Local Vortex Generator Array for Turbomachine Stator
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Solution Overview
Problem
Existing turbomachines, such as gas turbine engines, face challenges with increased pressure losses and flow deviation in the stator of the compressor section, leading to reduced efficiency and increased specific fuel consumption.
Innovation Solution
The implementation of a local vortex generator array on the suction side of the airfoils in the turbomachine, extending onto the hub or shroud, to reduce pressure losses and flow deviation by introducing vorticity into the airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If cycle pressure ratios are increased to improve gas turbine engine performance, then aerodynamic loading in the compressor section is increased, but pressure losses and flow deviation in the stator increase, reducing efficiency
Solution Approach 1:
Vortex generators are placed at specific locations on the stator airfoils (suction side, extending onto hub or shroud) rather than uniformly across the entire surface. This localized placement creates vorticity precisely where needed to control boundary layer behavior and reduce pressure losses, while maintaining high aerodynamic loading in other regions.
Solution Approach 2:
The vortex generators act as intermediary elements that introduce controlled vorticity into the airflow. These vortices serve as a mediator between the high-speed mainstream flow and the boundary layer, enhancing mixing and preventing adverse pressure gradient effects that cause flow separation and energy losses.
2Power
If cycle pressure ratios are increased to improve gas turbine engine performance, then aerodynamic loading in the compressor section is increased, but flow deviation in the stator increases, reducing efficiency
Solution Approach 1:
Vortex generators are strategically positioned at specific spanwise and chordwise locations on the stator airfoils to address flow deviation locally. The localized vorticity generation corrects flow angles and reduces deviation without affecting the overall aerodynamic loading characteristics of the high-pressure ratio compressor.
3Loss of energy
If local vortex generator array is added to reduce pressure losses, then aerodynamic efficiency is enhanced, but device complexity increases
Solution Approach 1:
The vortex generator array is divided into multiple discrete elements arranged in a pattern across the stator airfoil surface. This segmentation allows for optimized placement at critical locations (suction side, hub region, shroud region) while maintaining manufacturing feasibility and avoiding the complexity of a continuous or overly dense configuration.
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 local vortex generator array effectively minimizes flow deviation and pressure losses, enhancing the aerodynamic efficiency of the compressor section, reducing specific fuel consumption, and allowing for increased cycle pressure ratios.
Implementation Method 1
The at least one local vortex generator array is defined on the suction side so as to extend onto the hub or the shroud
Data Source
AI summary
A turbomachine includes a shroud and a hub spaced apart from the shroud to channel an airflow along a direction. The turbomachine includes a plurality of airfoils coupled between the shroud and the hub. At least one airfoil of the plurality of airfoils includes a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side. The at least one airfoil has a chord that is 0% chord at the leading edge and 100% chord at the trailing edge, and a span defined as 0% at the hub and 100% at the shroud. The turbomachine includes at least one local vortex generator array defined onto the hub between 0% chord to −10% chord at 0% span so as to extend forward of the leading edge.