Turbine rear bearing case integrally connected with rectifying cascade

A load-bearing casing and rectifying cascade technology, applied in the field of aviation propulsion, to reduce weight, increase thrust-to-weight ratio, and shorten axial length

Inactive Publication Date: 2017-08-04
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the above-mentioned problems in the prior art, the present invention provides an integrated connection structure of the turbine rear bearing casing and the rectifying blade cascade, which does not significantly change the stress, deformation and support stiffness of the turbine rear bearing casing Next, the rectifying cascade structure can be connected and positioned with the rear bearing casing

Method used

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  • Turbine rear bearing case integrally connected with rectifying cascade
  • Turbine rear bearing case integrally connected with rectifying cascade
  • Turbine rear bearing case integrally connected with rectifying cascade

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Embodiment Construction

[0027] The present invention provides an integrated connection structure between the turbine rear bearing casing and the rectifying blade cascade. The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0028] Such as figure 2 with image 3 As shown, in the integrated connection structure of the turbine rear bearing casing and the rectifying blade cascade according to an embodiment of the present invention, in addition to the rear bearing casing outer ring 2 included in the existing turbine rear bearing casing structure 1. In addition to the inner ring 9 of the rear load-bearing casing and the load-bearing support plate 11, the blades 4 are discretely installed between each load-bearing support plate 11 along the circumferential direction. The cascade structure includes the blade upper edge plate 3, the blade 4, Blade runner 5 and blade lower edge plate 6 .

[0029] Open threaded holes at the upper edge...

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Abstract

The connection structure of the turbine rear bearing casing and the rectifying blade cascade is integrated, and the shape of the turbine rear bearing casing part is the same as that of the conventional turbine rear bearing casing. Its difference and characteristics are: it adds a rectifying blade structure between the outer ring, inner ring and support plate of the conventional turbine back bearing casing, wherein the blade structure includes; blade upper edge plate, blade, blade flow channel plate, The blade lower edge plate and the front end baffle of the blade lower edge plate. The upper edge plate of the blade is fixed on the outer ring of the load-bearing casing through radial screws, and the rear end of the lower edge plate of the blade is positioned on the rear end flange of the inner ring of the load-bearing casing through special radial bolts; An air flow channel is formed among the flow channel plate, the vane, the upper edge plate of the vane and the supporting support plate. The invention realizes the integration of the turbine rear bearing casing and the rectifying blade cascade without greatly changing the structure of the turbine rear bearing casing and without affecting the strength, deformation coordination and support rigidity of the turbine rear bearing casing.

Description

technical field [0001] The invention relates to an integrated connection structure of a turbine rear bearing casing and a rectifying blade cascade, and belongs to the technical field of aviation propulsion. Background technique [0002] In the current advanced aviation gas turbine engine, an afterburner is usually installed between the turbine and the exhaust nozzle to perform afterburning and afterburning, and continue to increase the thrust after the engine reaches the maximum thrust state. However, the airflow at the outlet of the low-pressure turbine usually cannot meet the requirements of the afterburner for the airflow angle at the outlet of the low-pressure turbine. Therefore, it is necessary to install rectifying blades between the rotor of the low-pressure turbine and the afterburner to rectify the airflow. [0003] The above-mentioned design will cause the rear bearing casing to be moved backward to install additional outlet rectifying vanes, thereby increasing the...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/20
Inventor 胡文通申秀丽
Owner BEIHANG UNIV
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