Advances in axial turbine blade profile aerodynamics-Reference-Cited by-同舟云学术

Advances in axial turbine blade profile aerodynamics

Published:2020-06-28 Issue:4 Volume:235 Page:652-669
ISSN:0954-4062
Container-title:Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science
language:en
Short-container-title:Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science

Author:

Gao Jie¹²³^ORCID,Huo Dongchen¹,Wang Guojie¹,Ma Guojun¹

Affiliation:

1. College of Power and Energy Engineering, Harbin Engineering University, Harbin, China

2. Center for Post-Doctoral Studies, Chongqing University, Chongqing, China

3. Center for Post-Doctoral Research, Chongqing Jiangjin Shipbuilding Industry Co., Ltd, Chongqing, China

Abstract

The aerodynamic performance of axial turbines depends significantly on profile losses, secondary flow losses, and clearance gap losses of vanes and blades. In modern high-efficiency turbomachinery operating at various working conditions, profile losses are very important criteria for the development of vanes and blades, and turbine designers strive to minimize the losses, based on better understandings of flow and loss characteristics at various working conditions. This paper summarizes recent advances in the field of turbine blade profile aerodynamics, and covers: (1) flow and loss characteristics of blade profiles, (2) flow structure and loss mechanism for transonic blade profiles, (3) off-design performance, (4) flow control, (5) design and optimization, (6) engineering design considerations, and (7) research methods of blade profile aerodynamics. The emphasis is placed on flow characteristics and loss control methods, and present insights regarding the current research trends and the prospects for future developments.

Funder

National Natural Science Foundation of China

Publisher

SAGE Publications

Subject

Mechanical Engineering

Link

http://journals.sagepub.com/doi/pdf/10.1177/0954406220936316

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