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A Calculation Method for Assessing the Effect of Mode Change on Stability Margin of Turbojet/Turbofan Variable Cycle Engine

A variable cycle engine and mode conversion technology, applied in design optimization/simulation, geometric CAD, etc., can solve the problem of turbojet/turbofan variable cycle engine aerodynamic stability is not involved, and achieve high accuracy.

Active Publication Date: 2021-02-26
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Scholars at home and abroad have accumulated some experience in the simulation of the steady-state performance of turbojet / turbofan variable cycle engines, but they have not involved in the evaluation of the effect of mode change on the aerodynamic stability of turbojet / turbofan variable cycle engines.

Method used

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  • A Calculation Method for Assessing the Effect of Mode Change on Stability Margin of Turbojet/Turbofan Variable Cycle Engine
  • A Calculation Method for Assessing the Effect of Mode Change on Stability Margin of Turbojet/Turbofan Variable Cycle Engine
  • A Calculation Method for Assessing the Effect of Mode Change on Stability Margin of Turbojet/Turbofan Variable Cycle Engine

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Embodiment

[0068] Table 1 is the meaning of each symbol involved in the present invention.

[0069] Table 1 Symbol table

[0070]

[0071] In this embodiment, the establishment of a calculation model for the influence of a certain type of variable cycle engine mode change on aerodynamic stability is taken as an example. figure 1 The calculation model and cross-sectional diagrams of a certain type of variable cycle engine are given. In the figure, cross-section 2 is the fan inlet, cross-section 20 is the fan outlet, cross-section 13 is the inlet of the secondary culvert, cross-section 21 is the inlet of the fan stage driven by the core engine, and cross-section 24 is 225 section is the auxiliary duct outlet, 25 section is the high-pressure compressor inlet, 15 section is the outlet of the front mixing chamber, 16 section is the main outer culvert outlet, 3 section is the high-pressure compressor outlet, 31 Section 4 is the inlet of the main combustion chamber, section 4 is the outlet ...

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Abstract

The invention discloses a calculation method for evaluating the influence of mode conversion on the stability margin of a turbojet / turbofan variable-cycle engine. First, a calculation model for evaluating the dynamic change of the inlet and outlet flow of the regulating structure during the mode conversion process of the variable-cycle engine is proposed. , and then calculate the function relationship between the angle of the mode change valve, the opening of the front variable area ducted ejector, the opening of the rear variable area ducted ejector and the flow rate when analyzing the mode change of the variable cycle engine. . The invention realizes the stability of the engine when the turbojet / turbofan variable cycle engine is dynamically changing the working modes such as the single bypass turbojet cycle, the double-extension high-bypass ratio turbofan cycle, and the single-extension small-bypass-ratio turbofan cycle. Calculation of degree change.

Description

technical field [0001] The invention belongs to the overall performance and stability of an engine in aerospace propulsion theory and engineering, and in particular relates to a method for calculating the aerodynamic stability of a turbojet / turbofan variable cycle engine. Background technique [0002] In order to achieve excellent performance in the full flight envelope range of advanced fighter jets and meet the multi-mission and multi-purpose requirements of military fighter jets in the future, the power plant of fighter jets - aeroengines will no longer be satisfied with the status quo of single design point and limited adjustment of working point . Turbojet / turbofan variable cycle engine, as a new type of aero engine, combines the advantages of turbojet engine and turbofan engine, and has two design points, namely subsonic flight condition design point and supersonic flight condition design point , and the corresponding working states are the turbofan mode with a large ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F30/15
CPCG06F30/15G06F30/20
Inventor 屠宝锋胡骏严伟李俊郭晋
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS