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An inlet variable camber guide vane structure that can eliminate the rotating boss

A technology of rotating bosses and guide vanes, used in combustion engines, machines/engines, stators, etc., can solve problems such as aerodynamic losses, and achieve the effect of avoiding aerodynamic losses

Active Publication Date: 2022-07-26
AECC SICHUAN GAS TURBINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] In view of this, the embodiment of the present application provides an inlet variable camber guide vane structure that can eliminate the rotating boss, at least partially solving the existing problem in the prior art that the turning surface of the front part of the adjustable guide vane body will be convex when rotating. The fixed strut blade body tail profile produces a rotating boss, resulting in serious aerodynamic loss

Method used

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  • An inlet variable camber guide vane structure that can eliminate the rotating boss
  • An inlet variable camber guide vane structure that can eliminate the rotating boss
  • An inlet variable camber guide vane structure that can eliminate the rotating boss

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Embodiment Construction

[0041] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0042] The embodiments of the present application are described below through specific specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, but not all of the embodiments. The present application can also be implemented or applied through other different specific embodiments, and various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other under the condition of no conflict. Based on the embodiments ...

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Abstract

The application provides an inlet variable camber guide vane structure that can eliminate the rotating boss, including a fixed support plate and an adjustable guide vane, the fixed support plate includes a blade body, a support plate head and an inner ring front section, and the fixed support plate blade body The tail is provided with a concave semicircular groove. The adjustable guide vane includes a blade body, an inner journal and an outer journal. The front part of the adjustable guide vane is provided with a convex semicircular protrusion. The groove and the semi-circular protrusion cooperate to form a rotating pair. The radius of gyration of the semi-circular groove is larger than that of the semi-circular protrusion. The rotating shaft of the fixed support plate and the adjustable guide vane is from the tip to the root of the blade. Straight line; there is a joint bearing installation groove on the head of the support plate, and the joint bearing with a waist-shaped mounting seat is installed in the joint bearing installation groove, including the joint ball and the waist-shaped mounting seat. The dimension of the waist-shaped mounting seat in the horizontal axis direction is larger than the longitudinal axis The size of the direction, and the joint ball is eccentrically installed in the transverse axis direction of the waist mount. The present application eliminates the rotating boss and reduces aerodynamic losses.

Description

technical field [0001] The present application relates to the technical field of aviation turbofan engines, and in particular, to an inlet variable camber guide vane structure that can eliminate rotating bosses. Background technique [0002] The small bypass ratio turbofan engine usually adopts the imported variable camber guide vane structure, which consists of two parts: the fixed support plate and the adjustable guide vane. The shaft journal and the blade body are formed, and are installed on the intake bearing frame through the inner and outer journals. In order to reduce the aerodynamic loss and ensure that the transition area between the outer journal of the adjustable guide vane and the blade tip has sufficient rigidity, the diameter of the outer journal is usually selected to be larger than the maximum thickness of the blade tip. The guide vane is smoothly installed in place, and it may interfere with the tail of the fixed support plate. There are generally three w...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D9/02F01D9/04
CPCF01D9/02F01D9/041F01D9/042Y02T10/12
Inventor 张万东邓杨王永明格桑央珍张强
Owner AECC SICHUAN GAS TURBINE RES INST
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