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Two-section type pre-compression central arced curve blade profile structure

An arc-blade, pre-compression technology, applied in non-variable volume pumps, non-displacement pumps, components of pumping devices for elastic fluids, etc., can solve the problem of small flow capacity, insufficient pressurization capacity, Unable to meet the design requirements of high-load fan rotor blades and other problems, to achieve the effect of large flow capacity, strong supercharging capacity, and small lag angle

Active Publication Date: 2016-04-06
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, most of the mid-arc forms are suitable for subsonic, transonic, and supersonic flow fields with a Mach number lower than 1.5. For the supersonic rotor design with a Mach number exceeding 1.5, there is no suitable mid-arc blade in engineering. Type exists, while the application of conventional blade type shows shortcomings such as insufficient boosting capacity and small flow capacity, which cannot meet the design requirements of high-load fan rotor blades

Method used

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  • Two-section type pre-compression central arced curve blade profile structure
  • Two-section type pre-compression central arced curve blade profile structure
  • Two-section type pre-compression central arced curve blade profile structure

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Embodiment 1

[0022] The invention provides a two-stage pre-compressed mid-arc airfoil structure, which is characterized in that: the two-stage pre-compressed mid-arc airfoil structure, the mid-arc airfoil is formed according to the difference of the inlet Mach number Two types, Ma = 0.8 ~ 1.2 across the range, the use of double-arc leaf type, the center line is a whole section of arc; The two arcs have the same slope at the transition point. When the Mach number exceeds 1.4, the shock loss is intensified, and the back and front of the blade are made into a concave shape to reduce the Mach number of the wave front, control the shock wave intensity, and reduce the shock wave loss. This blade shape is called a pre-compression blade shape.

[0023] Taking the maximum pre-compression point of the relative bending angle of the airfoil as the dividing point, the middle arc is divided into front and rear sections, and the front and rear sections adopt different relative bending angle changes, refe...

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Abstract

Provided is a two-section type pre-compression central arced curve blade profile structure. Central arced curve blade profiles have multiple types according to different inlet Mach numbers, the dual-arc blade profile is adopted in a transonic region with the Ma being equal to 0.8-1.2, and a whole arc serves as the central line; the multi-arc blade profile is adopted in a supersonic region with the Ma being equal to 1.2-1.4, the central line is composed of two arcs, and the slopes of the two arcs are identical at a transition point. When the Mach number is larger than 1.4, shock wave loss increases, the front section of the blade back is concave so as to reduce the wave-front Mach number, the shock wave strength is controlled, and the shock wave loss is reduced, namely the pre-compression blade profile is adopted. The central arced curve is divided into a front section and a rear section with the maximum pre-compression point of a blade profile relative bend as the demarcation point, and different relative bend changing laws are adopted by the front section and the rear section respectively. The two-section type pre-compression central arced curve blade profile structure has the advantages that the pressurizing capacity is high, the flow capacity is high, the deviation angle is small, the higher pre-compression quantity and the larger pre-compression section length are selected, and the two-section type pre-compression central arced curve blade profile structure is suitable for the design of hypersonic-speed rotors.

Description

technical field [0001] The invention relates to the field of fans and aerodynamics, in particular to a two-stage precompressed arc blade structure. Background technique [0002] The arc of the blade shape is the basis of the shape of the blade and plays a decisive role in the performance of the blade shape. When designing the blade shape, the matching arc of the blade shape should be adopted according to the corresponding Mach number of the different incoming flow. At present, most of the mid-arc forms are suitable for subsonic, transonic, and supersonic flow fields with a Mach number lower than 1.5. For the supersonic rotor design with a Mach number exceeding 1.5, there is no suitable mid-arc blade in engineering. Type exists, while the application of conventional blade type shows shortcomings such as insufficient boosting capacity and small flow capacity, which cannot meet the design requirements of high-load fan rotor blades. Contents of the invention [0003] The purp...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D29/26F04D21/00
Inventor 单玉姣郑宁
Owner AECC SHENYANG ENGINE RES INST
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