Dilution Passage Arrangement for Gas Turbine Combustor
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Solution Overview
Problem
Gas turbine engine combustor sections face challenges in efficiently directing airflow due to variations in dilution passage designs, which can affect cooling efficiency and structural integrity under thermal and mechanical tolerances.
Innovation Solution
The design includes a liner panel with a major dilution passage and a minor dilution passage, each with a seal boss that seals around apertures in the support shell, and is surrounded by effusion passages, allowing for improved airflow direction and thermal management through a line-to-line interface during thermal excursions and mechanical tolerance adjustments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a dilution passage extension protrudes through the combustor shell, then sealing reliability is improved, but manufacturing complexity increases due to larger holes required in the combustor shell
Solution Approach 1:
The dilution passage is segmented into two parts: a portion within the liner panel and an extension protruding through the combustor shell. This segmentation allows the extension to provide reliable sealing through the shell while the liner panel integrates the passage, balancing manufacturing requirements with sealing reliability.
Solution Approach 2:
The dilution passage extension acts as an intermediary element between the liner panel and the combustor shell. It provides a protruding structure that enables effective sealing at the interface while maintaining manufacturability by defining a controlled aperture path through the shell.
2Temperature
If cooling airflow is increased to meet service life requirements, then thermal management is improved, but energy loss increases
Solution Approach 1:
The dilution passage modifies airflow parameters by directing cooling air through a controlled path with an extension that protrudes through the combustor shell. This changes the flow distribution and temperature conditioning of the cooling air, improving thermal management while optimizing energy utilization through the defined flow path.
Data Source
AI summary
A liner panel is provided for use in a combustor of a gas turbine engine. The liner panel includes a major dilution passage having a lip and a first seal boss. The liner panel also includes a minor dilution passage having a second seal boss adjacent the first seal boss.