contributor author | ZhiHong Zhou | |
contributor author | HuoXing Liu | |
contributor author | Kun Zhou | |
contributor author | Chao Li | |
date accessioned | 2022-01-30T19:59:27Z | |
date available | 2022-01-30T19:59:27Z | |
date issued | 2020 | |
identifier other | %28ASCE%29AS.1943-5525.0001095.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl1/handle/yetl/4266328 | |
description abstract | To support the design of a two-dimensional turbine blade profile with reduced shock loss, an efficient model for shock system with separation shock in highly loaded turbine cascade needed to be established to realize parameterized shock losses prediction and analysis. The discussions on the model demonstrate that the effect of base pressure on shock losses can be achieved by controlling the width of the base region (the region between the pressure surface and suction surface trailing edge separation points). Increasing the trailing-edge wedge angle can increase the base pressure as well as the width of the base region, thus reducing the shock losses. Moreover, the pressure change caused by reducing the suction surface curvature downstream of the throat can reduce the loss caused by the reflected shock. | |
publisher | ASCE | |
title | Shock System Model of Highly Loaded Turbine Cascade | |
type | Journal Paper | |
journal volume | 33 | |
journal issue | 1 | |
journal title | Journal of Aerospace Engineering | |
identifier doi | 10.1061/(ASCE)AS.1943-5525.0001095 | |
page | 04019107 | |
tree | Journal of Aerospace Engineering:;2020:;Volume ( 033 ):;issue: 001 | |
contenttype | Fulltext | |