Gas Turbine Vane Adjustment Lever Clamping Design
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Solution Overview
Problem
Existing turbomachines, particularly gas turbines, face challenges in reducing size and weight while minimizing maintenance requirements and part count, particularly in the design of blade adjustment arms.
Innovation Solution
A blade adjustment arm with two pivoting legs forming a clamping device with clamping surfaces, which securely holds the guide vane shaft in a force-fitting manner, eliminating the need for nuts and cotter pins, and allowing for a reduced installation space and fewer parts.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a blade adjustment arm is fixed to the guide vane shaft using nuts and cotter pins, then the connection is secure and reliable, but the device complexity increases and the number of parts increases
Solution Approach 1:
The blade adjustment arm is merged with the guide vane shaft by forming an integral connection where the adjustment arm is directly formed as part of the shaft structure, eliminating the need for separate fastening components like nuts and cotter pins while maintaining structural integrity and reliability
Solution Approach 2:
The guide vane shaft is designed with multi-functionality by integrating the adjustment arm directly into the shaft structure, allowing the shaft to simultaneously serve as both the rotational axis and the adjustment mechanism mounting structure, thereby reducing the overall number of components
2Reliability
If traditional fastening components (nuts, cotter pins) are used to secure the blade adjustment arm, then the assembly is secure, but the weight of the turbomachine increases
Solution Approach 1:
The blade adjustment arm and guide vane shaft are combined into a single integrated structure, eliminating the weight of separate fastening components such as nuts and cotter pins while maintaining the security and reliability of the connection through the integral design
3Reliability
If multiple fastening components are used to attach the blade adjustment arm to the guide vane shaft, then the connection is secure, but the installation space required increases
Solution Approach 1:
The adjustment arm and shaft are merged into an integrated structure that eliminates the need for additional fastening components, thereby reducing the radial and axial space required for the assembly while maintaining secure connection through the integral design
4Reliability
If nuts and cotter pins are used to secure the blade adjustment arm, then the connection is reliable, but the number of parts increases and maintenance requirements increase
Solution Approach 1:
The blade adjustment arm is merged with the guide vane shaft into a single integrated component, eliminating the need for separate fastening parts such as nuts and cotter pins, thereby reducing the total number of parts while maintaining connection reliability through the integral structure
Solution Approach 2:
The design discards traditional fastening components (nuts, cotter pins) that require maintenance and replacement, recovering instead through the simplified integral structure that has fewer wear points and maintenance requirements
Data Source
Figure 1
Figure 2a
Figure 2b
AI summary
The invention relates to a blade adjustment arm (10) for a turbomachine, comprising two legs (12) which can be pivoted relative to one another between at least one open position and a closed position and which form a clamping device which has at least one clamping surface (14) on each of the legs (12), by means of which, in the closed position, a blade shaft (20) provided for adjusting a guide vane of the turbomachine can be held in a force-fitting manner between the two legs (12) via the two clamping surfaces (14) to form a clamping connection (16), wherein each of the legs (12) has an opening (50) which overlap one another in the closed position in such a way that a through-bolt can be pushed through the openings (50) and can be connected to an adjustment element of the turbomachine for adjusting an angle of rotation of the blade shaft (20).