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Two-stage axial swirler and aero-engine with cavity enhanced oil and gas mixing

A two-stage swirler and swirler technology, applied in the field of aero-engines, can solve the problems of unstable precession flow of the vortex core, reduced flame stability of the combustion chamber, unfavorable flame stability, etc. Improved outlet temperature distribution, improved blending and distribution

Active Publication Date: 2022-07-05
AECC HUNAN AVIATION POWERPLANT RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0006] The present invention provides a two-stage axial swirler with concave cavity enhanced oil-gas mixing, to solve the problem that the precession of vortex core (PVC) flow is unstable in the flow field of the existing two-stage axial swirl, which will cause Combustion instability and the reduction of flame stability in the combustion chamber, which is not conducive to the technical problems of flame stability

Method used

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  • Two-stage axial swirler and aero-engine with cavity enhanced oil and gas mixing
  • Two-stage axial swirler and aero-engine with cavity enhanced oil and gas mixing
  • Two-stage axial swirler and aero-engine with cavity enhanced oil and gas mixing

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Embodiment 2

[0047] refer to image 3 , the difference between this embodiment and Embodiment 1 is that the end of the guide ring 411 is arranged vertically, the guide ring 411 is installed and used in conjunction with the flame tube of the aero-engine during installation, and the end of the guide ring 411 is vertically arranged, It has the effect of positioning installation.

Embodiment 3

[0049] refer to Figure 4 The difference between this embodiment and Embodiment 1 is that the end of the guide ring 411 is chamfered, and the end of the guide ring 411 is chamfered to reduce the adsorption of oil and gas at the end of the guide ring 411, and by chamfering the end of the guide ring 411 The end of the ring 411 is chamfered, which reduces the weight of the aero-engine while cooling the cyclone casing, and the chamfering at the end of the guide ring 411 is convenient when processing the guide ring 411. Machining.

Embodiment 4

[0051] refer to Figure 5 The difference between this embodiment and Embodiment 1 is that the angle between the inner wall of the guide ring 411 and the end of the sleeve 4 is 135°, and the angle between the inner wall of the guide ring 411 and the end of the sleeve 4 is set to 135° , the angle between the guide ring 411 and the sleeve 4 is set to 135°, so that the oil and gas mixed in the cavity vortex 412 can smoothly enter the flame tube for combustion, and pass through the guide ring 411 and the end of the sleeve 4. The inclined setting between the first is to reduce the adsorption of oil and gas, the second is to increase the mixing residence time of fuel and air, and the mixing effect is strengthened, and the third is to reduce the weight of the sleeve 4. The aero-engine is a precision mechanical equipment and is equipped with aeroplanes to work. When designing aero-engine parts, it is necessary to consider the influence of weight, and it is necessary to reduce the weigh...

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Abstract

The invention discloses a dual-stage axial cyclone with a concave cavity for enhancing the mixing of oil and gas, comprising a primary cyclone and a secondary cyclone, wherein the first cyclone and the secondary cyclone A venturi is arranged between the two cyclones, a sleeve is arranged on the secondary cyclone, the primary cyclone is sleeved on the central nozzle, and also includes: a mixed flow part, and the mixed flow part is arranged on the sleeve At the end of the combustion chamber, the mixing part is used to fully mix the oil and gas in the combustion chamber again; the cooling part is arranged on the sleeve, and the cooling part is used to transport the cooling gas and swirl the combustion chamber. The vortex core precession (PVC) flow instability commonly exists in the flow field of the dual-stage axial swirler, which will cause combustion instability and reduce the flame stability of the combustion chamber, which is not conducive to the flame. stable effect.

Description

technical field [0001] The present invention relates to the technical field of aviation gas turbine engine combustion chambers, in particular, to a dual-stage axial swirler with a concave cavity for enhancing oil and gas mixing. In addition, the present invention also relates to a concave cavity for enhancing oil and gas mixing. A two-stage axial swirler for aero-engines. Background technique [0002] The development of high-performance combustion chambers has put forward higher requirements for fuel atomization technology, and it is necessary to achieve complete combustion in a shorter combustion area to shorten the length of the combustion chamber and reduce its weight; it is necessary to better organize the concentration field in the main combustion area , in order to cope with the shortage of gas volume caused by the high temperature rise combustion chamber used to adjust the outlet temperature field; it needs to have higher requirements for ignition performance, lean oi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F23R3/38F23R3/12F23R3/28
CPCF23R3/38F23R3/12F23R3/286Y02T50/60
Inventor 王志凯江立军陈盛彭中九刘冉刘逸博
Owner AECC HUNAN AVIATION POWERPLANT RES INST
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