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- W98572522 abstract "The aim of this work is to develop a systematic approach for multidisciplinary highpressure transonic axial compressor conceptual design. Several aspects have to betaken into account when establishing a new compressor design. Apart fromdeveloping a successful aerodynamic design that provides high efficiency andmaintaining a design that allows manufacturing at a reasonable cost, structuraldynamics and rotor dynamic considerations have to be taken to ensure a mechanicallystable operation. It is quite common that a seemingly well designed compressorexhibits rotor dynamic instability at some rotational speed and that this requires redesigningthe machine.This report presents the initial results of a multidisciplinary conceptual design of afive stage transonic high pressure compressor that has an overall pressure ratio of4.46, an inlet temperature of 401.4K an inlet pressure of 132.9 kPa and a mass flowof 14.18 kg/s. Basic parameters such as blade masses, disc stress calculations andconceptual disc design were carried out using existing tools and analytical techniques.The work consists of setting up a basic Finite Element (FE) model using the ANSYSsoftware and subsequently a basic rotor dynamic model in the DyRoBeS tool. In orderto evaluate these parameters, basic aerodynamic theory of the axial flow compressorwas used.The work starts with a brief introduction to the fundamentals of gas turbine theory andresults in a basic aerodynamics design. The aerodynamic theory of axial flowcompressors is used to calculate design parameters such as temperatures and pressuresfor all stages, geometrical parameters, velocity triangles, etc. After the aerodynamiccalculation, weight and stress calculation for the compressor disks follows. Sinceweight is one of the most important parameters when designing a gas turbine engine,an accurate weight estimation method is desired. In the beginning of the designprocess, several different approaches can be used in order to achieve the samefunctionality. In this report, an approach similar to the weight estimation methodWATE (Weight Analysis of Turbine Engines) was used to calculate rotor and statorblade weights. Subsequent steps are comprised of modelling the disks. A preliminarydesign calculation is carried out in such a way that the whole disk is approximated asa superposition of several coupled elementary parts: a ring disc, a section withhyperbolic shape and a section with a linearly varying thickness. This basic non-linearanalytic procedure is followed by creating the basic FE model using the ANSYSsoftware to determine best shape of the bladed disc (blisc) and vibrationalcharacteristics of the blisc geometries. After this step, a basic rotor dynamic model inthe DyRoBeS tool is established to correctly continue the analysis and to learn thebehaviour of the compressor during operation at high speed." @default.
- W98572522 created "2016-06-24" @default.
- W98572522 creator A5013812554 @default.
- W98572522 date "2011-01-01" @default.
- W98572522 modified "2023-09-23" @default.
- W98572522 title "Multidisciplinary Conceptual Design of a Transonic High Pressure Compressor" @default.
- W98572522 hasPublicationYear "2011" @default.
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