Gas Turbine Flow Distributor for Flame Temperature Control
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Solution Overview
Problem
Turbine engines face inefficiencies and mechanical anomalies due to inconsistent fuel flow to combustion zones, leading to high pattern factors and pressure oscillations, which existing control systems are insufficient to address, especially in hypersonic flight applications.
Innovation Solution
A flow distributor system with a balancing valve and multiple flow dividers that automatically equalizes fuel flow to each burner, using pressure adjustments and metered orifices to maintain consistent flow volumes across all combustion zones, thereby controlling the pattern factor and reducing temperature variations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If electronic control systems with temperature feedback are used to control pattern factor, then temperature profile control is achieved, but system cost, weight, and failure points increase
Solution Approach 1:
The flow distributor uses self-regulating flow dividers that automatically adjust fuel flow to each combustion zone based on local pressure conditions, eliminating the need for external electronic control systems. Each flow divider acts autonomously to maintain consistent fuel distribution without feedback sensors or actuators.
Solution Approach 2:
The patent replaces electronic control systems with a purely mechanical passive flow distribution system. The flow dividers use pressure-driven mechanical mechanisms to regulate fuel flow, substituting complex electronic feedback control with simple pressure-equalizing mechanical elements.
2Temperature
If electronic control systems are used for pattern factor control, then temperature variations are reduced, but system response time and accuracy are insufficient for high flow rates and pressures
Solution Approach 1:
The flow dividers automatically respond to pressure changes in real-time without electronic processing delays. Each flow divider self-adjusts based on local pressure conditions, providing instantaneous response to flow rate and pressure changes that electronic systems cannot match.
Solution Approach 2:
The system uses pressure-driven pneumatic mechanisms within the flow dividers to rapidly adjust fuel flow. The pressure differential across each flow divider directly controls fuel distribution, enabling fast response times suitable for high-flow-rate hypersonic flight applications.
3Device complexity
If passive flow distribution is used without active control, then system complexity is reduced, but fuel flow consistency to combustion zones deteriorates
Solution Approach 1:
The fuel distribution system is segmented into multiple independent flow dividers, each serving a specific combustion zone. This segmentation allows each divider to independently regulate fuel flow to its associated burner, maintaining precise flow distribution through simple mechanical means rather than a complex centralized control system.
Solution Approach 2:
The flow dividers are designed to equalize pressure across all combustion zones, creating equipotential conditions that naturally result in uniform fuel flow distribution. By maintaining equal pressure potential to each burner, the system achieves consistent fuel delivery without complex active control mechanisms.
4Manufacturing precision
If dimensioning tolerances of flow valves are tight, then fuel flow consistency is improved, but manufacturing cost and difficulty increase
Solution Approach 1:
The system uses multiple simple flow dividers with relaxed tolerances rather than a few complex precision valves. Each flow divider is a simple mechanical element that can be manufactured with standard tolerances, and the collective arrangement of multiple dividers achieves the required overall flow distribution uniformity.
Solution Approach 2:
The invention changes the design parameters from precision valve dimensions to pressure-equalizing flow divider geometry. This parameter change allows the use of simpler manufacturing processes with less stringent tolerances while achieving the same or better fuel flow consistency through pressure-based regulation rather than dimension-based control.
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 system ensures consistent fuel distribution, reducing temperature variations and mechanical anomalies, and operates effectively at high flow rates and pressures, eliminating the need for complex active control systems, thus enhancing turbine engine efficiency and reliability.
Implementation Method 1
The balancing valve has an inlet receiving media at a first pressure area and an outlet defining a plurality of first metering orifices. The valve member defines at least one second metering orifice receiving the media at a second pressure area.
Implementation Method 2
The outlet defining a plurality of first metering orifices. Each flow divider has an inlet receiving the media through an associated one of the first metering orifices at a third pressure area and an outlet defining one of a plurality of third metering orifices receiving the media at a fourth pressure area.
Implementation Method 3
The compressed air and fuel mixture is then ignited by one or more burners causing rapidly expanding air to flow through a turbine section. The overall flame temperature is actually an average of the flame temperature at each burner or combustion zone.
Data Source
AI summary
An equilibrating flow distributor for a gas turbine engine includes a balancing valve and multiple flow dividers, each with a movable valve or divider member. The balancing valve has an inlet receiving media at a first pressure area and an outlet defining a plurality of first metering orifices. The valve member defines at least one second metering orifice receiving the media at a second pressure area. Each flow divider has an inlet receiving the media through an associated one of the first metering orifices at a third pressure area and an outlet defining one of a plurality of third metering orifices receiving the media at a fourth pressure area. Each flow divider has a second pressure area in communication with second pressure area of the balancing valve. Flow through the fourth pressure area of each flow divider is substantially the same.