This paper presents the results of the experimental investigations on the effects of leaned and curved blade of plane axial compressor cascade. The ink trace method has been used for the surface flow visualization. The five-hole probe measurements are performed at the cascade exit 12.5 percent chord downstream, and the static pressure distributions are measured on the endwalls and blade surfaces.Copyright © 1993 by ASME

The experimental investigations on the compressor cascades with leaned and curved blade

This paper presents a parametric study of ice accretion on a high bypass turbofan engine booster rotor. Both flow and droplets' governing equations are formulated and solved in the reference frame of the rotating blades. A Eulerian-Lagrangian approach is used for the continuous and discrete phases with one-way interaction model to simulate momentum and energy exchange on the droplets and their effects on the three-dimensional droplet trajectories. The flux-based collection efficiency is calculated for the rotor blade at 60%, 70%, 80%, 90% and 100% engine design speed. A quasi-3D analysis of the ice accretion over the rotor blade is conducted based on the computed flow characteristics using the code LEWICE. Results are presented for the ice shape variation along the span, inlet temperature and rotor speeds. The highest accumulation was predicted on the blade pressure side leading edge near the hub and increased with reduced rotor speed and flow temperature.

Ice Shape Prediction For Turbofan Rotating Blades

An equation and numerical solution procedure for a steady-state aerodynamic analysis of a turbofan engine in the meridional plane is presented. An axisymmetric average of the three-dimensional fluid flow equations within the engine is presented. The equations simultaneously represent the major engine components and include terms for blade forces, loss, combustor heat addition, blockage, bleeds and convective mixing in the mixer. These general equations are specialized with modeled terms and advanced to a steady-state with a time-marching scheme on a multi-block grid. The procedure is verified with comparisons to one-dimensional analytic solutions and a compressor stage. How this procedure can capture component interactions is demonstrated with a solution for General Electric’s Energy Efficient engine, which is representative of modern turbofan engines.Copyright © 1995 by ASME

Axisymmetric Aerodynamic Numerical Analysis of a Turbofan Engine

The two-dimensional through-flow modeling of turbomachinery is still one of the most powerful tools available to the turbomachinery industry for aerodynamic design, analysis, and post-processing of test data due to its robustness and speed. Although variety of aspects of such a modeling approach are discussed in the publicly available literature for compressors and turbines, not much emphasis is placed on combined modeling of the fan and the downstream splitter of turbofan engines. The current article addresses this void by presenting a streamline curvature through-flow methodology that is suitable for inverse design for such a problem. A new split-flow method for the streamline solver, alternative to the publicly available analysis-oriented method, is implemented and initially compared with two-dimensional axisymmetric computational fluid dynamics on two representative geometries for high and low bypass ratios. The empirical models for incidence, deviation, loss, and end-wall blockage are compiled from t...

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An extension of the streamline curvature through-flow design method for bypass fans of turbofan engines

A numerical investigation is conducted to study water droplet collection on a high bypass turbofan engine booster rotor under different rotational speeds. An Eulerian-Lagrangian approach is used in formulating the flow and droplet governing equations in the rotating reference frame. A one-way interaction model is used to model the effects of momentum and energy exchange effects with the flow on the droplets as they travel through the rotor. Results are presented for the computed flow field, droplet trajectories, water collection efficiency and droplet exit mass and temperature profiles at 60%, 70%, 80%, 90%, and 100% design rotational speeds. The highest collection is predicted near the tip at the pressure surfaces leading edge. It then drops considerably at 40%–60% of the booster rotor blade chord and remains low over the aft portion of the pressure side. In general, the rotor blade collection efficiency is strongly influenced by rotor speed and increases as the rotational speed decreases.Copyright © 2006 by ASME

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Droplet Trajectories and Collection on Fan Rotor at Off-Design Conditions

A single stage fan and quarter stage booster were designed for the energy efficient engine. The fan has an inlet radius ratio of 0.342 and a specific flow rate of 208.9 Kg/S sq m (42.8 lbm/sec sq ft). The fan rotor has 32 medium aspect ratio (2.597) titanium blades with a partspan shroud at 55% blade height. The design corrected fan tip speed is 411.5 M/S (1350 ft/sec). The quarter stage island splits the total fan flow with approximately 22% of the flow being supercharged by the quarter stage rotor. The fan bypass ratio is 6.8. The core flow total pressure ratio is 1.67 and the fan bypass pressure ratio is 1.65. The design details of the fan and booster blading, and the fan frame and static structure for the fan configuration are presented.

T. J. Sullivan

Papers

Energy efficient engine: Fan test hardware detailed design report