Acoustic Flutter Control of Three-Dimensional Transonic Rotor Flow

2002 ◽  
Vol 18 (5) ◽  
pp. 1003-1011 ◽  
Author(s):  
Pong-Jeu Lu ◽  
Dartzi Pan ◽  
Yi-Di Yu
Keyword(s):  
Three Dimensional ◽  
Transonic Rotor ◽  
Rotor Flow

Quasi‐Three‐Dimensional Shock Fitting for Transonic Rotor Flow Fields in Hover

1995 ◽  
Vol 40 (1) ◽  
pp. 83-86
Author(s):  
Valana L. Wells ◽  
Thomas E. Vincent ◽  
John W. Rutherford
Keyword(s):  
Three Dimensional ◽  
Flow Fields ◽  
Shock Fitting ◽  
Transonic Rotor ◽  
Rotor Flow

scholarly journals Combined Free Wake / CFD Methodology for Predicting Transonic Rotor Flow in Hover

2002 ◽  
Vol 15 (2) ◽  
pp. 65-71 ◽  
Author(s):  
Yi-hua CAO ◽  
Zhi-qiang YU ◽  
Yuan SU ◽  
Kai KANG
Keyword(s):  
Free Wake ◽  
Transonic Rotor ◽  
Rotor Flow

Effects of Stator Wakes and Spanwise Nonuniform Inlet Conditions on the Rotor Flow of an Axial Turbine Stage

1993 ◽  
Vol 115 (1) ◽  
pp. 128-136 ◽  
Author(s):  
J. Zeschky ◽  
H. E. Gallus
Keyword(s):  
Flow Field ◽  
Three Dimensional ◽  
Axial Flow ◽  
Tip Clearance ◽  
Hot Wire ◽  
Turbine Stage ◽  
Static Pressure Distribution ◽  
Inlet Conditions ◽  
Experimental Values ◽  
Rotor Flow

Detailed measurements have been performed in a subsonic, axial-flow turbine stage to investigate the structure of the secondary flow field and the loss generation. The data include the static pressure distribution on the rotor blade passage surfaces and radial-circumferential measurements of the rotor exit flow field using three-dimensional hot-wire and pneumatic probes. The flow field at the rotor outlet is derived from unsteady hot-wire measurements with high temporal and spatial resolution. The paper presents the formation of the tip clearance vortex and the passage vortices, which are strongly influenced by the spanwise nonuniform stator outlet flow. Taking the experimental values for the unsteady flow velocities and turbulence properties, the effect of the periodic stator wakes on the rotor flow is discussed.

Research of Aerodynamic Performance of HP-Turbine with Coolant Injections for Variable Cycle Engine

2011 ◽  
Vol 110-116 ◽  
pp. 1047-1053
Author(s):  
Zhi Gang Liu ◽  
Xiang Jun Fang ◽  
Si Yong Liu ◽  
Ping Wang ◽  
Zhao Yin
Keyword(s):  
Film Cooling ◽  
Guide Vane ◽  
Supersonic Nozzle ◽  
Three Dimensional ◽  
Flow Characteristics ◽  
Thermodynamic Cycle ◽  
Aerodynamic Performance ◽  
Nozzle Guide Vane ◽  
Nozzle Guide ◽  
Transonic Rotor

A highly loaded high-pressure turbine with a supersonic nozzle guide vane and a transonic rotor for a Variable Cycle Engine (VCE) has been investigated. Film cooling strategies were designed for the whole stage, during which the positions, injection orientations and arrangements of cooling holes were confirmed. Three-dimensional steady numerical simulations have been performed in the two operation modes of low and high bypass ratio with different thermodynamic cycle parameters according to the VCE and the coolant injections have been simulated by means of additional source term method. The influences of coolant injections in the fully cooled turbine stage on aerodynamic performance and flow characteristics have been analyzed. The results indicate that, the supersonic nozzle guide vane, over-expansion degree of main flows, fluctuations of static pressure and intensity of corner vortex are lessened or alleviated. In the transonic rotor, expansion and doing work capabilities in the mixed fluid are strengthened. Proper coolants injections are beneficial to the flow characteristics in the blade passage.

Three-Dimensional Analysis of Turbine Rotor Flow Including Tip Clearance

1993 ◽  
Author(s):  
R. Heider ◽  
J. M. Duboue ◽  
B. Petot ◽  
G. Billonnet ◽  
V. Couaillier ◽  
...  
Keyword(s):  
Stokes Equations ◽  
Three Dimensional ◽  
Turbine Rotor ◽  
Operating Conditions ◽  
Tip Clearance ◽  
Navier Stokes ◽  
Navier Stokes Equations ◽  
Turbine Rotor Blade ◽  
Calculation Results ◽  
Rotor Flow

A 3D Navier-Stokes investigation of a high pressure turbine rotor blade including tip clearance effects is presented. The 3D Navier-Stokes code developed at ONERA solves the three-dimensional unsteady set of mass-averaged Navier-Stokes equations by the finite volume technique. A one step Lax-Wendroff type scheme is used in a rotating frame of reference. An implicit residual smoothing technique has been implemented, which accelerates the convergence towards the steady state. A mixing length model adapted to 3D configurations is used. The turbine rotor flow is calculated at transonic operating conditions. The tip clearance effect is taken into account. The gap region is discretized using more than 55,000 points within a multi-domain approach. The solution accounts for the relative motion of the blade and casing surfaces. The total mesh is composed of five sub-domains and counts 710,000 discretization points. The effect of the tip clearance on the main flow is demonstrated. The calculation results are compared to a 3D inviscid calculation, without tip clearance.

Reconstruction of a Three-Dimensional, Transonic Rotor Flowfield from Holographic Interferograms

AIAA Journal ◽  
1987 ◽  
Vol 25 (2) ◽  
pp. 300-305 ◽  
Author(s):  
Yung H. Yu ◽  
John K. Kittleson
Keyword(s):  
Three Dimensional ◽  
Transonic Rotor

scholarly journals Unsteady Upstream Effects in Axial-Flow Supersonic Compressor Stages

1979 ◽  
Author(s):  
H. E. Gallus ◽  
D. Bohn ◽  
K.-D. Broichhausen
Keyword(s):  
Static Pressure ◽  
Three Dimensional ◽  
Axial Flow ◽  
Three Dimensional Flow ◽  
Outlet Angle ◽  
Flow Disturbances ◽  
Flow Information ◽  
Design Speed ◽  
Flow Effects ◽  
Rotor Flow

An investigation of the unsteady flow effects in a supersonic compressor stage is reported. Semiconductor transducers mounted in the casing, a stroboscopic schlieren-technique and probes equipped with semiconductor transducers were used to obtain unsteady static pressure, flow visualization and three-dimensional flow information, respectively. The throttling effect during the starting procedure of the stage was found to produce changes of the quasi-steady and unsteady rotor flow pattern as well as changes in both amplitude and frequency of the flow disturbances at the inlet. The conditions which are generated in this way at design speed are different from those reached by back-pressure imposed on the started supersonic rotor at the same speed. The relative position of rotor and stator has an influence on the flow field only below design speed. One can conclude from the measurements of the rotor outlet angle that these effects generated by throttling the rotor flow by a stator during the starting procedure might be avoided with movable stator blades.

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