Aero-engine integrated air exhaust structure

A technology of aero-engine and tail cone, applied in the direction of engine components, machines/engines, mechanical equipment, etc., can solve the problems of reducing assembly, disassembly, maintenance efficiency, increasing cost, etc., to improve reflection effect, reduce quantity, and good assembly. and maintenance effects

Inactive Publication Date: 2019-02-19
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Under the application background condition that the present invention faces, the shortcoming of prior art scheme and prior art related to the present invention is: technical aspect, prior art scheme and prior art are under the background of no turbine rear casing, are fixed For the tail cone, an additional non-main load-bearing casing is required, and the lobe mixer also needs to be fixed on the non-main load-bearing casing, that is, the non-main load-bearing casing replaces the function of fixing the exhaust components of the original turbine rear casing; In terms of cost, the existing technical solution and the existing technology need to add an additional non-main load-bearing casing, which increases the cost; in terms of efficiency, the existing technical solution and the existing technology reduce the assembly and disassembly due to the additional components. , maintenance efficiency

Method used

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  • Aero-engine integrated air exhaust structure
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Embodiment Construction

[0014] The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the related application, not to limit the application. In addition, it should be noted that, for ease of description, only parts relevant to the present application are shown in the drawings.

[0015] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0016] It should be noted that in the description of this application, the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. The terms of the indicated direction or positional relationship are based on the direction or positional ...

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Abstract

The invention provides an aero-engine integrated air exhaust structure. The structure comprises a fixing flange edge, a straight segment, a lobe mixer, a coccyx, supporting plates and self-locking wire thread inserts. The straight segment is connected with the fixing flange edge and the lobe mixer. The coccyx is connected to the straight segment through the supporting plates. The self-locking wirethread inserts are arranged in the positions where the coccyx is connected with the supporting plates correspondingly.

Description

technical field [0001] The present application relates to the technical field of aero-engines, and specifically provides an integrated exhaust structure for aero-engines. Background technique [0002] The exhaust method of the traditional dual-duct aero turbofan engine is separate exhaust and mixed exhaust. In the mixed exhaust aeroengine, the nozzle, mixer and nozzle together form the exhaust assembly. In the existing aero-engine, the mixer adopts a flange to be fixed on the rear flange of the turbine rear casing outer ring casing, and the tail cone is also fixed on the rear installation edge of the turbine rear casing inner ring casing by a flange. The background of the present invention is that in a mixed-displacement aero-turbofan engine, when the overall structural layout of the aero-engine cancels the turbine rear casing and shaft ventilation, the tail cone in the exhaust assembly faces a situation where there is no fixed stator casing. [0003] The implementation sch...

Claims

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Application Information

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IPC IPC(8): F02K3/06F01D25/30
CPCF01D25/305F02K3/06
Inventor怀时卫徐雪张德志徐朋飞
OwnerAECC SHENYANG ENGINE RES INST