Variable Area Turbine Nozzle for High-Altitude Performance
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Solution Overview
Problem
Existing turbine systems face challenges in maintaining optimal performance across varying operational demands, particularly at high altitudes and during rapid power changes, leading to issues like surge conditions and inefficiencies due to fixed nozzle geometries, which result in weight penalties and reduced time-on-wing.
Innovation Solution
A variable area turbine nozzle (VATN) system with rotating vanes that adjust the flow area and pressure ratio by positioning vanes to match changing operational requirements, allowing the turbine engine to operate like multiple engines of different sizes, thereby compensating for changing conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of stationary object
If a fixed nozzle geometry is used in the turbine system, then the structure is simple and weight is reduced, but the performance deteriorates at high altitudes and during rapid power changes
Solution Approach 1:
The patent applies the Dynamics principle by transforming the fixed nozzle geometry into a variable geometry system. The turbine nozzle includes movable vanes that can change the flow area dynamically to adapt to different operating conditions. This allows the nozzle to optimize performance across extreme operating ranges including high-altitude operations and rapid power changes, resolving the contradiction between structural simplicity and operational adaptability.
2Reliability
If midcompressor bleed is used to control surge, then surge control is achieved, but device complexity and weight increase due to complex manifolds, large piping and large bleed valves
Solution Approach 1:
The patent applies the Taking out principle by removing the complex midcompressor bleed system (manifolds, piping, and large bleed valves) and replacing it with a simpler variable area turbine nozzle system. The surge control function is extracted from the compressor side and implemented on the turbine side through nozzle area modulation, significantly reducing device complexity while maintaining surge control capability.
Solution Approach 2:
The patent uses the variable area turbine nozzle as an intermediary mechanism to control surge conditions. Instead of directly controlling surge at the compressor through complex bleed systems, the nozzle area is modulated to indirectly control the flow and pressure conditions, acting as a mediator between the turbine and compressor systems to prevent surge.
3Reliability
If midcompressor bleed is used to control surge, then surge control is achieved, but weight penalties increase due to large piping and components
Solution Approach 1:
The patent removes the heavy midcompressor bleed system components (manifolds, large piping, and bleed valves) and replaces them with a lightweight variable area turbine nozzle system. This extraction of the surge control function to the turbine side eliminates the need for heavy structural components while maintaining effective surge control.
4Adaptability or versatility
If a variable area turbine nozzle is implemented, then high-altitude performance and time-on-wing are improved, but device complexity increases due to moving vanes and actuation systems
Solution Approach 1:
The patent implements a dynamic variable area turbine nozzle system with movable vanes and actuation mechanisms that can adapt to different operating conditions. This dynamic capability enables high-altitude performance improvement and extended time-on-wing, while the complexity is managed through integrated control systems that coordinate vane positioning with engine operating parameters.
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
The VATN system enhances high-altitude performance, extends time-on-wing, and improves starting capability by actively controlling flow and pressure ratios, reducing weight penalties and maintaining efficient operation across extreme operating ranges.
Implementation Method 1
Vanes are disposed in the turbine inlet nozzle and rotate to vary a flow area through which the core flow passes
Implementation Method 2
A turbine receives a core flow of the combusted gas to rotate a turbine rotor
Implementation Method 3
a compressor that receives and compresses incoming gas such as air that is received through an inlet
Implementation Method 4
a combustor in which the compressed gas is mixed with fuel and burned to produce high-pressure, high-temperature gas
Data Source
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AI summary
A gas turbine engine with a compressor supplying compressed air. A combustor receives the compressed air and fuel and generates a flow of combusted gas. A turbine receives a core flow of the combusted gas to rotate a turbine rotor. A turbine inlet nozzle directs the combusted gas to the turbine rotor. Vanes are disposed in the turbine inlet nozzle and rotate to vary a flow area through which the core flow passes. The vanes adjust a pressure ratio of the gas turbine engine to compensate for changing operational requirements of the gas turbine engine by rotating to positions matching the changing operational requirements.