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Nowadays industrial aerodynamic compressor design is based on mature computer programs developed during several decades. State of the art is to split the complex design process into subsequent design subtasks which are solved by different experts via time-consuming parameter studies. Isolated design of subproblems based on human intuition, however, will result in sub-optimal solutions only. Due to the increasing demand on higher aero engine performance and design cycle time reduction the aspects of process integration and automation as well as numerical optimization become more and more important in today’s aerodynamic compressor design. The intention of this work is to show how process integration and optimization can be used efficiently to support engineering design work in optimal solution finding. Since the aerodynamic compressor design is characterized by many design parameters, multiple constraints and contradicting objectives, multi-objective optimization is used to find Pareto-optimal solutions from which the design engineer can choose trade-offs for his particular design problem. The improvements in terms of process acceleration and design optimization are demonstrated for three selected, but typical industrial engineering design tasks required in three different design phases of the aerodynamic compressor design process, namely preliminary design, throughflow off-design, and blading procedure.
By offering good ride safety and ride comfort to passenger cars, active suspensions have attracted more and more attentions of investigators. Numerous approaches of designing controller for active suspension systems have been introduced mostly restricted to linear time-invariant systems. In this dissertation, optimization methods are applied to a special three degree-of-freedom spatial car model with active suspensions to define an optimal controller. The optimal control law with state-feedback and disturbance-feed forward parts is derived by extending the linear-quadratic regulator (LQR) control to linear systems with measurable disturbances and combining it with a multi-criterion optimization (MCO) procedure. This allows to reduce the number of design variables of the MCO problem significantly. The approach is applied also to gain-scheduling control of the linear-parameter varying spatial car model. The effectiveness of the designed controller with respect to ride safety and ride comfort of the car in yaw motion is demonstrated through the simulation of double-lane-change maneuvers, where the paths are found by an optimization procedure.
For many countries, gasturbine technology is one of the key technologies for the reduction of climate-damaging pollutant emissions. The profitability of such facilities, however, is highly dependent on the price for the utilized fossil fuel, which is why there is a constant need for increased efficiency. The potential of increasing the efficiency of the individual components is basically limited by factors which will reduce operating life. The goal of this thesis is to develop methods for improved automated structural design optimization, which shall be developed on the basis of compressor airfoils. Special attention is payed to avoid the excitation of failure critical eigenmodes by detecting them automatically. This is achieved by introducing a method based on self-organizing neural networks which enables the projection of eigenmodes of arbitrary airfoil geometries onto standard surfaces, thereby making them comparable. Another neural network is applied to identify eigenmodes which have been defined as critical for operating life. The failure rate of such classifiers is significantly reduced by introducing a newly developed initialization method based on principle components. A structural optimization is set up which shifts the eigenfrequency bands of critical modes in such a way that the risk of resonance with engine orders is minimized. In order to ensure practical relevance of optimization results, the structural optimization is coupled with an aerodynamic optimization in a combined process. Conformity between the loaded hot-geometry utilized by the aerodynamic design assessment and the unloaded cold-geometry utilized by the structural design assessment is ensured by using loaded-to-unloaded geometry transformation. Therefor an innovative method is introduced which, other than the established time-consuming iterative approach, uses negative density for a direct transformation taking only a few seconds, hence, making it applicable to optimization. Additionally, in order for the optimal designs to be robust against manufacturing variations, a method is developed which allows to assess the maximum production tolerance of a design from which onwards possible design variations are likely to violate design constraints. In contrast to the usually applied failure rate, the production tolerance is a valid requirement for suppliers w.r.t.~expensive parts produced in low-quantity, and therefore is a more suitable optimization objective.
Surface variations are an unavoidable byproduct of any manufacturing process and may lead to deviating part performance and even elevated part rejection rates. Because traditional computer aided-design approaches are aimed towards production of idealized, nominal geometric shapes, the wide geometric-and statistical-variability typical for any manufacturing process remains unrepresented and is frequently ignored during design. Thus, the present work aims at a more realistic design approach and, therefore, develops a collection of computer-aided design strategies for accurate representation, statistical analysis and prospective estimation of surface deviations with validation examples on aero engine turbine blades.
The CAD representation of real manufactured surfaces requires the ability to accurately recreate complex geometric shapes. This is achieved by automated re-parametrization of any CAD face of interest as B-spline surface with a rather dense control point grid. Face matching to scanned manufactured samples is then performed by calculating control point displacements, which successfully deliver surface representation errors below typical measurement uncertainties on multiple matching examples from turbine shank and hot-gas faces. Since inference of performance variability due to manufacturing is usually limited by the amount of scanned manufactured parts, a probabilistic model is formulated based on singular-value decomposition of control point displacements and identification of dominant manufacturing modes. This allows generation of an infinite set of synthetic deviating surfaces faithful to experimental deviation patterns.
Nominal geometric features may significantly differ between design iterations and manufacturing modes may not necessarily be transferable between different designs. Thus, deviation estimation may remain infeasible before manufacturing. To enable deviation estimation during the design phase, the present work proposes a machine learning strategy to identify deviation patterns explained by nominal geometric properties-such as relative position and local orientation-and use them for deviation estimation on new designs. This strategy is able to predict realistic stress variability induced by shank deviations of a turbine blade design using only surface deviation information from three given designs, which encourages machine-learning approaches as valuable tool for geometric deviation estimation as part of robust design.