Novel nozzle and fin combined type vortex reduction system

A composite, nozzle technology, used in non-variable-capacity pumps, cooling of turbines/propulsion devices, cooling of engines, etc., can solve the problems of viscous dissipation of airflow, unfavorable airflow, small flow area, etc., to reduce flow Obstruction, avoids widening and narrowing, and has the effect of large circulation area

Pending Publication Date: 2021-04-13
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the straight tube vortex reducer will cause the expansion and contraction of the airflow channel at its inlet and outlet, causing the vi

Method used

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  • Novel nozzle and fin combined type vortex reduction system
  • Novel nozzle and fin combined type vortex reduction system
  • Novel nozzle and fin combined type vortex reduction system

Examples

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Example Embodiment

[0032]figure 1 It is a schematic perspective view of a novel nozzle fin composite slide system according to an embodiment of the present application.figure 2 Yesfigure 1 A schematic main view of the nozzle fin composite slide system.image 3 Yesfigure 1 A schematic top view of the nozzle fin composite slide system shown.

[0033]Such asfigure 1 As shown, please also seeFigure 2 - Figure 3In this embodiment, the present embodiment provides a novel nozzle fin composite shaping vortex system, which is arranged at the radial drainage section of the compressor of the secondary air system of the aeroengine. The pressurizing machine includes: a drum 3, a drum 3 extending perpendicular to the outer edge of the two side compressor discs, each side of the outer edge of the compressor disk 2 The disk and the drum 3 form an interior disc. A plurality of drum bore 31 is provided at the drum 3. Several drum holes 31 are uniformly arranged on the drum 3 in the circumferential direction. The tube hole ...

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Abstract

The invention discloses a novel nozzle and fin combined type vortex reduction system, and relates to aero-engines. The novel nozzle and fin combined type vortex reduction system comprises a plurality of reverse rotation nozzles and a plurality of reverse rotation fins, each reverse rotation nozzle is installed at the position of a two-stage gas compressor disc, and each reverse rotation fin is installed at the position of a front-stage gas compressor disc and located at the downstream position of the multiple reverse rotation nozzles; the reverse-rotation nozzles and the reverse-rotation fins are evenly arranged in the circumferential direction of the gas compressor discs and are coaxial with the gas compressor discs on the two sides, the structures of the reverse-rotation nozzles and the reverse-rotation fins are the same, the corresponding installation radiuses are the same, the circumferential speed of airflow is limited, development of free vortexes is restrained, and flow hindrance is reduced. Compared with a vortex reducing pipe, the flow area of the reverse rotation fins is large, sudden expansion and sudden shrinkage of a flow channel in the air entraining process are avoided, therefore viscous dissipation caused by airflow mixing is reduced, and airflow total pressure losses are reduced.

Description

technical field [0001] The present application relates to the technical field of drag reduction in the bleed air section of the compressor of the secondary air system of the aero-engine, and in particular to a novel nozzle-fin composite vortex reduction system for the aero-engine. Background technique [0002] The cold air of the internal flow air cooling system of the aero-engine is drawn from the middle stage of the compressor. On the one hand, this part of cold air is used to cool high-temperature components such as turbine blades, casings, discs, shafts and bearings, so that they can work under the allowable temperature and ensure the pressure of the intake air of relevant parts; on the other hand, the cold air will It is used for sealing to prevent gas backflow; at the same time, the cold air is also used to maintain the pressure of the unloading chamber, so as to meet the requirements of the axial force of the engine. However, a large amount of bleed air will reduce t...

Claims

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Application Information

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IPC IPC(8): F02C3/04F02C7/18F04D29/40F04D29/66
CPCF02C3/04F02C7/18F04D29/403F04D29/667
Inventor 罗翔何建白阳邬泽宇
Owner BEIHANG UNIV
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