Integrated Fuel Nozzle with Optical Sensor Feedback Control
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Solution Overview
Problem
Existing feedback control systems for gas turbine engine combustors are too heavy and compromise structural integrity, making them unsuitable for aircraft engines due to elevated temperatures and pressures, and require additional housing penetrations.
Innovation Solution
A fuel nozzle assembly with an integrated optical sensor and trim valve, where the sensor detects parameters like air/fuel ratio within the combustion chamber, allowing the controller to adjust fuel delivery without additional housing penetrations, using a sensor housed within the nozzle to maintain structural integrity and reduce weight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a separate sensor, valve and fuel nozzle are used for feedback control, then feedback control functionality is achieved, but weight increases and structural integrity is compromised
Solution Approach 1:
The patent combines the sensor, trim valve, and fuel nozzle into a single integrated fuel nozzle assembly. The sensor is positioned within the nozzle housing to detect combustion parameters, while the trim valve is integrated into the same assembly to adjust fuel flow based on sensor feedback. This merging eliminates the need for separate components and their associated mounting structures, thereby reducing weight while maintaining feedback control functionality.
2Reliability
If separate components are used for feedback control, then sensing and control functions are achieved, but additional penetrations into housing diffuser case are required
Solution Approach 1:
By integrating the sensor and trim valve into the existing fuel nozzle assembly, the patent utilizes the fuel nozzle's existing penetration through the diffuser case housing. This eliminates the need for additional penetrations, as the integrated assembly uses the same pathway that the fuel nozzle already provides, thereby reducing structural complexity and maintaining sealing integrity.
3Weight of moving object
If integrated sensor and trim valve are used, then weight is reduced and structural integrity is maintained, but feedback control robustness may be compromised
Solution Approach 1:
The patent positions the sensor within the nozzle housing at a specific location optimized for detecting combustion parameters. The sensor is strategically placed to monitor the combustion process closely while being protected by the nozzle housing structure. The trim valve is integrated into the same assembly with direct access to the fuel line, enabling precise local control of fuel flow based on real-time sensor feedback, thereby maintaining robustness despite the 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 provides robust feedback control that balances fuel delivery across multiple nozzles, enhancing fuel efficiency and reducing emissions without increasing weight or compromising the engine's reliability, while being easily replaceable and integrated within the existing nozzle structure.
Implementation Method 1
In one example, the sensor is an optical sensor coupled to an optical decoder for ascertaining the parameter. The optical sensor 'sees' into the combustion chamber and detects at least one of oxygen, nitrogen, water, carbon monoxide, carbon dioxide, and a hydrocarbon to determine an air fuel ratio within the combustion chamber
Data Source
AI summary
A gas turbine engine includes a combustor having a fuel nozzle assembly for delivering fuel to a combustion chamber. A sensor is at least partially housed within the fuel nozzle assembly for sensing a parameter associated with the delivery of fuel to the combustion chamber. In one example, the sensor is an optical sensor coupled to an optical decoder for ascertaining the parameter. A trim valve is in communication with the fuel nozzle assembly. A controller is in communication with the sensor and is programmed to actuate the trim valve to adjust the amount of fuel delivered through the fuel nozzle assembly in response to the parameter. In one example, an end of the optical sensor is arranged near a fuel exit of the fuel nozzle assembly. The controller actuates the trim valve for the fuel nozzle assembly to achieve a desired air/fuel ratio and/or balance the fuel delivery of the fuel nozzle assembly relative to another fuel nozzle assembly within the gas turbine engine's combustor system.