Fuel Injector Perforated Plate Combustion Oscillation Control
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Solution Overview
Problem
Gas turbine engine combustor components are prone to damage and reduced operating life due to combustion oscillations resulting from resonance between fuel and air flows and heat release processes in fuel injectors.
Innovation Solution
A fuel injector design featuring a primary fuel gallery with a perforated plate and vane portions to control fuel flow, including adjustable perforations and outlets, which dampen oscillations by altering the impedance of the system and enhancing the interaction between main and pilot flames.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional fuel injector design is used, then fuel delivery function is maintained, but combustion oscillations damage components and reduce operating life
Solution Approach 1:
The patent utilizes the combustion oscillations that were previously harmful and damaging to the combustor components. By strategically positioning fuel outlets and configuring fuel passages, the invention converts these oscillations into beneficial effects that enhance mixing between fuel and air, improve combustion efficiency, and stabilize the flame. The oscillations are no longer treated as detrimental disturbances but as a mechanism to be harnessed for improved combustion performance.
Solution Approach 2:
The invention changes key parameters of the fuel delivery system including the number, size, and positioning of fuel outlets; the configuration and dimensions of fuel passages; and the arrangement of mixing zones. These parameter modifications alter the fuel flow characteristics and impedance to resonate with or dampen combustion oscillations, transforming the system's response to oscillatory conditions and improving component durability.
2Reliability
If fuel flow is restricted to reduce oscillations, then component durability improves, but fuel delivery efficiency may be compromised
Solution Approach 1:
The fuel delivery system is segmented into multiple independent fuel outlets distributed around the combustor periphery. Each outlet can be independently configured with specific sizing and positioning. This segmentation allows the system to restrict fuel flow in a distributed manner that reduces oscillations while maintaining overall fuel delivery efficiency through the collective action of multiple outlets.
Solution Approach 2:
The patent introduces intermediary mixing zones and air-fuel mixing passages between the fuel outlets and the main combustion chamber. These intermediaries allow fuel to be delivered and pre-mixed with air before entering the primary combustion zone, reducing oscillations while maintaining efficient fuel delivery through staged combustion.
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
The design effectively reduces combustor oscillations, increasing the durability and operating life of gas turbine engine components by optimizing the interaction between fuel and air flows, thereby stabilizing the combustion process.
Implementation Method 1
The primary perforated plate having a first perforation to restrict flow
Implementation Method 2
dampen oscillations by altering the impedance of the system
Implementation Method 3
combustion oscillations may be the result of resonance of the fuel and/or air flows in the fuel injectors with heat release process due to chemical reactions
Data Source
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AI summary
A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel delivery system for receiving and distributing fuel and an injector body. The injector body includes a primary fuel gallery, a pilot fuel gallery, a primary perforated plate, and a pilot distributor plate. The primary fuel gallery is formed as an annular cavity in the injector body and extends around an assembly axis. The primary fuel gallery and the pilot fuel gallery are in flow communication with the fuel delivery system. The primary perforated plate is disposed within the primary fuel gallery and divides the primary fuel gallery. The primary perforated plate having a first perforation to restrict flow. The pilot distributor plate is disposed within the center body assembly and radially inward of the first portion of the primary gallery, adjacent to portions of the tube stem. The pilot distributor plate having a pilot distributor passage to restrict flow.