Loading...

Performance enhancement in transonic axial compressors using blade tip injection coupled with casing treatment

Beheshti, B. H ; Sharif University of Technology | 2005

361 Viewed
  1. Type of Document: Article
  2. DOI: 10.1243/095765005X28607
  3. Publisher: 2005
  4. Abstract:
  5. The casing treatment and flow injection upstream of the rotor tip are two effective approaches in suppressing instabilities or recovering from a fully developed stall. This paper presents numerical simulations for a high-speed transonic compressor rotor, NASA Rotor 37, applying a state-of-the-art design for the blade tip injection. This is characterized by introducing a jet flow directly into the casing treatment machined into the shroud. The casing treatment is positioned over the blade tip region and exceeds the impeller axially by ∼30 per cent of the tip chord both in the upstream and in the downstream directions. To numerically solve the governing equations, the three-dimensional finite element based finite volume method CFD solver CFX-TASCflow (version 2.12.1) is employed. For a compressible flow with varying density, Reynolds-averaging leads to appearance of complicated correlations. To avoid this, the mass-weighted or Favre-averaging is applied. Using an injected mass flow of 2.4 per cent of the annulus flow, the present design can improve stall margin by up to 7 per cent when compared with a smooth casing compressor without tip injection. This research can lead to an optimum design of recirculating casing treatments or other mechanisms for performance enhancement applying tip flow injection. © IMechE 2005
  6. Keywords:
  7. Computer simulation ; Correlation methods ; Equations of motion ; Finite element method ; Finite volume method ; Flow of fluids ; Jets ; Reynolds number ; Rotors ; Turbomachine blades ; Blade tip injection ; Casing treatment ; Flow injection upstream ; Injected mass flow ; NASA Rotor 37 ; Performance enhancement ; Stability improvement ; Transonic axial compressors ; Compressors ; Axial compressor ; Blade ; Computational fluid dynamics ; Turbomachinery
  8. Source: Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy ; Volume 219, Issue 5 , 2005 , Pages 321-331 ; 09576509 (ISSN)
  9. URL: https://journals.sagepub.com/doi/10.1243/095765005X28607