Variable Vane Airfoil Recess for Protuberance Clearance
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Solution Overview
Problem
Existing variable vane arrays in gas turbine engines have limitations in achieving large pivot angles, which restrict their ability to effectively regulate airflow into the compressor section.
Innovation Solution
The design includes a variable vane with a pivot axis that can pivot more than forty degrees, featuring an airfoil with a recess at one end that aligns with a protuberance when in the second position, allowing for increased pivot range and airflow regulation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a variable vane array is designed with large pivot angles to enhance airflow regulation, then airflow control capability is improved, but the risk of collision between vanes and protuberances increases
Solution Approach 1:
The invention extracts the conflicting element (protuberance) from the collision path by providing a recess in the airfoil that accommodates the protuberance. This allows the vane to pivot through large angles without the airfoil colliding with the protuberance, thereby resolving the contradiction between achieving large pivot angles for airflow regulation and avoiding collisions with structural features.
2Productivity
If the pivot angle is increased beyond forty degrees to improve airflow metering, then airflow control is enhanced, but the structural complexity of accommodating the increased range increases
Solution Approach 1:
The invention resolves the structural complexity issue by adding a dimensional feature (recess) to the airfoil cross-section that accommodates the protuberance in the spanwise direction. This allows the vane to achieve large pivot angles (greater than forty degrees) without requiring complex mechanical restraint systems, as the recess provides geometric clearance for the increased range of motion.
Data Source
AI summary
A gas turbine engine apparatus includes an engine flowpath, a protuberance and a variable vane. The protuberance projects into the engine flowpath. The variable vane extends across the engine flowpath. The variable vane includes a pivot axis and an airfoil. The variable vane is configured to pivot about the pivot axis between a first position and a second position. The airfoil extends spanwise along a span line between a first end and a second end. The airfoil extends chordwise along a chord line between a leading edge and a trailing edge. A recess extends spanwise into the airfoil from the first end. The airfoil, at the first end, is spaced from the protuberance when the variable vane is in the first position. The airfoil, at the first end, is aligned with the protuberance and the protuberance projects into the recess when the variable vane is in the second position.