Nasze serwisy używają informacji zapisanych w plikach cookies. Korzystając z serwisu wyrażasz zgodę na używanie plików cookies zgodnie z aktualnymi ustawieniami przeglądarki, które możesz zmienić w dowolnej chwili. Więcej informacji odnośnie plików cookies.

Obowiązek informacyjny wynikający z Ustawy z dnia 16 listopada 2012 r. o zmianie ustawy – Prawo telekomunikacyjne oraz niektórych innych ustaw.

Wyłącz komunikat

 
 

Logowanie

Logowanie za pomocą Centralnej Usługi Uwierzytelniania PRz. Po zakończeniu pracy nie zapomnij zamknąć przeglądarki.

Mechanika

Mechanika
86 (1/14), DOI: 10.7862/rm.2014.16

Transonic axial compressor active boundary layer control concept and its evaluation

Bartosz Ziegler

DOI: 10.7862/rm.2014.16

Abstract

The article presents a concept of boundary layer control in transonic axial compressors. Two methods for obtaining boundary layer control are presented. It is proposed that by combining those two methods, an efficient way of preventing turbulent boundary layer separation in transonic compressor passages can be obtained without the loss of the compressor flux. The concept, is based on the idea of removing boundary layer flows at one stage, and using this removed flux as a blowing type boundary layer control, at previous stage where lower pressures occur. This creates a loop of secondary flow between those stages preventing the boundary layer separation (especially the shock induced separation) on both stages. Two dimensional numerical analyses are performed to assess the possible passage performance (especially the diffusion factor). On the basis of two dimensional analyses, the possible performance of such compressor stage is estimated. The aerodynamic possibility of greatly increasing the axial compressing stage loadings and pressure ratios without increasing blade velocities and passage flow Mach numbers is shown. This possibility has a growing importance as the overall pressure ratio of turbojet engines and tends to rise with every next engine generation. Main conclusions are drawn, showing the possibilities for further research in the scope of this concept.

Full text (pdf)

References

  1. Kerrebrock J. : Final Technical Report on AFOSR Grant F49620-98-1-0493 entitled RESEARCH AND DEVELOPMENT ON ASPIRATED COMPRESSORS, Gas Turbine Laboratory Department of Aeronautics and Astronautics MIT, Cambridge 2003.
  2. Epstein A. et al. : Final Technical Report on AFOSR Grant F49620-03-1-0309 entitled ASPIRATED HIGH PRESSURE COMPRESSOR, Gas Turbine Laboratory Department of Aeronautics and Astronautics MIT, Cambridge 2006.
  3. Knapke R.D., Turner M.G.: Detailed Unsteady Simulation of a Counterrotating Aspirated Compressor with a Focus on the Aspiration Slot and Plenum, Int. J. Rotating Machinery, 2013, Article ID 857617.
  4. Colombo E. et al.: Investigations on axial compressor cascades with aspiration on blades and hub, European Workshop on New Aero Engine Concepts, Munich 2010.

About this Article

TITLE:
Transonic axial compressor active boundary layer control concept and its evaluation

AUTHORS:
Bartosz Ziegler

AUTHORS AFFILIATIONS:
Poznań University of Technology, ul. Piotrowo 3, 60-695 Poznań

JOURNAL:
Mechanika
86 (1/14)

KEY WORDS AND PHRASES:
flow separation, transonic diffusers, turbojet engines

FULL TEXT:
http://doi.prz.edu.pl/pl/pdf/mechanika/77

DOI:
10.7862/rm.2014.16

URL:
http://dx.doi.org/10.7862/rm.2014.16

RECEIVED:
2014-05-15

COPYRIGHT:
Publishing House of Rzeszow University of Technology Powstańców Warszawy 12, 35-959 Rzeszow

POLITECHNIKA RZESZOWSKA im. Ignacego Łukasiewicza; al. Powstańców Warszawy 12, 35-959 Rzeszów
tel.: +48 17 865 11 00, fax.: +48 17 854 12 60
Administrator serwisu:

Deklaracja dostępności | Polityka prywatności