Stator Vane Cooling Passage Connection for Gas Turbines
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Solution Overview
Problem
The complex geometry of cooling passages in gas turbine stator vanes prevents the combination of ceramic cores into a single core, leading to suboptimal cooling air sources and reduced producibility, as well as inefficient thermal conditioning due to separate cooling airflow sources.
Innovation Solution
A connection passage is formed between the external surface and internal cooling passages of the stator vane, allowing a common cooling airflow source to supply both passages, with a closure such as a plug or cover secured over the external surface opening to prevent leakage, improving producibility and thermal conditioning.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Shape
If separate ceramic cores are used to form cooling passages, then the complex geometry of cooling passages can be achieved, but producibility is reduced and multiple cooling airflow sources are required
Solution Approach 1:
The cooling passages are segmented into multiple zones (e.g., leading edge cooling passages and platform cooling passages) that can be independently configured but are fed from a single unified cooling source, allowing complex geometry while simplifying manufacturing and airflow management
Solution Approach 2:
A single cooling airflow source serves multiple functions by supplying cooling air to both the leading edge cooling passages and platform cooling passages through the stator vane, eliminating the need for separate cooling sources and simplifying the manufacturing process
2Shape
If separate ceramic cores are used for cooling passages, then complex geometry is achieved, but multiple cooling airflow sources are required which is not optimal
Solution Approach 1:
The cooling system is designed so that a single cooling airflow source performs multiple functions by supplying cooled air to different regions of the stator vane (leading edge and platform areas) through a unified cooling passage network, optimizing energy utilization
3Shape
If separate cooling airflow sources are used, then complex passage geometry is achieved, but thermal conditioning efficiency is reduced
Solution Approach 1:
Multiple cooling passages (leading edge cooling passages and platform cooling passages) are merged into a unified cooling system fed from a single cooling source, improving thermal conditioning efficiency by coordinating cooling across different regions of the stator vane while maintaining the necessary complex geometry
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 enhances the producibility and efficiency of gas turbine engines by utilizing a single optimal cooling airflow source for both vane leading edge and platform cooling passages, improving thermal conditioning and engine durability.
Implementation Method 1
cooling airflow to flow through, and additionally may have openings in an outer surface of the vane for cooling airflow to exit the interior of the vane structure and form a cooling film of air over the outer surface
Implementation Method 2
cooling airflow to maintain turbine components within this particular temperature range
Implementation Method 3
a closure secured over the passage opening to prevent leakage of the cooling fluid flow through the passage opening
Implementation Method 4
The closure may be secured over the passage opening via welding or brazing
Implementation Method 5
The closure may be secured over the passage opening via welding or brazing
Data Source
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AI summary
The invention is related to turbine stator (46) for gas turbine engines, including a stator vane (52), a first cooling passage (58) for providing a cooling fluid flow to a first portion of the stator (46), e.g., the leading edge (60), and a second cooling passage (62) for providing a cooling fluid flow to a second portion of the stator, e.g., the outer vane platform (54). A connection passage (70) extends at least partially through the stator (46) to connect an inlet (66) of the first cooling passage (58) to an inlet (64) of the second cooling passage (62). Thus, the cooling fluid flow is directed from a common cooling flow source (68) into the first cooling passage (58) and the second cooling passage (62) via the first cooling passage inlet (66). Thus, due to complex geometries, the cooling channels (58,62) may be machined separately improving manufacturability.