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Gas compressor stationary blade cascade with equal-width linear groove formed in blade root

A technology for compressors and sub-leaf cascades, which is applied in passive flow control, a flow control scheme for the blade root of a compressor stator cascade, and the flow control field of a compressor stator cascade, which can solve the slotting scheme to connect the arcs randomly and control the The solution is difficult to optimize the design, lack of design guidelines and other problems, to achieve the effect of convenient optimization design, good engineering application prospects, and easy processing

Active Publication Date: 2015-12-23
BEIHANG UNIV
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  • Claims
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Problems solved by technology

The above-mentioned technology has at least the following disadvantages: For engineering applications, the connecting arc of the slotting scheme is relatively random, which is not easy to process; there are too many control parameters, and the lack of design criteria makes it difficult to optimize the design of the control scheme

Method used

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  • Gas compressor stationary blade cascade with equal-width linear groove formed in blade root
  • Gas compressor stationary blade cascade with equal-width linear groove formed in blade root
  • Gas compressor stationary blade cascade with equal-width linear groove formed in blade root

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Embodiment Construction

[0024] Specific embodiments of the present invention will be described below in conjunction with the accompanying drawings.

[0025] Such as figure 1 As shown, the compressor stator cascade with equal-width linear grooves on the blade root has equal-width linear grooves 5 on the end wall 2 of the root of the cascade 1 from the pressure surface 3 to the suction surface 4 of the cascade 1 .

[0026] Such as figure 2 As shown, according to the PVD prototype stator cascade flow field, the position of the outlet of the channel 5 on the suction surface 4 is selected before the separation point; along the axial direction of the cascade, the position of the inlet of the channel 5 on the pressure surface 3 is located on the suction surface 4 Upstream of the outlet position; according to the pressure distribution on the surface of the PVD prototype stator cascade, the position of the inlet of the channel 5 on the pressure surface 3 is selected at the place where the static pressure on...

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Abstract

The invention provides a gas compressor stationary blade cascade with an equal-width linear groove formed in a blade root and relates to the passive flow control technology in the technical field of turbomachinery. By means of the gas compressor stationary blade cascade, the equal-width linear groove is formed in the blade root end wall of the gas compressor stationary blade cascade from the pressure face to suction face, and jet flow is formed through detour flow pressure differentials of a blade, so that flow separation is restrained and delayed. The groove is located in the blade root end wall of the gas compressor stationary blade cascade. The spanwise height is a constant value. The inlet of the groove is located in the pressure face of the stationary blade cascade. The outlet of the groove is located in the suction face of the blade cascade. The center line of the groove is a straight line and equidistant from the two side walls of the groove. The gas compressor stationary blade cascade has the beneficial effects that corner separation is restrained; the flow capacity of the blade cascade is increased; the total pressure loss is reduced; the diffusion capacity is improved.

Description

technical field [0001] The invention relates to the flow control of a stator cascade of a compressor, in particular to a flow control scheme for slotting a blade root of a stator cascade of a compressor to suppress the angular separation of the compressor stator, and belongs to the passive flow control technology in the technical field of impeller machinery. Background technique [0002] Among the internal flow of turbomachinery, the most complicated flow is the flow in the corner area. The end wall boundary layer, blade boundary layer, various vortex structures and their interactions exist in the corner flow between the suction surface and the end wall, which are the main factors that cause the performance deterioration of the compressor stator. The flow separation in the corner area will lead to channel blockage, blade load and diffuser capacity reduction, resulting in total pressure loss and efficiency reduction, and in severe cases, it will cause engine surge. The flow ...

Claims

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Application Information

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IPC IPC(8): F04D29/54
CPCF04D29/682F04D29/684
Inventor 柳阳威唐雨萌陆利蓬孙槿静
Owner BEIHANG UNIV
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