Side-Initiated Augmentor Eliminates Flowpath Protrusions
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Solution Overview
Problem
Current gas turbine engine augmentor designs with components penetrating the engine flowpath cause flow losses and pressure drops, reducing engine efficiency and thrust during dry operation.
Innovation Solution
The introduction of a side-initiated fluid-based augmentor initiator with chambers in flow communication with air and fuel sources, featuring ejection openings that produce fuel-rich hot jets radially into the exhaust flowpath without any exhaust flowpath protrusions, eliminating the need for components that obstruct the flow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional augmentor components (spraybars, flameholders) are positioned within the engine flowpath, then flame stability and fuel dispersion are improved, but pressure losses and flow obstructions increase during dry operation
Solution Approach 1:
The augmentor components (spraybars, flameholders, fuel injectors) are extracted from the engine flowpath and repositioned in the exhaust section downstream of the turbine. This allows the engine to operate without flowpath obstructions during dry operation, eliminating pressure losses while maintaining the capability for thrust augmentation when fuel is injected in the exhaust section.
Solution Approach 2:
The augmentor function is moved from the radial dimension (components extending into the flowpath) to the axial dimension (components positioned in the exhaust section). The spraybars are oriented perpendicular to the exhaust flow, injecting fuel radially into the exhaust stream rather than into the compressor discharge flowpath.
2Power
If augmentor components are located within the engine flowpath, then thrust augmentation capability is provided, but engine efficiency decreases during dry operation due to flow obstruction
Solution Approach 1:
The augmentor components are extracted from the main engine flowpath and relocated to the exhaust section. This separation allows the engine to maintain high efficiency during dry operation without flowpath obstructions, while still providing full thrust augmentation capability when fuel is injected and combusted in the exhaust section downstream of the turbine.
Solution Approach 2:
The exhaust section serves as an intermediary zone where fuel injection and combustion occur outside the main engine flowpath. This intermediary location allows thrust augmentation to occur without interfering with the efficient operation of the compressor and turbine during dry operation.
3Quantity of substance
If spraybars and flameholders extend radially into the exhaust flowpath, then fuel dispersion is improved, but flow losses and pressure drops are created
Solution Approach 1:
The spraybars are oriented perpendicular to the exhaust flow direction, injecting fuel radially into the exhaust stream rather than axially along the flowpath. This dimensional change allows effective fuel dispersion and atomization while avoiding the creation of flow obstructions and pressure drops associated with radial extensions into the exhaust flowpath.
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 configuration minimizes pressure losses and maintains thrust performance by ensuring no dry-loss due to pressure drops during unfueled operation, enhancing engine efficiency and reducing specific fuel consumption.
Implementation Method 1
The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath
Implementation Method 2
The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath
Data Source
AI summary
A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.