2D CFD Studies Using Different Turbulence Models of a Circulation Control Inlet Guide Vane

2007 ◽  
Author(s):  
H. E. Hill ◽  
W. F. Ng ◽  
P. P. Vlachos ◽  
S. A. Guillot ◽  
S. T. Bailie
Keyword(s):  
Isotropic Turbulence ◽  
Flow Problem ◽  
Guide Vane ◽  
Turbulence Models ◽  
Internal Flow ◽  
Inlet Guide Vane ◽  
Trailing Edge ◽  
Turning Angle ◽  
Streamline Curvature ◽  
Edge Geometry

The IGV in this study is an uncambered airfoil, designed to use the Coanda effect to achieve flow vectoring. For this internal flow problem, two isotropic turbulence models are compared to an anisotropic model. Good trend comparison was seen for turning angle and pressure loss performance characteristics given a nominal fixed trailing edge geometry. However, as the trailing edge geometry is modified in an attempt to increase turning, discrepancies become evident, possibly due to the effects of streamline curvature. As the trailing edge radius decreases, significant variations in the jet separation location are predicted, which translates directly into flow turning predictions. Further, one turbulence model was examined using a second CFD code to ensure software independence of the solutions.

Error Evaluation in Metal Surface Temperature Prediction Due to Non-Simulation of the Effect of Water Impingement and Runback Water on an Anti-Iced Turboprop Engine Inlet Guide Vane Structure

2008 ◽  
Author(s):  
Javier Castillo ◽  
Gema Ortega
Keyword(s):  
Surface Temperature ◽  
Material Selection ◽  
Guide Vane ◽  
Leading Edge ◽  
Simulation Software ◽  
Inlet Guide Vane ◽  
Development Phase ◽  
Trailing Edge ◽  
Airfoil Surface ◽  
Effect Of Water

During the optimization of the TP400D6 engine (powering the A400M military transport aircraft), the mechanical design of the Front Bearing Structure has proven to be one of the most challenging topics in the engine development programme. One of the leading technical subjects has been the design and optimization of the thermal anti-icing system of the component. When non-specific icing simulation software tools are available, the effect of the water impingement and runback water is difficult to simulate. The objective of this paper is to show one particular aspect learnt during the design and development phase of the project: the evaluation of the error obtained in the calculation of metal temperatures on an antiiced airfoil surface due to the effect of water impingement and runback water. TP400D6 engine front end arrangement consists of a single radial structure after the engine air intake performing both the structural and aerodynamic function, transmitting bearing and high propeller loads and being the compressor IGVs. The anti-icing system employs hot compressor bleed air circulating internally in the component through a series of internal channels and passages and exiting the airfoil through trailing edge holes. Due to airfoil aerodynamic constraints and material selection, it was realised in the earlier stages of the project that it was not possible to heat the whole vane profile up to the trailing edge. In consequence, the effects of the impingement water and runback of non-evaporated water from the intake and the IGV leading edge itself, play a key role on the determination of the airfoil surface temperature and potential ice accretion. Because of not having a specific icing simulation software, water impingement and runback water effects cannot be predicted with sufficient accuracy. During the engine programme’s development phase, a dedicated component antiicing rig test was conducted in order to evaluate and obtain a closer approximation of the real behaviour of the system. The scope of this paper is to go through the details of the aforementioned effect of icing water on airfoil surface temperature, focusing on the discrepancies between predicted temperatures and test rig measured temperatures. Typical thermal modelling is used, which incorporates the best possible understanding of the water particle impingement pattern onto the airfoils and flow lines distribution around the IGV profiles. Results from the rig test have been applied to the traditional thermal model in order to improve the thermal prediction simulation and understanding of the component.

scholarly journals An Analysis of Spatial Nonuniformity of the Flow at the Entrance Section of the Axial-Radial Impeller of a Centrifugal Compressor Stage Working on Regulation Modes

2019 ◽  
pp. 30-40
Author(s):  
A.D. Vanyashov ◽  
V.V. Karabanova
Keyword(s):  
Centrifugal Compressor ◽  
Guide Vane ◽  
Inlet Guide Vane ◽  
Compressor Stage ◽  
Turning Angle ◽  
Centrifugal Compressor Stage ◽  
Entrance Section ◽  
Spatial Nonuniformity ◽  
Optimum Diameter ◽  
Significant Difference

The article presents an analysis of the experimental data on testing a centrifugal compressor stage on regulation modes by changing the rotational speed of the rotor and the turning angle of the blades in the inlet guide vane unit. The distribution of the angles of attack at the entrance section of the impeller in relation to the blade height is obtained. It is established that a significant difference in the angles of attack from the plug to the periphery influences the polytropic efficiency of the compressor stage. Recommendations are given on the improvement of the mechanism of regulation by the inlet guide vane unit and on the choice of the optimum diameter for the entrance part of the driving impeller blades.

scholarly journals Experimental Performance in Annular Cascade of Variable Trailing-Edge Flap, Axial-Flow Compressor Inlet Guide Vanes

1970 ◽  
Author(s):  
T. H. Okiishi ◽  
G. H. Junkhan ◽  
G. K. Serovy
Keyword(s):  
Guide Vane ◽  
Axial Flow ◽  
Inlet Guide Vane ◽  
Variable Geometry ◽  
Trailing Edge ◽  
Axial Flow Compressor ◽  
Compressor Inlet ◽  
Trailing Edge Flap ◽  
Flow Compressor ◽  
Annular Cascade

Aerodynamic performance of a variable-geometry axial-flow compressor inlet guide vane configuration for a gas turbine unit was determined in a series of annular cascade tests. The variable-geometry vanes used uncambered, symmetrical airfoil sections as the basic blade profile with the rear 70 percent of the vane profile movable as a trailing-edge flap. Vane flap mechanical setting angles of 0 to 50 deg measured from the axial direction were possible, and performance parameters were determined over this range of angles. Turning angles followed a general trend obtained with Carter’s rule for accelerating cascades with the presently measured values tending to be lower than those obtained with Carter’s rule at higher setting angles. For large camber angles (greater than 35 deg) zero-incidence blade element total-pressure loss coefficients for the 50 percent passage location of the flapped vanes tested were higher than those that might have been obtained with a continously cambered vane row of the same solidity and camber.

Experimental and Numerical Researches in a Four-Stage Low Speed Research Compressor Facility

2020 ◽  
Author(s):  
Mingmin Zhu ◽  
Xiaoqing Qiang ◽  
Zhenzhou Ju ◽  
Yuchen Ma ◽  
Jinfang Teng
Keyword(s):  
Guide Vane ◽  
Axial Compressor ◽  
Internal Flow ◽  
Flow Fields ◽  
Inlet Guide Vane ◽  
External Diameter ◽  
Low Speed ◽  
Single Passage ◽  
Overall Performance ◽  
Inlet Conditions

Abstract The flow fields in rear stages of multi-stage axial compressor is difficult to measure in detail owing to the limited height and space. Thus, low speed research compressor (LSRC) facilities which are modelled from rear stages have been widely used to explore the internal flow fields and improve compressor design. A newly-designed vertical LSRC facility is established and put into used in Shanghai Jiao Tong University. The construction and design features of this LSRC facility are introduced in this paper. A cantilevered stage has been tested in this test rig. Compressor performance, inter-stage parameters distributions and contours are measured at design point and near stall point. Steady single passage simulations for four-stage compressor are carried out to validate numerical methods and further interpret the internal flow fields in test stages. This vertical LSRC facility consists of inlet guide vane (IGV) and four repeated stages with an external diameter of 1.5 meter and a rotating speed of 900 RPM. The third stage is the mainly tested one, while the first and second stages provide the inlet conditions and the fourth stage provides the outlet conditions. Complete measuring methods and systems are established for this newly-built LRSC facility. The measurements of overall performance and inter-stage flow fields are carried out for test stage with cantilevered stator rows. The simulation for four-stage compressor are also performed for cantilevered configuration. The results of steady single-passage simulation have a similar trend with experimental ones, in terms of overall performance and parameters distributions.

The Effects of Inlet Guide Vane-Wake Impingement on the Boundary Layer and the Near-Wake of a Rotor Blade

2010 ◽  
Vol 132 (4) ◽  
Author(s):  
Francesco Soranna ◽  
Yi-Chih Chow ◽  
Oguz Uzol ◽  
Joseph Katz
Keyword(s):  
Boundary Layer ◽  
Rotor Blade ◽  
Guide Vane ◽  
Shear Velocity ◽  
Inlet Guide Vane ◽  
Surface Boundary ◽  
Momentum Thickness ◽  
Suction Surface ◽  
Near Wake ◽  
Trailing Edge

This paper examines the response of a rotor blade boundary layer and a rotor near-wake to an impinging wake of an inlet guide vane (IGV) located upstream of the rotor blade. Two-dimensional particle image velocimetry (PIV) measurements are performed in a refractive index matched turbomachinery facility that provides unobstructed view of the entire flow field. Data obtained at several rotor phases enable us to examine the IGV-wake-induced changes to the structure of the boundary layer and how these changes affect the flow and turbulence within the rotor near-wake. We focus on the suction surface boundary layer, near the blade trailing edge, but analyze the evolution of both the pressure and suction sides of the near-wake. During the IGV-wake impingement, the boundary layer becomes significantly thinner, with lower momentum thickness and more stable profile compared with other phases at the same location. Analysis of available terms in the integral momentum equation indicates that the phase-averaged unsteady term is the main contributor to the decrease in momentum thickness within the impinging wake. Thinning of the boundary/shear layer extends into the rotor near-wake, making it narrower and increasing the phase-averaged shear velocity gradients and associated turbulent kinetic energy (TKE) production rate. Consequently, the TKE increases during wake thinning, with as much as 75% phase-dependent variations in its peak magnitude. This paper introduces a new way of looking at the PIV data by defining a wake-oriented coordinate system, which enables to study the structure of turbulence around the trailing edge in great detail.

Aerodynamic Performance of a Transonic Turbine Guide Vane With Trailing Edge Coolant Ejection: Part I—Experimental Approach

1996 ◽  
Vol 118 (3) ◽  
pp. 519-528 ◽  
Author(s):  
C. Kapteijn ◽  
J. Amecke ◽  
V. Michelassi
Keyword(s):  
Gas Turbines ◽  
Experimental Approach ◽  
Guide Vane ◽  
Flow Behavior ◽  
Aerodynamic Performance ◽  
Inlet Guide Vane ◽  
Trailing Edge ◽  
Cooling Flow ◽  
Turbine Guide Vane ◽  
Transonic Turbine

Inlet guide vanes (IGV) of high-temperature gas turbines require an effective trailing edge cooling. But this cooling significantly influences the aerodynamic performance caused by the unavoidable thickening of the trailing edge and the interference of the cooling flow with the main flow. As part of a comprehensive research program, an inlet guide vane was designed and manufactured with two different trailing edge shapes. The results from the cascade tests show that the flow behavior upstream of the trailing edge remains unchanged. The homogeneous values downstream show higher turning and higher losses for the cut-back blade, especially in the supersonic range. Additional tests were conducted with carbon dioxide ejection, in order to analyze the mixing process downstream of the cascade.

Effect of Geometry Deviations on the Aerodynamic Performance of an Outlet Guide Vane Cascade

2010 ◽  
Author(s):  
Valery Chernoray ◽  
Sofia Ore ◽  
Jonas Larsson
Keyword(s):  
Guide Vane ◽  
Three Dimensional ◽  
Turbulence Models ◽  
Surface Geometry ◽  
Turning Angle ◽  
Low Pressure Turbine ◽  
Repair Patch ◽  
Roughness Elements ◽  
Baseline Case ◽  
Large Roughness

Influence of the surface geometry variations on the flow in a low-pressure turbine outlet guide vane cascade is studied experimentally and numerically. Experiments are performed in a linear cascade facility at Chalmers, and numerical simulations are carried out at the rig conditions using steady RANS equations. Investigated surface nonconformances are specially designed two- and three-dimensional surface roughness elements which simulate a generic welding trace and a surface repair patch. These surface modifications were implemented on the cascade vanes at different surface locations, and the aerodynamics of the cascade with geometry deviations was compared to the baseline case without them. Investigated characteristics include the cascade performance in terms of the total pressure loss and flow turning angle as well as a detailed description of the downstream development of the secondary flow field. It is found that there is a range of locations on the vane surface where even relatively large roughness elements as were investigated (with height up to 20% of the blade maximum thickness) do not affect the OGV performance significantly. Another range of locations, where the effect is critical and the flow separation is triggered, are identified as well. An accurate prediction of the separation margins in the latter case was found a challenging task for turbulence models.

A Three-Dimensional CFD Design Study of a Circulation Control Inlet Guide Vane for a Transonic Compressor

2009 ◽  
Author(s):  
Sandra L. Gunter ◽  
Stephen A. Guillot ◽  
Wing F. Ng ◽  
S. Todd Bailie
Keyword(s):  
Guide Vane ◽  
Three Dimensional ◽  
Inlet Guide Vane ◽  
Manufacturing Cost ◽  
Optimization Approach ◽  
Circulation Control ◽  
Operational Parameters ◽  
Trailing Edge ◽  
Transonic Compressor ◽  
Optimization Parameters

A three-dimensional computational investigation was conducted to evaluate the performance of a circulation control inlet guide vane (IGV) designed for a transonic compressor test rig. The general configuration of the IGV is an uncambered airfoil designed to exploit the Coanda effect for flow turning through the use of a jet that exhausts along a curved trailing edge. Computational fluid dynamics (CFD) was used in conjunction with an optimization approach to design an IGV that balances performance potential with manufacturing cost and complexity. Optimization parameters include geometry specifications such as jet height and trailing edge radius, as well as operational parameters such as jet supply pressure and inlet Mach number. The potential for positive flow turning was shown for all geometries examined. Operational goals such as increased turning at lower off-design inlet Mach numbers were demonstrated, and an optimum configuration was established.

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