[en] The novel approach to parametric topology of the 2D compressor airfoil was tested at multi-criteria optimisation problem for high speed subsonic application. Some results regarding the shape of the blade are presented. (paper)

[en] Blade flutter is one of the major problems that designers of modern gas-turbine engines face. In this paper, a study of the influence of the design parameters on prediction of blade flutter in compressors of gas-turbine engines is presented. As a rule, the flutter of compressor blades is predicted using simplified criteria based on the experience of designing and refining engines. These empirical and probabilistic criteria are not applicable to evaluation of the flutter since the parameters in question are not among the decisive parameters for simplified criteria. In this work, the energy method is used. It is shown that the inter-blade tension value has a significant influence on the blade flutter prediction, while the effect of other design parameters under investigation on the blade flutter prediction is insignificant. (paper)

[en] Although compressor blades have long been shrouded for aerodynamic and structural reasons, the importance of the leakage flow in the shrouded axial compressor has been investigated recently. However, the effects of the leakage tangential velocity variation on the blade passage flow are unknown. Therefore, this paper reports on an experimental investigation of the loss and flow turning in the blade passage in shrouded axial compressor cascades subject to the variation of the leakage tangential velocity. The newly found results are as follows. First, increasing the leakage tangential velocity reduces overall loss up to 32.6% compared to the reference case. Second, increasing the leakage tangential velocity spreads loss core in the pitch-wise direction. Thus, loss core becomes more two-dimensional. Third, increasing the leakage tangential velocity makes the near hub passage flow more radially uniform

[en] In this study, the axial-compressor-design and performance/flow analysis program is developed. A mean-line analysis was used to determine optimum arrangement of overall geometry and its off-design performance is predicted by stage-stacking method. Three dimensional blade shape is generated using radial equilibrium equation and vortex methods. Various blade shape is generated and their performance is compared. Finally the quasi-three dimensional flow analysis is applied to investigate the detailed flow phenomena

[en] The shock wave boundary layer interaction on the suction side of transonic compressor blade is one of main objectives of TFAST project (Transition Location Effect on Shock Wave Boundary Layer Interaction). In order to look more closely into the flow structure on the suction side of a blade, a design of a generic test section in linear transonic wind tunnel was proposed. The test section which could reproduce flow structure, shock wave location, pressure distribution and boundary layer development similar to the obtained on a cascade profile is the main objective of the presented here design. The design of the proposed test section is very challenging, because of shock wave existence, its interaction with boundary layer and its influence on the 3-D flow structure in the test section.

[en] In the present work the results of analytical models of performance are compared with experimental data acquired in the multi flux axial compressor test facility, built in The Pilcaniyeu Technological Complex for the SIGMA project.We describe the experimental circuit and the data of the dispersion inside the axial compressor obtained using a tracer gas through one of the annular inlets.The attained results can be used to validate the design code for the multi flux axial compressors and SIGMA industrial plant

[en] A self-recirculating casing treatment is designed for a transonic compressor stage and its performance at 100% rotational speed is numerically investigated. The casing treatment consists of 9 segments within every rotor blade pitch and each segment is built by one bleed port, one injection port and one bridge channel connecting the bleed and the injection ports. The coupled unsteady flow through the compressor blade passages and the casing treatment is simulated with a state-of-the-art CFD solver TRACE. At the stator-rotor and the treatment-rotor interfaces a conservative zonal approach and a conservative mixed-cell approach are applied, respectively, both of which are in second-order accuracy. The calculated results show that the self-recirculating casing treatment herein is able to effectively extend the stall margin by improving the flow conditions near the casing and by weakening the tip leakage flow. The casing treatment is also found to be able to reduce the incidence to the downstream stator blade near the casing thereby delaying the separation over the stator blade suction surface. (author)

[en] The article presents one optimization method for improving of the working process of an axial compressor of gas turbine engine. Developed method allows to perform search for the best geometry of compressor blades automatically by using optimization software IOSO and CFD software NUMECA Fine/Turbo. Optimization was performed by changing the form of the middle line in the three sections of each blade and shifts of three sections of the guide vanes in the circumferential and axial directions. The calculation of the compressor parameters was performed for work and stall point of its performance map on each optimization step. Study was carried out for seven-stage high-pressure compressor and three-stage low-pressure compressors. As a result of optimization, improvement of efficiency was achieved for all investigated compressors. (paper)

[en] This-paper presents analysis of the flows through three different types of radial compressor by using quasi-three-dimensional analysis method. The method obtains two-dimensional solution for velocity distribution on meridional plane, and then calculates approximately the static pressure distributions on blade surfaces. Finite difference method is used for the solutions of governing equations. The compressors have low level compression-ratio and 12 straight radial blades with no sweepback. The results are compared with experimental data and the results of inviscid analysis with finite element method. It can be concluded that the agreement is good for the cases where viscous effects are not dominant

[en] In this work, the process design and the economic feasibility of natural astaxanthin extraction fromHaematococcus pluvialisspecies have been reported. Complete process drawing of the process was first performed, and then the process was designed including five main steps being the harvesting process, the cell disruption, the spray drying, the supercritical CO₂extraction and the anaerobic digestion. The major components of the facility would include sedimentation tanks, a disk stack centrifuge, a bed miller, a spray dryer, a multistage compressor, an extractor, a pasteurizer and a digester. All units have been sized assuming a 10 kg/h of dried biomass as a feedstock to produce nearly 2592 kg of astaxanthin per year. The investment payback time and the return on investment were all estimated for different market prices of astaxanthin. Based on the results the production process was found to become economically feasible for a market price higher than 1500$/Kg. Also, a payback period of 1 year and an ROI equal to 113% was estimated for an astaxanthin market price equal to 6000$/Kg. (paper)