolution shock-capturing scheme has been developed in order to analyze complex flow phenomena inside transonic fan/compressor rotors, especially tip clearance flow. The aim of this research is to find out a key element concerned with aerodynamic instability of transonic fan/compressor rotors such as rotating stall and surge by using this newly developed numerical tool. The numerical analysis of this research is twofold. First it investigates the flowfield of a transonic compressor rotor along the design speed operating line. It obtains definite flow structures around the tip region and clear description of the transition of the flow pattern inside the clearance gap between operating points, which shows that shock-tip leakage vortex interaction plays an important role on both loss generation and the failure of steady flow, or surge. A model will be proposed on the onset of tip stall in transonic compressor rotors according to the calculated results. Secondly, the above model will be examined through a series of numerical experiments by altering tip clearance height white keeping the design speed. From qualitative point of view, the model works fairly well and seems geometry-independent for typical transonic fan/compressor rotors. A clue to the optimum clearance is also obtained.

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