Turbine rear force bearing case integrally connected to rectification blade cascade

Abstract

The invention relates to a turbine rear force bearing case and rectification blade cascade integrally-connecting structure, wherein the shape of the turbine rear force bearing case part is the same as the conventional turbine rear force bearing case, and the difference and the characteristics comprise that a rectification blade structure is arranged among the outer ring, the inner ring and the support plate of the conventional turbine rear force bearing case, the blade structure comprises a blade upper edge plate, blades, a blade flow channel plate, a blade lower edge plate and a blade lower edge front end baffle, the blade upper edge plate is fixed on the force bearing case outer ring through a radial screw, the rear end of the blade lower edge plate is axially and circumferentially positioned on the flange of the rear end of the force bearing case inner ring through a special radial bolt, and a gas flow channel is formed among the blade flow channel plate, the blades, the blade upper edge plate and the force bearing support plate. According to the present invention, under the premise of no substantial change of the turbine rear force bearing case structure, and no influence on the rear force bearing case strength, the deformation coordination and the support stiffness, the integration of the turbine rear force bearing case and the rectification blade cascade is achieved.

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...

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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

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