Method for impelling through flow by air compressor time by considering air source bleed air of air system

An air system, time-propulsion technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as reduced surge margin and reduced compressor performance

Inactive Publication Date: 2009-10-28
BEIHANG UNIV
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Problems solved by technology

If the influence of bleed air from the air system source is not correctly reflected in the design, it w

Method used

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  • Method for impelling through flow by air compressor time by considering air source bleed air of air system
  • Method for impelling through flow by air compressor time by considering air source bleed air of air system
  • Method for impelling through flow by air compressor time by considering air source bleed air of air system

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Embodiment Construction

[0033] In order to describe the present invention more clearly, this specific embodiment takes the design scheme of a high-pressure compressor as an example, and further illustrates the present invention in conjunction with the accompanying drawings.

[0034] The example of the present invention is a seven-stage high-pressure compressor with a design flow rate of 91.2kg / s, a design pressure ratio of 6.0, a design efficiency of 0.85, a blade tip tangential velocity of 450m / s, and an inlet hub ratio of 0.72. The flow path geometry of the compressor, such as image 3 .

[0035] (1) According to the overall indicators of the aircraft and the engine, the bleed air in the middle stage of the multi-stage compressor is considered to be used as the cooling function of the hot-end parts of the engine, and the pressure of the airflow itself is driven to complete the delivery, and the selection is made according to the pressure relationship between the air source and the user end. The fi...

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Abstract

The invention relates to a method for impelling through flow by air compressor time by considering air source bleed air of an air system. By analyzing the characteristics and the requirement of the air source of the air system of an engine, the air source bleed air and the air compressor are designed to be associated, a bleed air model with a bleed air position, a bleed air area, a bleed air volume, a bleed air speed and a bleed air angle combined with boundary conditions of a flow passage of the air compressor is established, and the influence of the bleed air parameters on the flow field of the air compressor is transmitted to the upstream and the downstream by impelling the solving of the through flow procedure by time, thus involving influencing factors of the bleed air on flow field characteristics such as flow field air flow angle, end wall loss, power adding quantity, blade shape and the like in the flow field solving of the through flow of the air compressor, and finally obtaining the through flow design result of the air compressor considering the air source bleed air of the air system. The method completely involves the influencing factors of the bleed air on the flow field characteristics of the air compressor in the flow field solving of the through flow of the air compressor, and thoroughly and deeply considers the air source bleed air of the air system in the through flow design of the air compressor, thus being the exploration and innovation of the bleed air realized in the design of the air compressor.

Description

technical field [0001] The invention relates to the design system of an air source bleed air of an aviation turbofan engine (referred to as a turbofan engine) and a compressor, and is a time-propelled flow method that integrates the air source bleed air of the air system into the design of an aviation compressor. Background technique [0002] In an aviation gas turbine engine, some airflows other than the main gas flow that have important functions for the safe and effective operation of the aircraft and the engine constitute the air system of the engine. According to the different working conditions of the aircraft and the engine, the air system bleeds air from different compressor stages of the engine, and uses the air of appropriate pressure and temperature as the air conditioning and pressurization system of the aircraft cabin, the thermal anti-icing system of the wing, and the anti-icing system of the engine inlet fairing. Ice system, sealing of bearing lubrication syst...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 侯安平袁巍赵斌周盛
Owner BEIHANG UNIV
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