Edge Cooled Divergent Seals for Gas Turbine Nozzles
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing gas turbine engines with convergent/divergent nozzles face challenges in efficiently cooling the divergent sections, which are exposed to high temperatures, leading to potential gas leakage and reduced thrust efficiency.
Innovation Solution
The implementation of a cooled divergent seal arrangement featuring a body with a spine member, joint structure, and flap position guide, utilizing multiple intakes for cooling airflow that flows through longitudinal and edge channels to efficiently cool the divergent seals and flaps, thereby minimizing gas leakage and optimizing thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling air is used to cool the divergent sections, then the temperature of the divergent sections is maintained, but the cooling air utilization efficiency is insufficient
Solution Approach 1:
The divergent seal is divided into multiple segments with individual cooling channels (first cooling channel, second cooling channel, third cooling channel) that receive cooling air at different positions and direct it to specific cooling locations. This segmentation allows more precise control of cooling air distribution, improving utilization efficiency while maintaining temperature control of the divergent sections.
Solution Approach 2:
Different regions of the divergent seal are provided with dedicated cooling channels positioned to cool specific high-temperature areas. The first cooling channel cools the forward end section, the second cooling channel cools the aft end section, and the third cooling channel cools the gas path surface. This localized cooling approach optimizes cooling air usage by directing it precisely where needed rather than applying uniform cooling throughout.
2Temperature
If conventional cooling arrangements are used, then some cooling is provided, but gas leakage between flaps increases
Solution Approach 1:
Cooling air is introduced at multiple positions along the divergent seal before the hot gas can cause excessive heating and degradation. The cooling channels are positioned to deliver cool air to the seal surfaces in advance, creating a protective thermal barrier that maintains seal effectiveness and prevents gas leakage between flaps.
Solution Approach 2:
The cooling air acts as an intermediary substance between the hot exhaust gas and the divergent seal structure. By introducing this cooler intermediate fluid through strategically positioned channels, the seal is protected from direct thermal exposure, maintaining its dimensional stability and sealing effectiveness, thereby preventing gas leakage.
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 effectively utilizes cooling air to maintain the divergent sections' temperature, reducing gas leakage and enhancing the overall thrust efficiency of the gas turbine engine by ensuring efficient cooling of the divergent sections.
Implementation Method 1
Cooling airflow from the longitudinal channels is communicated through the multiple of edge channels to cool the edges of the divergent seals as well as the gas path surface of the adjacent divergent flaps
Implementation Method 2
The cooling airflow from the longitudinal channels is communicated through the multiple of edge channels to cool the edges of the divergent seals
Data Source
AI summary
A nozzle system includes a multitude of circumferentially distributed divergent seals that circumscribe an engine centerline. Each divergent seal includes a multiple of divergent seal intakes adjacent to a joint structure to receive cooling airflow. Each divergent seal body is manufactured of a metallic hot sheet inner skin and a metallic cold sheet outer skin. The skins form a multiple of longitudinal channels which communicate with a multiple of edge channels formed within the first longitudinal side and the second longitudinal side of each divergent seal. The multiple of edge channels are located transverse to the longitudinal axis and are raked aft to facilitate cooling of the gas path surface of each divergent seal and adjacent divergent flaps.