Gas Turbine Flow Path Member for Windage Heating Reduction
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Solution Overview
Problem
Existing gas turbine engine cooling systems face inefficiencies in directing fluid flow paths, particularly in reducing windage heating and ensuring thrust balance, which affects engine performance.
Innovation Solution
A unique flow path member, such as a conical flow shield, is positioned between the compressor and turbine shafts to direct cooling air and reduce windage heating, while allowing for radially and axially free movement, and is coupled with stiffening ribs and seal lands for stability, using materials like IN 718 sheet metal and GTAW welding.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a flow path member is positioned between the compressor and turbine shafts to direct cooling air, then windage heating is reduced and thrust balance is enhanced, but the device complexity increases
Solution Approach 1:
The flow path member is divided into multiple functional sections: a first section positioned between the compressor shaft and combustor, and a second section positioned between the turbine shaft and combustor. Each section independently directs cooling air to specific areas, reducing windage heating while maintaining thrust balance. This segmentation allows the complex function to be distributed across simpler, manageable components.
Solution Approach 2:
The flow path member serves multiple functions simultaneously: it directs cooling air to reduce windage heating, maintains thrust balance, and provides structural support between the compressor and turbine sections. By combining these functions into a single integrated component, the design achieves multiple objectives without proportionally increasing device complexity.
2Productivity
If a flow path member is added to direct cooling air and reduce windage heating, then engine performance is improved, but the manufacturing complexity increases
Solution Approach 1:
The flow path member is manufactured as separate first and second sections that can be produced independently using standard manufacturing processes. The first section is positioned between the compressor shaft and combustor, while the second section is positioned between the turbine shaft and combustor. This segmentation simplifies manufacturing by allowing each section to be optimized and produced separately, then assembled together.
Solution Approach 2:
The flow path member acts as an intermediary component that interfaces with existing engine structures (compressor shaft, turbine shaft, and combustor). By designing the member to fit within the existing engine architecture and use standard materials and processes, the manufacturing complexity is minimized while still achieving the performance improvements through optimized cooling air direction.
3Ease of operation
If the flow path member is designed with specific positioning between shafts and combustor, then cooling air direction is optimized, but the device complexity increases
Solution Approach 1:
The flow path member is segmented into distinct first and second sections with specific positioning functions. The first section is located between the compressor shaft and combustor to direct cooling air to the compressor area, while the second section is located between the turbine shaft and combustor to direct cooling air to the turbine area. This segmentation allows optimized cooling air direction to each component without requiring a single complex integrated design.
Solution Approach 2:
The flow path member utilizes three-dimensional positioning between the rotating shafts and the stationary combustor to optimize cooling air direction. By extending the member in multiple dimensions and positioning it strategically between the shafts and combustor, the design achieves effective cooling air distribution without requiring complex mechanical mechanisms, thereby limiting the increase in device complexity.
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 solution effectively reduces windage heating and enhances thrust balance by directing cooling air efficiently within the gas turbine engine, improving overall engine performance and operational stability.
Implementation Method 1
A flow path member is positioned between a compressor and a turbine of the gas turbine engine. The flow path member is configured to receive a flow of cooling air at a first end and direct the flow of cooling air at a second end.
Implementation Method 2
the flow path member is positioned between a flow path of the gas turbine engine and a rotating shaft of the gas turbine engine, the flow path member shielding the rotating shaft from a flow of cooling air
Data Source
AI summary
A gas turbine engine is disclosed having a compressor, combustor, and turbine and a flow path therethrough. A flow path member is disposed between an inner surface of the flow path and a rotating shaft that couples the compressor and turbine. The flow path member directs a cooling fluid along a path to cool a portion of the gas turbine engine between the inner surface and the rotating shaft. The flow path member is retained to permit radially free motion and can also be retained to permit axially free motion. The flow path member can have feed holes that permit the cooling fluid to pass.