an axial flow compressor
A technology for axial flow compressors and rotating shafts, applied in axial flow pumps, mechanical equipment, machines/engines, etc., can solve the problems affecting the actual effect and increasing the complexity of the adjustment system, so as to improve efficiency and reduce the possibility of rotating stall performance, margin improvement effect
Active Publication Date: 2021-07-30
AECC COMML AIRCRAFT ENGINE CO LTD
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Problems solved by technology
In addition, the airflow direction at the inlet of the rotor blade is affected by three factors: the airflow direction at the outlet of the guide vane or stator blade, the speed of the compressor, and the gas flow through the compressor. The value of the adjustment of the installation angle of the guide vane and stator blade must It is determined according to the speed and flow of the compressor at the working state at that time, which will greatly increase the complexity of the regulating system
Therefore, in practical applications, in order to reduce the structural weight and the complexity of the adjustment system, the adjustment of the guide vanes or stator vanes is often unable to be multi-stage or steplessly adjustable as the working state of the compressor changes, and even the guide vanes or The stator vane can only work under two installation angles, which greatly affects its actual effect
Method used
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[0032] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.
[0033] The technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Apparently, the described embodiments are only some of the embodiments of this application, not all of them. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way serves as any limitation of the application, its application or uses. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application.
[0034] It should be noted that the terminology used here is only for describing specific implementations, and is not intended...
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The invention relates to an axial flow compressor. The axial flow compressor has a rotor as a rotating shaft and a row of rotor blades mounted on the rotor and arranged along the circumferential direction of the rotating shaft, the row of rotor blades includes a plurality of rotor blades arranged along the circumferential direction of the rotating shaft; the axial flow compressor It also includes a guide rotor blade row installed on the rotor and arranged along the circumferential direction of the rotating shaft, the guide rotor blade row includes a plurality of guide rotor blades arranged along the circumferential direction of the rotating shaft; the airflow in the axial flow compressor In terms of direction, the guide rotor blade row is arranged before the rotor blade row, and the bending direction of the mid-arc line of the airfoil section of the guide rotor blade is opposite to the bending direction of the mid-arc line of the airfoil section of the rotor blade. The invention provides an axial flow compressor, which can effectively improve the aerodynamic stability of the axial flow compressor.
Description
technical field [0001] The invention relates to the technical field of impeller machinery, in particular to an axial flow compressor. Background technique [0002] Since the rotor blade row of the axial flow compressor rotates at high speed during operation, in order to avoid breakage under the action of centrifugal force and aerodynamic force, the rotor blade row of the existing axial flow compressor adopts a geometrically non-adjustable structural scheme, that is, when the compression The change of the working state of the machine leads to the change of the airflow direction to the rotor blade row, but because the inlet geometric angle of the rotor blade is fixed, there is a disharmony between the gas flow direction and the blade geometry, especially when the rotor blade inlet When the airflow angle of attack is large, it will cause the compressor to stall or surge, resulting in the compressor not working properly. [0003] In order to reduce the mismatch between aerodyna...
Claims
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IPC IPC(8): F04D19/02F04D29/32F04D29/38F04D29/54
CPCF04D19/028F04D29/321F04D29/324F04D29/544
Inventor 刘佳骏
Owner AECC COMML AIRCRAFT ENGINE CO LTD