Axial flow compressor and turbofan engine

A technology for axial flow compressors and turbofan engines, which is applied in the direction of machines/engines, liquid fuel engines, axial flow pumps, etc., can solve problems affecting the performance of compressors, achieve enhanced anti-separation ability, enhanced working ability, and improved The effect of working range

Active Publication Date: 2021-12-17
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to overcome the defect that the non-adjustable stages of the axial flow compressor in the prior art affect the performance improvement of the compressor, and provide an axial flow compressor and a turbofan engine

Method used

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  • Axial flow compressor and turbofan engine
  • Axial flow compressor and turbofan engine
  • Axial flow compressor and turbofan engine

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Embodiment Construction

[0036] In the following, the present invention will be more clearly and completely described by means of an embodiment in conjunction with the accompanying drawings, but the present invention is not limited to the scope of the embodiment.

[0037] It should be understood that the orientation or positional relationship indicated by orientation words such as "front", "rear", "front side", "rear side" etc. is usually based on the orientation or positional relationship shown in the drawings, and is only for convenience To describe the present invention and to simplify the description, these orientation words do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation unless stated to the contrary, and therefore should not be construed as essential to the present invention. Limitation of Scope of Protection. At the same time, the use of words such as "first" and "second" to define parts or...

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Abstract

The invention discloses an axial flow compressor and a turbofan engine. The axial flow compressor comprises a flow channel, an adjustable supercharging stage and a non-adjustable supercharging stage, the adjustable supercharging stage and the non-adjustable supercharging stage are arranged in the flow channel, the non-adjustable supercharging stage comprises a first rotor blade arranged on the rear side of the adjustable supercharging stage, connecting points of the front edge blade root and the tail edge blade root of the rotor blade and the inner wall surface of the flow channel are a first intersection point and a second intersection point respectively, the relative height of the second intersection point is larger than that of the first intersection point, and the height difference between the second intersection point and the first intersection point is 5%-20% of the meridian chord length of the blade root position of the rotor blade. The relative height of the blade root at the blade rear edge of the rotor blade of the first non-adjustable supercharging stage is increased, so that the hub streamline of the rotor blade is increased, then the tangential speed of the pitch diameter of the rotor blade of the stage is increased, the working capacity of the rotor blade of the stage is enhanced, the separation resistance of the supercharging stage is enhanced, and the surge margin of the first non-adjustable supercharging stage can be improved.

Description

technical field [0001] The invention relates to an axial compressor and a turbofan engine. Background technique [0002] As the core component of an aero-engine, the axial-flow compressor has a direct impact on the pressure ratio and efficiency of the compressor, which in turn affects the overall performance of the engine. The current development trend of aero-engines puts forward the requirements of high efficiency, high load, few stages and light weight for the compressor. To continuously improve the average stage pressure ratio and performance of the compressor, the matching of parameters at all stages is very important. When all stages of the compressor are in non-ideal working conditions, even if each stage has good performance, it is difficult for the multi-stage compressor to work normally. Only when all stages of the compressor are in good working condition, the multi-stage compressor In order to exert the greatest function. [0003] In order to take into account ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F04D19/02F04D29/38F04D29/54F04D27/02F02C3/06
CPCF04D19/02F04D29/388F04D29/542F04D27/02F02C3/06
Inventor 曹传军王进春张晓诗
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
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