Gas compressor of gas turbine, gas turbine and aircraft
A technology for gas turbines and compressors, which is applied in the aviation field and can solve the problem of a large ratio between the axial length and radial dimension of the compressor
Active Publication Date: 2021-09-14
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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- Abstract
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- Application Information
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Problems solved by technology
[0003] The present invention aims to provide a gas turbine compressor, a gas turbine and an aircraft to improve the problem in the related art that the ratio of the axial length to the radial dimension of the compressor is relatively large
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[0027] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. The following description of at least one exemplary embodiment is merely illustrative in nature and in no way taken as limiting the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0028] combine Figures 1 to 6 As shown, the compressor of the gas turbine in this embodiment includes a casing 1, a rotating shaft 6 and a plurality of compression channels. The rotating shaft 6 is rotatably arranged in the housing 1; a plurality of compression channels are arranged side by side in...
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The invention relates to a gas compressor of a gas turbine, the gas turbine and an aircraft. The gas compressor of the gas turbine comprises a shell (1), a rotating shaft (6) rotatably arranged in the shell (1), and multiple compression flow channels arranged between the rotating shaft (6) and the shell (1) side by side in the radial direction and sequentially communicated in the gas flowing direction, wherein multiple stator blades (2) and multiple rotor blades (3) are arranged in each compression flow channel side by side in the gas flowing direction, and the stator blades (2) and the rotor blades (3) are alternately arranged. The multiple compression flow channels which are arranged side by side in the radial direction and sequentially communicated in the airflow flowing direction are formed in the space between the shell (1) and the rotating shaft (6), the paths of the compression flow channels are effectively increased, the axial length of the gas compressor can be reduced, and therefore the ratio of the axial length to the radial size of the gas compressor is reduced.
Description
technical field [0001] The invention relates to the field of aviation technology, in particular to a compressor of a gas turbine, a gas turbine and an aircraft. Background technique [0002] In order to achieve a higher compression ratio for the compressor of a gas turbine (such as an aero engine), it is generally necessary to design more compressors for airflow compression, and then the axial length of the compressor is relatively long. Such an arrangement leads to a low space utilization rate of the compressor. . At the same time, the ratio of the axial length to the radial dimension of the compressor is large, and the rigidity of the parts is affected. Therefore, it is considered to design a compressor with good space utilization and good rigidity. Contents of the invention [0003] The present invention aims to provide a gas turbine compressor, a gas turbine and an aircraft, so as to improve the problem in the related art that the ratio between the axial length and t...
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IPC IPC(8): F04D29/52F04D29/54F04D29/38F04D29/08
CPCF04D29/522F04D29/542F04D29/388F04D29/083
Inventor 陆晓锋郭绍唱党捷曹传军
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD