Multi-Impingement Plate Assembly for Gas Turbine Cooling
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Solution Overview
Problem
Existing Blade Outer Air Seal (BOAS) designs in gas turbine engines face challenges in efficiently managing thermal variations and dynamic loads, particularly in high-pressure turbine sections, where conventional cooling methods may not adequately distribute cooling airflow to maintain optimal temperature control and operational efficiency.
Innovation Solution
A multi-impingement plate assembly is introduced, featuring a first and second impingement plate with specific hole arrangements and passages that facilitate the recirculation of secondary cooling airflow between cavities within the BOAS segments, enhancing cooling efficiency and reducing temperature gradients.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling methods are used in BOAS segments, then the structure is simple, but cooling efficiency is insufficient and temperature control is inadequate
Solution Approach 1:
The cooling structure is divided into multiple impingement plates (first impingement plate, second impingement plate, third impingement plate) with distinct cavities (first cavity, second cavity, third cavity). Each plate and cavity combination creates a localized cooling zone, allowing temperature control at different positions along the BOAS segment. This segmentation enables improved temperature control while maintaining manageable structural complexity through modular design.
Solution Approach 2:
The cooling airflow is directed to impinge upon the BOAS segment at multiple locations along its length, transitioning from a single-point or single-zone cooling approach to a multi-zone distributed cooling system. The secondary cooling airflow communicates between cavities and impingement plates at different axial positions, creating a three-dimensional cooling pattern that enhances temperature control effectiveness.
2Productivity
If multiple impingement plates with cavity communication are used, then cooling efficiency improves, but manufacturing complexity increases
Solution Approach 1:
The multi-impingement plate assembly is divided into discrete plates (first, second, third impingement plates) with associated cavities. Each plate-cavity combination can be manufactured independently as a modular unit, allowing for standardized production processes. The segmentation enables parallel manufacturing of individual components, improving overall productivity while controlling manufacturing complexity through repetition of similar structural elements.
Solution Approach 2:
The impingement plates and cavities are arranged in a nested configuration where the first, second, and third impingement plates are positioned within or adjacent to corresponding cavities. The secondary cooling airflow pathways are nested within the structure, communicating between cavities through defined passages. This nested arrangement consolidates multiple cooling functions into a compact assembly, enhancing cooling efficiency while managing manufacturing complexity through integrated design.
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 achieves a 0.06% reduction in cooling flow requirements and a corresponding 0.006% decrease in Thrust Specific Fuel Consumption (TSFC), while extending the operational life of BOAS segments by maintaining lower temperatures through improved axial crossflow heat transfer and pressure management.
Implementation Method 1
A multiple of impingement plates are provided within the body and a multiple of cavities within the body are defined axially spaced apart. A first passage provides fluid communication for a secondary cooling airflow from a forward one of the cavities to a rearward one of the cavities. The cooling airflow impinges upon only a portion of the BOAS segment in the forward cavity and is then directed to impinge again upon a portion of the BOAS segment in the rearward cavity.
Implementation Method 2
The cooling airflow impinges upon only a portion of the BOAS segment in the forward cavity and is then directed to impinge again upon a portion of the BOAS segment in the rearward cavity.
Data Source
Figure 1
Figure 2
Figure 3~4
AI summary
A multi impingement plate assembly (54) for a Blade Outer Air Seal (40) includes a first impingement plate (60) which defines a multiple of first impingement plate holes (68) and a second impingement plate (62) attached to the first impingement plate (60). The second impingement plate (62) includes a platform section (70) spaced away from the multiple of first impingement plate holes (68) to define a plate cavity (78).