Angled Cooling Holes in Gas Turbine Diaphragms
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Solution Overview
Problem
Gas turbine engines face inefficiencies due to uncontrolled cooling air leakage and improper cooling, which reduces the engine's efficiency and can lead to premature wear of turbine components.
Innovation Solution
A gas turbine engine diaphragm with angled holes is designed to direct cooling air with a matching angular velocity to the adjacent turbine disk, providing predictable and efficient cooling, while stress relief regions reduce stress concentrations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is directed through internal cooling passages from the compressor, then the turbine section is cooled, but the efficiency of the gas turbine engine is reduced
Solution Approach 1:
The patent applies local quality by providing different cooling solutions to different parts of the turbine assembly. The diaphragm receives cooling through angled holes that direct air to specific locations, while the turbine disk receives cooling through axial holes. This localized approach ensures each component is cooled where needed without unnecessarily reducing overall engine efficiency.
Solution Approach 2:
The patent transitions from traditional axial cooling passages to angled holes in the diaphragm that direct cooling air in radial and axial dimensions simultaneously. This dimensional change allows cooling air to reach the turbine disk more effectively while minimizing the impact on engine efficiency compared to conventional axial-only cooling.
2Temperature
If cooling air leakage is uncontrolled, then cooling is provided, but loss of efficiency and improper cooling occur
Solution Approach 1:
The patent incorporates feedback mechanisms through carefully designed hole configurations and positioning that respond to thermal conditions. The angled holes in the diaphragm and axial holes in the turbine disk are positioned to provide cooling feedback based on the thermal state of each component, preventing both over-cooling and under-cooling while minimizing energy loss.
Solution Approach 2:
The patent changes parameters such as hole angle, hole position, and hole diameter to optimize cooling effectiveness. The angled holes in the diaphragm are specifically oriented to direct cooling air to the turbine disk at the appropriate angle, while the axial holes in the turbine disk provide targeted cooling. These parameter changes ensure efficient cooling without excessive energy loss.
3Temperature
If traditional cooling passages are used, then cooling is provided, but stress concentrations occur in the diaphragm
Solution Approach 1:
The patent segments the cooling function into separate pathways: angled holes in the diaphragm for directing cooling air, and axial holes in the turbine disk for direct cooling. This segmentation allows each component to be optimized for both cooling and stress resistance, with the diaphragm's angled holes distributing stress more evenly than traditional passages.
Solution Approach 2:
The patent employs composite material strategies by integrating the cooling hole system with the diaphragm and turbine disk structures. The angled and axial holes are strategically positioned and dimensioned to work with the material properties of the diaphragm and disk, creating a composite structure that provides both cooling and stress resistance.
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 configuration enhances the cooling efficiency, extends the service life of turbine components, and maintains engine performance by ensuring consistent and effective cooling, even under thermal expansion.
Implementation Method 1
a plurality of angled holes configured to direct cooling air to the turbine disk with a matching angular velocity
Data Source
AI summary
A gas turbine engine turbine diaphragm (460) includes an inner cylindrical portion (461), a mounting portion (463), and a disk portion (462). The mounting portion (463) is located radially outward from the inner cylindrical portion (461). The disk portion (462) extends radially between the inner cylindrical portion (461) and the mounting portion (463). The disk portion (462) includes a plurality of angled holes (464). Each angled hole (464) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular to a radial extending from an axis of the diaphragm (460). The component of the vector is angled relative to an axial direction of the diaphragm (460).