Gas Turbine Combustor Bypass Flow Reintroduction
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Solution Overview
Problem
Existing gas turbine combustion bypass systems suffer from flame quenching and high atmospheric pollutant emissions when reintroducing bypass flow as a single dilution jet, causing distortions in the hot gas temperature profile, which cannot be tailored to meet downstream hardware thermal requirements during load reductions.
Innovation Solution
A system where compressor discharge air is bypassed through an extraction manifold and reintroduced downstream of the reaction zone via reintroduction slots, with optional cooling holes to maintain temperature control, allowing for tailored temperature profiles and reduced pollutant emissions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If bypass flow is reintroduced as a single dilution jet directly into the duct, then the bypass air can be introduced downstream of the combustor, but flame quenching and high levels of atmospheric pollutants occur
Solution Approach 1:
The patent divides the single dilution jet into multiple separate jets that are distributed around the duct perimeter. This segmentation prevents the concentrated cooling effect that causes flame quenching while still achieving the desired bypass flow introduction downstream of the combustor.
Solution Approach 2:
The patent creates different local conditions by distributing bypass flow through multiple jets at different locations around the duct. Each jet can be optimized for its specific position, allowing tailored temperature profiles in different regions while preventing localized flame quenching.
2Temperature
If combustor bypass air is introduced directly into the duct at one localized spot, then the bypass flow can be reintroduced, but distortions in the temperature pattern and profile of the hot gas occur
Solution Approach 1:
The patent segments the bypass flow introduction into multiple distributed jets rather than a single localized injection point. This distribution prevents localized temperature distortions and creates a more uniform temperature profile in the hot gas flowing to the turbine.
Solution Approach 2:
The patent extracts the bypass flow from the traditional single-point injection approach and redistributes it through multiple jets. This extraction of the problematic concentrated injection method eliminates the temperature pattern distortions while maintaining the bypass functionality.
3Adaptability or versatility
If bypass flow is reintroduced as a single dilution jet, then the system structure is simpler, but the effect on pattern and profile cannot be tailored to meet downstream hardware thermal requirements
Solution Approach 1:
The patent segments the bypass flow system into multiple controllable jets that can be individually optimized. This segmentation provides the adaptability to tailor temperature profiles for downstream hardware thermal requirements while distributing the complexity across multiple standardized components.
Solution Approach 2:
The patent transitions from a single-point (zero-dimensional) bypass injection to a distributed multi-point (three-dimensional) injection system. This dimensional change enables spatial distribution of the bypass flow, allowing tailored temperature profiles that match downstream hardware requirements.
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 approach reduces flame quenching and pollutant emissions, enabling tailored temperature profiles that meet downstream hardware thermal requirements, enhancing operational efficiency and emissions compliance during turndown operations.
Implementation Method 1
one or more reintroduction slots in communication with the reintroduction manifold for injecting the combustor bypass air into the combustor body downstream of the reaction zone
Implementation Method 2
one or more cooling holes for providing cooling air to the one or more reintroduction slots
Implementation Method 3
the combustor body includes a reaction zone for primary combustion of fuel and air
Data Source
AI summary
A system and method for reintroducing gas turbine combustion bypass flow. The system may include a combustor body, wherein the combustor body includes a reaction zone for primary combustion of fuel and air, and a casing enclosing the combustor body and defining an annular passageway for carrying compressor discharge air into the combustor body at one end. The system further may include a reintroduction manifold for receiving combustor bypass air extracted from the compressor discharge air in the annular passageway, and one or more reintroduction slots in communication with the reintroduction manifold for injecting the combustor bypass air into the combustor body downstream of the reaction zone. The method may include extracting combustor bypass air from the annular passageway, transporting the combustor bypass air to a reintroduction manifold, and reintroducing the combustor bypass air into the combustor body through one or more reintroduction slots in communication with the reintroduction manifold.