Gas Turbine Stator Vane Cooling via Oriented Stationary Member Holes
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Solution Overview
Problem
The stator vane stage in gas turbines experiences increased temperature due to heating from two sides, making it difficult to cool effectively using existing cooling air distribution configurations.
Innovation Solution
A stator vane assembly with an annular stationary member and stator vane segments, where holes penetrating through the stationary member from the outer side to the inner side are oriented towards the circumferential-direction end portions of the shrouds, allowing for intensified cooling of the heated areas.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is supplied uniformly to the stator vane stage, then the overall cooling is maintained, but the circumferential-direction end portions of the shrouds (heated from two sides) cannot be cooled effectively
Solution Approach 1:
The patent applies local quality by providing differentiated cooling air supply to different regions of the stator vane stage. Specifically, the circumferential-direction end portions of the shrouds (which are heated from two sides and require more cooling) are provided with dedicated cooling air passages, while other portions receive cooling through the general cooling air supply. This localized cooling approach addresses the higher temperature requirements of specific heated regions without requiring complete redesign of the entire cooling system.
Solution Approach 2:
The cooling air supply system is segmented into multiple independent passages. The patent divides the cooling air supply into a general cooling air passage for overall cooling and specific cooling air passages directed at the circumferential-direction end portions of the shrouds. This segmentation allows independent control and optimization of cooling air distribution to different thermal zones, enabling effective cooling of critical heated areas while maintaining overall system simplicity.
2Temperature
If the number of cooling air passages is increased to cool all heated areas, then cooling effectiveness is improved, but the device complexity and manufacturing difficulty increase
Solution Approach 1:
Instead of uniformly increasing cooling throughout the entire stator vane stage, the patent applies local quality by providing enhanced cooling only at the circumferential-direction end portions of the shrouds where heating from two sides creates critical temperature conditions. This targeted approach achieves effective cooling of the most problematic areas while avoiding the manufacturing complexity that would result from adding numerous cooling passages throughout the entire structure.
3Temperature
If cooling air is directed intensively to the circumferential-direction end portions of shrouds, then cooling effectiveness is improved, but the overall cooling distribution becomes unbalanced
Solution Approach 1:
The patent segments the cooling air supply into distinct passages: a general cooling air passage that provides uniform cooling to the overall stator vane stage, and specific cooling air passages that direct cooling air intensively to the circumferential-direction end portions of the shrouds. This segmentation enables intensive cooling of critical heated areas while maintaining balanced overall cooling distribution through the general passage, preventing thermal imbalance across the stator vane stage.
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 enables effective cooling of the circumferential-direction end portions of the shrouds, which are prone to higher temperatures, by directing cooling air directly to the heated areas, thereby improving cooling efficiency.
Implementation Method 1
a cooling air passage penetrating through the inner casing of a turbine casing from the radially outer side toward the radially inner side. The cooling air after passing through the cooling air passage is utilized in cooling of a stator vane stage disposed inside the turbine casing
Implementation Method 2
The temperature of the part heated from two sides as described above tends to increase readily, and thus requires more cooling than other parts
Data Source
AI summary
A stator vane assembly of a gas turbine includes: a stationary member formed to have an annular shape; and a plurality of stator vane segments each including a shroud and a vane body, the plurality of stator vane segments disposed along a circumferential direction of the stationary member at a radially inner side of the stationary member such that a cavity is disposed between the shrouds and the stationary member and the shrouds are disposed adjacent to one another in the circumferential direction of the stationary member. The stationary member has a hole which penetrates through the stationary member from a radially outer side toward the radially inner side, and a center axis of the hole is oriented toward a circumferential-direction end portion of the shroud.