Turbofan engine design parameter optimization method

A turbofan engine and design parameter technology, which is applied in the optimization field of turbofan engine design parameters of direct binary exhaust system, can solve problems such as engine failure and thrust loss, and achieve simple optimization process and low fuel consumption efficiency, the effect of low infrared radiation intensity

Pending Publication Date: 2021-06-25
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, reducing the intensity of infrared radiation often comes with a severe loss of thrust and may even render the engine inoperable

Method used

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  • Turbofan engine design parameter optimization method
  • Turbofan engine design parameter optimization method
  • Turbofan engine design parameter optimization method

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Embodiment Construction

[0027] The technical scheme of the present invention is described in detail below in conjunction with accompanying drawing:

[0028] Compared with the traditional axisymmetric exhaust system, the straight binary exhaust system can effectively reduce the projected area of ​​the internal high-temperature wall (such as the central cone wall, etc.) on the outlet of the exhaust system, thereby reducing the infrared radiation intensity of the exhaust system, directly The shape of the binary nozzle is as figure 1 shown.

[0029] For the turbofan engine adopting straight binary exhaust system, the solution idea of ​​the present invention is to aim at high thrust, low fuel consumption rate and low infrared radiation intensity, carry out multi-objective optimization to the design parameters, and optimize the design of the model to Reduce computational complexity. To achieve this goal, the technical scheme proposed by the present invention is specifically as follows:

[0030] A method...

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Abstract

The invention discloses a turbofan engine design parameter optimization method. An exhaust system of the turbofan engine is a straight two-dimensional exhaust system with a straight two-dimensional nozzle; the design parameters of the turbofan engine are subjected to multi-objective optimization by taking high thrust, low oil consumption rate and low infrared radiation intensity as objectives; an optimization model takes linear weighted sum of thrust, oil consumption rate and infrared radiation intensity as an objective function, and upper and lower limit constraints of each design parameter are considered at the same time. Compared with the prior art, the method has the advantages that aiming at the turbofan engine with the straight binary exhaust system, the design parameters are subjected to multi-objective optimization by taking high thrust, low oil consumption rate and low infrared radiation intensity as objectives, the objectives of high thrust, low oil consumption rate and low infrared radiation intensity can be realized at the same time, the optimization model is simple and clear, and the optimization process is simple, convenient and feasible.

Description

technical field [0001] The invention relates to a method for optimizing design parameters of a turbofan engine, in particular to a method for optimizing design parameters of a turbofan engine with a straight binary exhaust system with a straight binary nozzle. Background technique [0002] In air combat, combat fighters with good infrared stealth performance are often difficult to be found by the enemy, so they have a high survival rate. Therefore, the infrared stealth capability of the aircraft is particularly important. For combat fighters, high infrared stealth capability is very important, which makes traditional turbofan engines continue to develop towards turbofan engines with low infrared radiation intensity. In order to improve the infrared stealth performance of the engine and reduce the infrared radiation intensity of the aircraft engine exhaust system, the method of installing a straight binary nozzle can be adopted. Compared with traditional axisymmetric nozzle...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/17G06F30/28G06F111/06G06F113/08G06F119/08G06F119/14
CPCG06F30/15G06F30/17G06F30/28G06F2111/06G06F2113/08G06F2119/08G06F2119/14
Inventor 姜尚彬姜威张海波陈浩颖
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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