Inter-Turbine Duct Splitter Blades with Vortex Generators
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Solution Overview
Problem
Conventional gas turbine engines face performance issues due to boundary layer separation in inter-turbine ducts, which are often elongated to mitigate this problem, resulting in suboptimal size ratios between high and low pressure turbines and increased weight and efficiency losses.
Innovation Solution
The use of splitter blades with vortex generating structures on the suction side within the inter-turbine duct to prevent and mitigate boundary layer separation, allowing for shorter duct lengths and improved airflow transition between turbines.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of stationary object
If the inter-turbine duct length is decreased to reduce weight and improve compactness, then the radial angle increases which causes boundary layer separation and deteriorates low pressure turbine performance
Solution Approach 1:
A flow control mechanism is introduced as an intermediary element within the inter-turbine duct to manage the airflow and prevent boundary layer separation. This mediator component allows the duct to maintain a shorter length with a more aggressive radial angle while still protecting the low pressure turbine performance by controlling the flow characteristics between the high and low pressure turbines.
2Length of moving object
If the inter-turbine duct length is decreased to improve compactness, then the radial angle increases which may result in boundary layer separation and increases pressure losses
Solution Approach 1:
The flow control mechanism serves as a mediator that enables the duct to achieve a shorter axial length with a more aggressive radial angle without incurring excessive pressure losses. By actively managing the boundary layer through this intermediary device, the design can optimize compactness while maintaining acceptable pressure loss characteristics.
3Length of moving object
If the inter-turbine duct is designed with a more aggressive radial angle to reduce axial length, then compactness improves but boundary layer separation occurs deteriorating airflow quality
Solution Approach 1:
The flow control mechanism is positioned within the inter-turbine duct to act as a mediator that prevents boundary layer separation caused by aggressive radial angles. This intermediary element allows the duct geometry to be optimized for compactness with shorter axial length while the flow control device actively manages the airflow to maintain attachment and prevent separation, thereby preserving airflow quality.
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 solution enables more compact and efficient turbine designs by reducing pressure losses and maintaining smooth airflow, allowing for a more aggressive radial angle and shorter axial length in the inter-turbine duct, thereby improving the overall efficiency and reducing weight.
Implementation Method 1
The use of splitter blades with vortex generating structures on the suction side within the inter-turbine duct to prevent and mitigate boundary layer separation
Implementation Method 2
boundary layer separation of the flow within the duct, which may adversely affect the performance of the low pressure turbine
Data Source
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AI summary
A turbine section is provided for a gas turbine engine. The turbine section is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct being defined by a hub and a shroud; and at least a first splitter blade disposed within the inter-turbine duct. The first splitter blade includes a pressure side facing the shroud, a suction side facing the hub, and at least one vortex generating structure positioned on the suction side.