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Centrifugal compressor casing with large circumferential spacing and small through holes

A technology of centrifugal compressors and large intervals, which is applied in the direction of machines/engines, mechanical equipment, liquid fuel engines, etc., and can solve problems such as increased engine weight and cost, complex pipeline structure and control valves, and reduced compressor efficiency. The effect of convenient application and implementation and simple structure

Active Publication Date: 2020-11-10
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But its disadvantage is that the excitation intensity needs to be applied is very large, and the impact on the mainstream is obvious. While expanding the stability margin, the efficiency of the compressor will be reduced, and the complex pipeline structure and control valves are required, which increases the weight and cost of the engine.

Method used

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  • Centrifugal compressor casing with large circumferential spacing and small through holes
  • Centrifugal compressor casing with large circumferential spacing and small through holes
  • Centrifugal compressor casing with large circumferential spacing and small through holes

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] Embodiment 1 (taking the centrifugal compressor of a micro-turbojet engine as an example)

[0027] The casing of the centrifugal compressor has large intervals and small through holes in the circumferential direction, and its structure includes casing 1, through holes 2, main blades 3, and splitter blades 4; through holes 2 are set on the surface of casing 1, main blades 3 and splitter blades 4 Set inside the casing 1.

[0028] There are N1 through-holes 2, which are set around the casing 1 surface at the short distance L1 between the inlet of the rotor impeller and the leading edge of the blade. The number of through-holes 2 is selected with reference to the number of main blades of the centrifugal compressor, and the number of main blades of the compressor is Z, it is known that Z=10, N1 / Z is 0.5, and N1=5.

[0029] The gauge pressure of the internal flow field of the compressor at the position of the through hole is negative, the excitation method is periodic air in...

Embodiment 2

[0032]Embodiment 2 (taking the centrifugal compressor of a micro-turbojet engine as an example)

[0033] The casing of the centrifugal compressor has large intervals and small through holes in the circumferential direction, and its structure includes casing 1, through holes 2, main blades 3, and splitter blades 4; through holes 2 are set on the surface of casing 1, main blades 3 and splitter blades 4 Set inside the casing 1.

[0034] There are N1 through-holes 2, which are set around the surface of casing 1 at the long distance L2 between the inlet of the rotor impeller and the leading edge of the blade. The number of through-holes 2 is selected with reference to the number of main blades of the centrifugal compressor, and the number of main blades of the compressor is Z, known Z=10, N1 / Z is 0.5, then N1=5.

[0035] The gauge pressure of the internal flow field of the compressor at the position of the through hole is positive, the excitation method is periodic suction, the di...

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Abstract

The invention relates to a centrifugal compressor casing with large intervals and small circumferential through holes. The casing structurally comprises a casing, through holes, main blades and splitter blades, wherein the through holes are formed in the surface of the casing; the main blades and the splitter blades are arranged inside the casing; the gas flow at the through holes is driven by utilizing the relative movement of the casing and a rotor and the pressure difference between interior and exterior of the casing at the through holes; and the gas flow in the through holes periodicallysweeps through a compressor rotor flow channel to realize the periodic excitation effect on the flow in the compressor. The casing has the advantages that: (1) the influence range and the strength ofunfavorable low-energy flow near blade tips of the centrifugal compressor can be inhibited, so that the stable working margin of the centrifugal compressor is significantly expanded; (2) the influenceon the efficiency of the centrifugal compressor is small by utilizing an unsteady excitation effect; and (3) the casing is simple in structure and convenient to apply and implement.

Description

technical field [0001] The invention relates to a casing of a centrifugal compressor with large circumferential intervals and small through holes, belonging to the technical field of compressor design. Background technique [0002] With the requirements of modern aero-engines for high thrust-to-weight ratio, low fuel consumption rate, and small windward area, the compressor needs to have a higher stage pressure ratio to meet these performance requirements. However, the higher the stage pressure ratio of the compressor, the greater the load, and prone to unstable conditions such as rotating stall and surge. Unstable operating conditions such as rotating stall and surge will bring about a sharp decline in engine performance and serious vibration problems, which will adversely affect the life of the engine. Therefore, it is necessary to develop effective flow control means to expand the stability margin of the compressor. [0003] Due to the high Mach number of the blade tip ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D29/42F04D29/68
CPCF04D29/4206F04D29/682F04D29/684
Inventor 黄国平洪树立杨雨轩张志远刘泽鹏
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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