TY - JOUR
AU - 
AB - energies Article The Analysis of Leading Edge Deformations on Turbomachine Blades 1 , 2 1 , 2 , Le Li and Huoxing Liu * School of Energy and Power Engineering, Beihang University, Beijing 100191, China; lile199087@163.com National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, Beihang University, Beijing 100191, China * Correspondence: liuhuoxing@buaa.edu.cn; Tel.: +86-10-8231-6418 Received: 29 January 2019; Accepted: 19 February 2019; Published: 22 February 2019 Abstract: With recent advancements in the development of material and manufacturing technology, the leading edge geometry of turbomachine blades has attracted widespread attention. “Sharp” leading edges always have a better aerodynamic performance, though it is prone to deformations easily. Thus, ﬂat plates and real compressor cascades with different leading edge deformations were investigated to study the inﬂuence, which is applicable for thin blades at low speeds. Different boundary layer characteristics, including the velocity proﬁle, transition process, and loss, are compared. The results show that there are several kinds of contradictory inﬂuence mechanisms and that the ﬁnal phenomenon is closely related to the condition of the original boundary layer. In low turbulence, with large and laminar separation, the deformations can suppress separation and decrease loss. In high turbulence, with short and transitional 
TI - The Analysis of Leading Edge Deformations on Turbomachine Blades
JF - Energies
DO - 10.3390/en12040736
DA - 2019-02-22
UR - https://www.deepdyve.com/lp/unpaywall/the-analysis-of-leading-edge-deformations-on-turbomachine-blades-hsz2lmG9dr
DP - DeepDyve
ER -