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Multidisciplinary design of a three stage high speed booster

Lejon, Marcus; Gronstedt, Tomas; Glodic, Nenad; Petrie-Repar, Paul; Genrup, Magnus LU and Mann, Alexander (2017) ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017 In Turbomachinery 2B-2017.
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... (More)

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.

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Please use this url to cite or link to this publication:
author
organization
publishing date
type
Chapter in Book/Report/Conference proceeding
publication status
published
subject
in
Turbomachinery
volume
2B-2017
publisher
American Society Of Mechanical Engineers (ASME)
conference name
ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
external identifiers
  • scopus:85029007233
ISBN
9780791850794
DOI
10.1115/GT2017-64466
language
English
LU publication?
yes
id
91184f71-0d0d-4fd1-aff8-c3dc36155acc
date added to LUP
2017-09-28 07:30:07
date last changed
2018-01-07 12:19:50
@inproceedings{91184f71-0d0d-4fd1-aff8-c3dc36155acc,
  abstract     = {<p>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.</p>},
  author       = {Lejon, Marcus and Gronstedt, Tomas and Glodic, Nenad and Petrie-Repar, Paul and Genrup, Magnus and Mann, Alexander},
  booktitle    = {Turbomachinery},
  isbn         = {9780791850794},
  language     = {eng},
  publisher    = {American Society Of Mechanical Engineers (ASME)},
  title        = {Multidisciplinary design of a three stage high speed booster},
  url          = {http://dx.doi.org/10.1115/GT2017-64466},
  volume       = {2B-2017},
  year         = {2017},
}