### Skapa referens, olika format (klipp och klistra)

**Harvard**

Lejon, M., Grönstedt, T., Genrup, M., Glodic, N., Petrie-Repar, P. och Mann, A. (2017) *Multidisciplinary Design of a Three Stage High Speed Booster *.

** BibTeX **

@conference{

Lejon2017,

author={Lejon, Marcus and Grönstedt, Tomas and Genrup, Magnus and Glodic, Nenad and Petrie-Repar, Paul and Mann, Alexander},

title={Multidisciplinary Design of a Three Stage High Speed Booster },

booktitle={ASME Turbo Expo 2017: Turbine Technical Conference and Exposition},

isbn={978-0-7918-5079-4},

abstract={The paper describes a multidisciplinary conceptual design of an axial compressor, targeting a three stage, high speed, high efficiency booster with a design pressure ratio of 2.8. The paper is outlined in a step wise manner starting from basic aircraft and engine thrust requirements, establishing the definition of the high speed booster interface points and its location in the engine. Thereafter, the aerodynamic 1D/2D design is carried out using the commercial throughflow tool SC90C. A number of design aspects are described, and the steps necessary to arrive at the final design are outlined. The SC90C based design is then carried over to a CFD based conceptual design tool AxCent, in which a first profiling is carried out based on a multiple circular arc blade definition. The design obtained at this point is referred to as the VINK compressor. The first stage of the compressor is then optimized using an in-house optimization tool, where the objective functions are evaluated from detailed CFD calculations. The design is improved in terms of efficiency and in terms of meeting the design criteria put on the stage in the earlier design phases. Finally, some aeromechanical design aspects of the first stage are considered. The geometry and inlet boundary conditions of the compressor are shared with the turbomachinery community on a public server. This is intended to be used as a test case for further optimization and analysis.},

year={2017},

keywords={Design, Compressor, Optimization},

}

** RefWorks **

RT Conference Proceedings

SR Print

ID 251303

A1 Lejon, Marcus

A1 Grönstedt, Tomas

A1 Genrup, Magnus

A1 Glodic, Nenad

A1 Petrie-Repar, Paul

A1 Mann, Alexander

T1 Multidisciplinary Design of a Three Stage High Speed Booster

YR 2017

T2 ASME Turbo Expo 2017: Turbine Technical Conference and Exposition

SN 978-0-7918-5079-4

AB The paper describes a multidisciplinary conceptual design of an axial compressor, targeting a three stage, high speed, high efficiency booster with a design pressure ratio of 2.8. The paper is outlined in a step wise manner starting from basic aircraft and engine thrust requirements, establishing the definition of the high speed booster interface points and its location in the engine. Thereafter, the aerodynamic 1D/2D design is carried out using the commercial throughflow tool SC90C. A number of design aspects are described, and the steps necessary to arrive at the final design are outlined. The SC90C based design is then carried over to a CFD based conceptual design tool AxCent, in which a first profiling is carried out based on a multiple circular arc blade definition. The design obtained at this point is referred to as the VINK compressor. The first stage of the compressor is then optimized using an in-house optimization tool, where the objective functions are evaluated from detailed CFD calculations. The design is improved in terms of efficiency and in terms of meeting the design criteria put on the stage in the earlier design phases. Finally, some aeromechanical design aspects of the first stage are considered. The geometry and inlet boundary conditions of the compressor are shared with the turbomachinery community on a public server. This is intended to be used as a test case for further optimization and analysis.

LA eng

DO 10.1115/GT2017-64466

OL 30