Reverse Core Turbine Engine Above Wing
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Solution Overview
Problem
Existing gas turbine engines for aircraft applications are not effectively designed for compact mounting above an aircraft wing, limiting their integration and efficiency.
Innovation Solution
A reverse core gas turbine engine configuration with a fan, core turbine, combustor, and compressor arranged in series, where the core engine is centered on a non-parallel axis to the fan, and a free turbine drives the fan through gear reduction, with a particle separator and exhaust nozzle positioned for optimal airflow and compactness.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If a conventional axial gas turbine engine is used with all components centered on a common axis, then the engine structure is simple and easy to manufacture, but the engine size is large and cannot be compactly mounted above an aircraft wing
Solution Approach 1:
The patent inverts the conventional axial arrangement by using a reverse core configuration where the turbine is positioned ahead of the compressor in the airflow path, and components are arranged radially rather than axially. This inversion enables compact mounting above the wing while maintaining functional efficiency.
Solution Approach 2:
The patent transitions from a one-dimensional axial arrangement to a two-dimensional radial arrangement, with components positioned at different radial distances from the rotation axis. This dimensional change allows for compact packaging while preserving the functional relationships between components.
2Volume of moving object
If the core engine is centered on an axis parallel to the fan axis, then the alignment is simple, but the engine cannot achieve optimal compact mounting above the wing
Solution Approach 1:
The patent employs asymmetric alignment where the core engine axis is deliberately offset and angled relative to the fan axis. This asymmetric configuration optimizes the engine's footprint for mounting above the wing while maintaining proper airflow paths and component clearances.
3Volume of moving object
If the inlet duct is positioned close to the fan inlet, then the engine is more compact, but the airflow path becomes complex and difficult to manage
Solution Approach 1:
The patent segments the airflow paths by providing separate inlet ducts for the fan and core engine, with distinct turning sections for each. This segmentation allows for compact positioning while managing the complexity of different airflow paths independently.
Solution Approach 2:
The patent introduces turning sections as intermediary components that redirect airflow from the inlet ducts into the respective engine sections. These intermediaries simplify the overall airflow management by providing dedicated turning paths for fan and core airflows.
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 allows for a compact, integrated engine mounting above the wing, improving lift and propulsion efficiency while maintaining a compact design.
Implementation Method 1
a particle separator is positioned to allow removal of impurities from the air prior to it turning into the core compressor section
Implementation Method 2
a free turbine is positioned downstream of the core engine turbine. The free turbine receives products of combustion from the core engine turbine, and drive the fan
Implementation Method 3
the free turbine drives the fan rotor through a gear reduction
Data Source
AI summary
A gas turbine engine has a fan inlet and a fan configured to deliver air to an exhaust nozzle. A core gas turbine engine. including in serial order extending further into the engine, a core turbine section, a combustor and a core compressor section. A core engine inlet duct is spaced from the fan inlet. A method is also described.