桨扇发动机进气道/对转桨扇气动干扰影响

doi:10.7527/S1000-6893.2024.31042

Abstract

Abstract:

A study was conducted on the aerodynamic interference effects of Contra-Rotating Propfan （CRP） and propfan engine inlet. Unsteady numerical calculation was carried out by the sliding grid method， and the coupled aerodynamic effects of the 8X8 CRP and inlet were compared and analyzed under two typical operating conditions： the high-altitude cruising state and ground takeoff state. The mechanism and quantitative results of slipstream effects on inlet under different conditions， and differences of CRP aerodynamic performance before and after coupled inlet were summarized. Results indicate that the hub vortex produced by the CRP is the primary factor influencing the flow characteristics within the intake duct. Under the cruise condition， wake vortices of the rear row dominated the vortex structure of the inlet and cause non-uniform flowfield. Under the takeoff condition， the coupling of wake vortices of both front and rear rows was enhanced， leading to the presence of vortices in pairs. These paired vortices collectively impacted the flow field within the inlet. The periodic movement of wake vortices within the inlet induced periodic fluctuations in aerodynamic parameters. When propfan wake vortices dominated the vortex structure， the amplitude of parameter oscillations diminished along the duct， yet the oscillation frequency remained constant and the phase angle maintained a uniform lag. Following the detachment of wall-separated vortices， the duct’s vortex structure underwent changes， disrupting the amplitude， frequency， and phase angle of parameter oscillations due to the mixing of these separated vortices. The slipstream enhanced the total pressure of inlet； however， intricate trailing vortices significantly exacerbated the total pressure and swirl distortions at the duct's exit， leading to pronounced uneven internal flow distributions. Internal flow losses increased by 2.85 times during cruising and 1.09 times during takeoff. In addition， integration of the intake duct altered the internal flow field structure of the rear blade channel of the counter-rotating propfan. This results in a decrease in velocity within the channel， a forward shift in the position of the shock wave on the blade suction surface， and a modification of the operational characteristics of blade elements at varying heights. Consequently， this improved the thrust performance of the propeller fan. Under the design condition， the thrust coefficient of the front row blades rose by 5.9%， that of the rear row blades increased by 27%， and the overall efficiency of the propfan improved by 5.2%.

Key words: propfan engine, annular inlet, Contra-Rotating Propfan (CRP), inlet performance, slipstream

CLC Number:

V231.1

Haiyu ZHAO, Li ZHOU, Wenjian DENG, Zhanxue WANG. Aerodynamic interference effects of propfan engine inlet and contra-rotating propfan[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(8): 631042.

Figures/Tables 24

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	参数	数值
飞行条件	飞行高度/m	10 668
飞行条件	飞行马赫数	0.785
对转桨扇设计参数	前后排叶片数	8×8
	前后排转速/（r·min^-1）	900
	桨叶直径/m	4
	轮毂直径/m	1
进气道设计参数	流量系数	0.75
	质量流量/（kg·s^-1）	50
	进气道长度/m	1.5

工况	总压恢复系数	总压损失系数	总压畸变指数	旋流畸变指数
孤立进气道（巡航）	0.976	0.007		0.01
耦合桨扇（巡航）	1.043	0.027	0.039	0.277
孤立进气道（起飞）	0.988	0.011		0.008
耦合桨扇（起飞）	1.033	0.023	0.017	0.129

工况	前排推力系数	前排功率系数	后排推力系数	后排功率系数	桨扇效率
孤立桨扇	0.484	2.687	0.779	3.349	0.812
耦合进气道	0.512	2.784	0.990	4.037	0.854

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Aerodynamic interference effects of propfan engine inlet and contra-rotating propfan

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