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Multidisciplinary Design of a Three Stage High Speed Booster

Lejon, Marcus, 1986 (author)
Chalmers University of Technology
Grönstedt, Tomas, 1970 (author)
Chalmers University of Technology
Petrie-Repar, Paul (author)
KTH,Kraft- och värmeteknologi,KTH Royal Institute of Technology, Sweden,Kungliga Tekniska Högskolan (KTH),Royal Institute of Technology (KTH)
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Glodic, Nenad (author)
KTH,Kraft- och värmeteknologi,KTH Royal Institute of Technology, Sweden,Kungliga Tekniska Högskolan (KTH),Royal Institute of Technology (KTH)
Genrup, Magnus (author)
Lund University,Lunds universitet,Kraftverksteknik,Institutionen för energivetenskaper,Institutioner vid LTH,Lunds Tekniska Högskola,Thermal Power Engineering,Department of Energy Sciences,Departments at LTH,Faculty of Engineering, LTH
Mann, Alexander (author)
RISE,IVF,Swerea IVF
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 (creator_code:org_t)
ASME Press, 2017
2017
English.
In: ASME Turbo Expo 2017: Turbine Technical Conference and Exposition. - : ASME Press. ; 2B-2017
  • Conference paper (peer-reviewed)
Abstract Subject headings
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  • 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.

Subject headings

TEKNIK OCH TEKNOLOGIER  -- Maskinteknik (hsv//swe)
ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering (hsv//eng)
TEKNIK OCH TEKNOLOGIER  -- Maskinteknik -- Energiteknik (hsv//swe)
ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering -- Energy Engineering (hsv//eng)
TEKNIK OCH TEKNOLOGIER  -- Maskinteknik -- Strömningsmekanik och akustik (hsv//swe)
ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering -- Fluid Mechanics and Acoustics (hsv//eng)
TEKNIK OCH TEKNOLOGIER  -- Maskinteknik -- Rymd- och flygteknik (hsv//swe)
ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering -- Aerospace Engineering (hsv//eng)
TEKNIK OCH TEKNOLOGIER  -- Maskinteknik -- Annan maskinteknik (hsv//swe)
ENGINEERING AND TECHNOLOGY  -- Mechanical Engineering -- Other Mechanical Engineering (hsv//eng)

Keyword

Design
Optimization
Compressor

Publication and Content Type

kon (subject category)
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