Aerodynamic Performance of an Annular Combustion Chamber Cooling with Swirler Design

• Dinh Cong-Truong

  Department of Aerospace Engineering, Hanoi University of Science and Technology

• Le Xuan-Truong

  Department of Aerospace Engineering, Hanoi University of Science and Technology

• Hoang Trong-Nghia

  Department of Aerospace Engineering, Hanoi University of Science and Technology

• Pham Quang-Anh

  Viettel Aerospace Institute

抄録

Gas turbines play a crucial role in the aviation industry as they are primary sources of power for most aircraft. The combustion chamber is one of the three essential part of jet engines, together with compressor and turbine. Energy is generated when fuel is burned in the combustor. In the primary zone, the recirculation flow is of great importance to aerodynamic performance. Swirlers, fitted in the dome around the fuel injector, can alter the behavior of the recirculation flow and thus, impact combustion performance. The vortex behind a swirler can be easily controlled by changing the swirl angle. In addition, changing the vortex angle leads to a difference in mixing between fuel and air. This paper investigates the effects of swirler design, based on the swirl angle, on aerodynamic performance of an annular combustion chamber in cooling condition using three-dimensional Reynolds-averaged Navier-Stokes equations with the SST turbulence model.

収録刊行物

• International Journal of Fluid Machinery and Systems

  International Journal of Fluid Machinery and Systems 14 (1), 1-12, 2021

  ターボ機械協会、韓国流体機械学会、中国工程熱物理学会、国際水理学会

キーワード

• Annular combustion chamber cooling
• Swirler design
• RANS analysis
• Overall pressure loss
• Swirl exit angle

詳細情報

• CRID: 1391131406304729216
• NII論文ID: 130007966978
• DOI: 10.5293/ijfms.2021.14.1.001
• ISSN: 18829554
• 本文言語コード: en
• データソース種別:
  • JaLC
  • Crossref
  • CiNii Articles
• 抄録ライセンスフラグ: 使用不可