Variable Area Turbine Nozzle Position Selector
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Solution Overview
Problem
Existing gas turbine engines face inefficiencies and increased maintenance costs due to the need for complex actuated systems to adjust nozzle vanes in response to varying ambient conditions, which can lead to distortion and stress on engine components.
Innovation Solution
A variable nozzle system with a position selector that allows for manual adjustment of nozzle airfoils into pre-selected positions, eliminating the need for continuous actuation and reducing maintenance costs by enabling external access for clocking position changes without disassembly of the engine.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If complex actuated systems are used to adjust nozzle vanes in response to varying ambient conditions, then engine efficiency can be optimized for different conditions, but device complexity and maintenance costs increase
Solution Approach 1:
The nozzle airfoils are designed to be adjustable between different clocking positions (e.g., first position for hot conditions, second position for cold conditions), allowing the engine to adapt to varying ambient conditions. This dynamic adjustability is achieved through a simplified mechanism rather than complex continuous actuation.
Solution Approach 2:
The system changes the operational parameters of the nozzle airfoils by switching between discrete clocking positions. Each position corresponds to different ambient temperature conditions, enabling the engine to optimize performance by selecting appropriate parameters without complex continuous control.
2Ease of operation
If complex linkage systems are used to adjust nozzle vanes, then precise control is achieved, but stress and distortion on engine components increase
Solution Approach 1:
The complex linkage system connecting the actuator to the nozzle airfoils is removed entirely. Instead, individual nozzle airfoils are adjusted independently using a simplified position selector mechanism, eliminating the stress and distortion caused by complex linkages while maintaining control precision.
Solution Approach 2:
The nozzle airfoil adjustment system is segmented into independent individual airfoils, each with its own position selector. This segmentation eliminates the need for a complex centralized linkage system, reducing component stress while allowing precise control of each airfoil's clocking position.
3Productivity
If actuated systems with linkages are used, then continuous adjustment is possible, but maintenance costs and repair difficulty increase
Solution Approach 1:
The position selector mechanism is designed to be externally accessible, allowing operators to manually adjust nozzle airfoils without disassembling engine components. This self-service capability significantly reduces maintenance costs and repair difficulty compared to systems requiring internal access and complex disassembly.
Solution Approach 2:
The complex actuated linkage system is removed and replaced with externally accessible position selectors. This extraction simplifies the overall system, making maintenance and adjustments easier while eliminating the high maintenance costs associated with complex internal linkage systems.
4Adaptability or versatility
If complex actuated systems are installed, then engine performance can be optimized, but initial manufacturing cost and device complexity increase
Solution Approach 1:
The system provides dynamic performance optimization through adjustable nozzle airfoil positions for different operating conditions. This adaptability is achieved through simple, manufacturable position selectors rather than complex actuated systems, reducing manufacturing costs while maintaining performance optimization capability.
Solution Approach 2:
The system enables performance optimization by allowing parameter changes (clocking positions) of the nozzle airfoils. These parameter changes are achieved through simple mechanical selectors that are easier and less costly to manufacture than complex actuated systems, while still providing the necessary adaptability for different operating conditions.
Data Source
AI summary
A gas turbine engine (100) variable nozzle (460) includes an outer shroud (461), an inner shroud (462), a variable nozzle airfoil (463), and a position selector (470). The inner shroud (462) is located radially inward from the outer shroud (461). The variable nozzle airfoil (463) extends radially between the outer shroud (461) and the inner shroud (462). The variable nozzle airfoil (463) includes a vane shaft (464) extending radially outward from the variable nozzle airfoil (463) through the outer shroud (461). The position selector (470) is coupled with the variable nozzle airfoil (463) to fixedly lock the variable nozzle airfoil (463) into one of a plurality of preselected positions.