Gas Turbine Accessory System Internal Integration
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Solution Overview
Problem
Existing gas turbine engine accessory systems face challenges in efficient integration and placement, leading to aerodynamic losses and increased aircraft drag due to external power device protrusions.
Innovation Solution
An integrated accessory system with a multi-pad mount and internal power devices, utilizing a gear box, device shaft, and right angle gear set to transmit and convert power within the engine casing, allowing for compact packaging and reduced drag by eliminating external protuberances.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If power devices are mounted externally on the gas turbine engine, then ease of access and maintenance is improved, but aerodynamic drag increases due to external protrusions
Solution Approach 1:
The power devices are nested within the engine casing, specifically mounted on the interior surface of the casing. This nesting approach allows the devices to be protected from environmental factors and reduces aerodynamic drag by eliminating external protrusions, while still providing access through designated openings in the casing.
Solution Approach 2:
The invention transitions from a radial mounting arrangement (external to the engine) to an axial/internal mounting arrangement (inside the engine casing). This dimensional change moves the power devices from the external surface into the internal volume of the engine, reducing the aerodynamic footprint while maintaining functional accessibility.
2Object-affected harmful factors
If power devices are integrated internally within the engine casing, then aerodynamic drag is reduced, but device complexity and integration difficulty increase
Solution Approach 1:
The engine casing is segmented into distinct mounting zones with designated openings for power devices. This segmentation allows for modular integration where power devices can be independently mounted and accessed without requiring complex reconfiguration of the entire engine assembly, thus reducing overall integration complexity.
Solution Approach 2:
The internal mounting structure is designed with universal features that can accommodate different types and sizes of power devices. The standardized mounting interfaces and openings provide multi-functionality, allowing the same integration framework to support various power device configurations without requiring custom solutions for each device type.
3Device complexity
If power devices are mounted externally, then structural simplicity is maintained, but packaging efficiency and aerodynamic performance deteriorate
Solution Approach 1:
By nesting power devices within the engine casing volume, the invention utilizes previously unused internal space for housing these components. This nesting approach improves packaging efficiency by consolidating components within the existing engine envelope rather than requiring additional external space, while the structural simplicity is maintained through straightforward mounting to the casing interior surface.
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 solution enables efficient power transmission and conversion within the gas turbine engine, reducing aerodynamic losses and drag by integrating power devices internally, enhancing the engine's aerodynamic efficiency and packaging.
Implementation Method 1
The integrated accessory system may include a gear box, a device shaft, and a right angle gear set
Data Source
AI summary
In one embodiment, a gas turbine engine may include an accessory system integrated in a frame between a bypass flow path and a core flow path. A shaft may be provided between the accessory system and a core shaft of the gas turbine engine. The integrated accessory system may include power devices such as motors and generators, among other types of devices. The gas turbine engine may have more than one device spaced at various circumferential locations. In one non-limiting example, two power devices may be spaced 180 degrees apart. In some embodiments, a shaft and gearing may be provided to a location such as a frame in preparation to receive a power device at a later time.