Effect of rotor–stator rim cavity flow on the turbine
Author:
Jia Xingyun1, Wang Wenhao1, Shi Hongrui2, Zhang Le1, He Lidong1
Affiliation:
1. College of Mechanical and Electrical Engineering, Beijing University of Chemical Technology , Beijing , 100029 , P. R. China 2. AECC Harbin Dongan Engine Co., Ltd , Harbin , 150066 , P. R. China
Abstract
Abstract
Relative high pressure in the rotor–stator (RS) cavity helps to improve its seal effectiveness. However, every 1% increase in the cavity flow results in a decrease of the stage power of turbine by about 0.32% and a decrease in the aerodynamic efficiency by about 0.33%. With rim cavity flow, the pressure distribution in the suction side of rotor blade domain and the turbine flow structure show obvious circumferential differences, which are caused by the interactions between the RS cavity flow and the mainstream. The flow characteristic in the false externally-induced ingress in rim clearance is proposed for the first time to reveal the flow mechanism in the effect of RS rim cavity flow on the turbine.
Funder
National Science and Technology Major Project China Postdoctoral Science Foundation Fundamental Research Funds for the Central Universities
Publisher
Walter de Gruyter GmbH
Subject
Aerospace Engineering
Reference24 articles.
1. Young, C, Smout, PD. Recent advances in the simulation of gas turbine secondary air systems. In: 25th congress of the international council of the aeronautical sciences, Hamburg; 2006. 2. Smout, PD, Chew, JW, Childs, P. ICAS-GT: a European collaborative research programme on internal cooling air systems for gas turbines. In: ASME turbo expo: power for land, sea, & air, Amsterdam; 2002. https://doi.org/10.1115/gt2002-30479. 3. Childs, P, Dullenkopf, K, Bohn, D. Internal air systems experimental rig best practice. In: ASME turbo expo 2006: power for land, sea and air, Barcelona; 2006. https://doi.org/10.1115/gt2006-90215. 4. Coren, DD, Atkins, NR, Turner, JR, Eastwood, DE, Davies, S, Childs, PRN, et al.. An advanced multi configuration turbine stator well cooling test facility. In: ASME turbo expo 2010, Glasgow; 2010. https://doi.org/10.1115/gt2010-23450. 5. Valencia, AG, Dixon, JA, Guardini, A, Coren, DD, Eastwood, D. Heat transfer in turbine hub cavities adjacent to the main gas path including FE-CFD coupled thermal analysis. In: ASME turbo expo 2011, Vancouver; 2011.
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