Remote Actuator for Compressor Vanes
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Solution Overview
Problem
Conventional turbine engines face packaging challenges due to the axial flow relationship, which complicates the elongated engine structure, and tip turbine engines struggle with accommodating actuators for variable compressor vanes without increasing the engine diameter, encroaching on the bypass airflow path.
Innovation Solution
A remote actuator system is implemented, where the actuator is located away from the variable guide vanes and connected via a torque rod and activation ring, allowing rotation of the compressor vanes about the engine centerline, enabling easy access and minimizing the compressor case size.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If actuators for variable compressor vanes are located on the compressor case in tip turbine engines, then the variable guide vanes can be actuated, but the engine diameter must be increased, encroaching on the bypass airflow path
Solution Approach 1:
The actuator is relocated from the radial direction (on the compressor case) to the axial direction (at the forward end of the compressor). This dimensional change allows the actuator to be positioned in the axial flow path without increasing the radial engine diameter, thereby avoiding encroachment on the bypass airflow path while maintaining accessibility for servicing.
Solution Approach 2:
A torque rod is introduced as an intermediary component to transmit rotational motion from the actuator to the activation ring, which then actuates the variable guide vanes. This mechanical linkage system enables remote actuation, allowing the actuator to be positioned away from the vanes while still providing effective control.
2Length of moving object
If the compressor case radial thickness is reduced to accommodate tip turbine design, then the engine length is reduced, but packaging actuators on the compressor case becomes difficult
Solution Approach 1:
The actuator positioning is moved from the radial dimension (on the thin compressor case) to the axial dimension (at the forward end of the compressor). This allows the actuator to be accommodated in the axial direction without requiring increased radial thickness, thus maintaining the compact engine length while providing sufficient space for the actuator and its plumbing.
3Ease of manufacture
If conventional axial flow engine structure is used, then variable guide vanes can be easily packaged on the compressor case, but the engine becomes elongated and complicated
Solution Approach 1:
The actuator is positioned in the axial direction at the forward end of the compressor rather than on the radial compressor case. This dimensional repositioning allows the actuator to be integrated into the compact tip turbine architecture without requiring an elongated engine structure, thereby maintaining ease of packaging while achieving a shorter overall engine length.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This configuration allows for the inclusion of variable compressor vanes in tip turbine engines, simplifies servicing, and maintains a compact engine design by avoiding the need to enlarge the splitter, thus optimizing packaging and accessibility.
Implementation Method 1
The torque rod rotatably drives an activation ring about the engine centerline
Implementation Method 2
The activation ring is coupled to each of the variable compressor vanes via levers, such that rotation of the activation ring about the engine centerline causes all of the variable compressor vanes to pivot
Data Source
AI summary
A turbine engine locates an actuator (55) for the compressor variable guide vanes (54a, b, c) at a location remote from the variable guide vanes. The actuator is connected to the variable guide vanes through a torque rod (56) inside an inlet guide vane. The torque rod rotatably drives an activation ring (57) about the engine centerline. The activation ring is coupled to each of the variable compressor vanes via linkage, such that rotation of the activation ring about the engine centerline causes all of the variable compressor vanes to pivot. With this configuration, a tip turbine engine can be more easily provided with variable compressor vanes for the axial compressor.