Blade cooling is a relevant topic in the design of modern gas turbine engines, because of the increase in performance due to the resulting increase in the inlet turbine temperature is counteracted by a corresponding decrease due to the air extraction from the high-p compressor. In this paper, a previous model published by De Paepe & Dick is revisited and extended: while the original model consi...

This thesis presents a simple, meanline analysis of the impact of blade roughness on the mass flow, work coefficient, and efficiency of a three-stage axial compressor as a function of the location of fouling. First, an extensive review is presented on the state-ofthe-art of measuring compressor degradation and on the impact of roughness on loss and deviation in a compressor cascade. The perform...

In this multidisciplinary study a geared open rotor configuration is assessed and compared to an ultra high bypass ratio geared turbofan engine. Both designs assume a 2020 entry into service level of technology. The specific thrust level for minimizing block fuel and the resulting engine emissions for a given mission is sought. The tool used contains models that effectively capture: engine perf...

In the current work, different methods for optimization of turbine blade internal cooling are investigated, to achieve higher cyclic efficiency and output power for a typical gas turbine. A simple two-dimensional model of C3X blade is simulated and validated with available experimental data. The optimization process is performed on this model with two different methods. The first method is ...

An automated, multi-disciplinary optimization procedure for sub-sonic gas turbine compressor blades is presented. Evolutionary optimization algorithms are coupled with existing tools for geometry generation, mechanical integrity analysis and Q3D flow analysis for design and off-design conditions. Aerodynamic and mechanical objectives and constraints are formulated based on the standard design c...

This paper focuses on the conceptual design of a two spool compressor for the NASA Large Civil Tilt Rotor engine, which has a design-point pressure ratio goal of 30:1 and an inlet weight flow of 30.0 lbm/sec. The compressor notional design requirements of pressure ratio and low-pressure compressor (LPC) and high pressure ratio compressor (HPC) work split were based on a previous engine system s...

This paper presents a methodology for conducting a 3-D static fracture analysis with applications to a gas turbine compressor blade. An open crack model is considered in the study and crack-tip driving parameters are estimated by using 3-D singular crack-tip elements in ANSYS . The static fracture analysis is verified with a special purpose fracture code (FRANC3D). Once the crack front is perfe...

In this paper non-synchronous vibration (NSV) of a GE axial compressor is simulated using a fully coupled fluid/strcuture interaction (FSI). Time accurate NavierStokes equations are solved with a system of 5 decoupled structure modal equations in a fully coupled manner. A 3rd order WENO scheme for the inviscid flux and a 2nd order central differencing for the viscous terms are used to resolve n...

Though the importance of curvature continuity on compressor blade performances has been realized, there are two major questions that need to be solved, i.e., the respective effects of curvature continuity at the leading-edge blend point and the main surface, and the contradiction between the traditional theory and experimental observations in the effect of those novel leading-edge shapes with s...

A four-blade-passage numerical model was developed for a two-stage axial-flow compressor with an inlet guide vane (IGV) the purpose of studying steady and dynamic characteristics approaching its stability limit. The flow-field information indicated that tip-leakage flow decreased more rapidly from blade’s leading edge to trailing edge, decreasing rate. leakage verified be driven via blade load ...