Separate-type nozzle design method for big-bypass-ratio engines

A technology of engine nozzle and large bypass ratio, which is applied in computing, special data processing applications, instruments, etc., and can solve problems such as reduced nozzle performance, sudden changes in speed and pressure, and discontinuous curvature.

Active Publication Date: 2014-05-28
AECC SHENYANG ENGINE RES INST
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Problems solved by technology

Due to the inconsistency of the curvature of the straight line and the arc, there is a transition point with discontinuous curvature at the junction of the curve, and a sudden change in velocity and pressure is likely to occur at the point of discontinuous curvature, which reduces the performance of the nozzle

Method used

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  • Separate-type nozzle design method for big-bypass-ratio engines
  • Separate-type nozzle design method for big-bypass-ratio engines
  • Separate-type nozzle design method for big-bypass-ratio engines

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Embodiment 1

[0039] This embodiment provides a design method for a split nozzle of a large bypass ratio engine, which is characterized in that: a design method for a split nozzle of a large bypass ratio engine, and the aerodynamic design method for a large bypass ratio engine nozzle is suitable for large bypass ratios Compared with the design of the inner nozzle and the outer nozzle in the split nozzle of the engine.

[0040] Using parametric design, the nozzle wall is constructed with a smooth and continuous curve, and the area change along the nozzle is determined by using a reasonable change law of the area along the convergence section. The specific process is as follows:

[0041] Step 1 for defining the initial parameters of nozzle aerodynamic design and assigning values;

[0042] Step 2 for solving the profile line of the plane in the nozzle;

[0043] Step 3 for solving the law of area change along the nozzle;

[0044] Step 4 for solving the molded lines of the inner and outer wall...

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Abstract

The invention discloses a separate-type nozzle design method for big-bypass-ratio engines and is applicable to design of an inner-culvert nozzle body and an outer-culvert nozzle body in a separate-type nozzle of a big-bypass-ratio engine. The separate-type nozzle design method includes that parametrization design is adopted, a nozzle wall is constructed through a smooth and continuous curve, route area changes of the nozzle are determined by applying the reasonable contraction section route area change rules, and the specific process includes the steps of 1), defining pneumatic design initial parameters of the nozzle and performing assignment; 2), analyzing planar lines in the middle of the nozzle; 3), analyzing the route area change rules of the nozzles; 4), analyzing the planar lines on the inner wall and the outer wall of the nozzle; 5), calculating pneumatic performance of the nozzle; the flow area is designed according to the contraction mode. The separate-type nozzle design method has the advantages that a flow path scheme of the nozzle of the big-bypass-ratio engine can be rapidly designed with trend of the nozzle adjustable according to the actual situation, and design cycle can be remarkably reduced.

Description

technical field [0001] The invention relates to the design field of aeroengine nozzles, in particular to a method for designing a separate nozzle of a large bypass ratio engine. Background technique [0002] The nozzle is an important part of the high bypass ratio engine, and its performance has a very obvious impact on the high-performance transport aircraft. Even a slight change in its performance will cause a large change in the performance of the aircraft. Split exhaust nozzle is the most widely used form of exhaust nozzle for large bypass ratio engines. The inner nozzle and outer nozzle have similar geometric shapes, and the same design method can be adopted in aerodynamic design. The method used in the traditional nozzle design of high bypass ratio engines is to construct a number of geometric parameters, establish a mathematical model, and construct the flow path shape of the nozzle. The shape of the nozzle wall is represented by a set of line segments, and the line ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 汪东丛明辉张佐依杜寅威石岩
Owner AECC SHENYANG ENGINE RES INST
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