Angled Core Gas Turbine Engine Mounting for Aircraft Survivability
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Solution Overview
Problem
Conventional gas turbine engine configurations are limited in their ability to accommodate alternate aircraft architectures, as they are designed for specific wing and fuselage configurations, restricting the flexibility in mounting locations and potentially compromising aircraft survivability due to the risk of engine failure fragmentation.
Innovation Solution
The proposed solution involves a unique configuration where two gas turbine engine cores are mounted at angled positions relative to each other, with each core positioned outside the other's 'burst zone' to prevent interference and ensure survivability, utilizing a reverse flow gas turbine engine design with angled propulsor and engine axes, allowing for alternate aircraft architectures and side-by-side mounting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If conventional gas turbine engine configurations are used, then engine operation is reliable, but adaptability to alternate aircraft architectures is limited
Solution Approach 1:
The patent applies asymmetry by skewing the engine core axis relative to the propulsor axis, creating an asymmetric mounting configuration that enables alternate aircraft architectures. This asymmetric arrangement allows the engine to be mounted in non-conventional positions while maintaining proper operation, thereby improving adaptability without significantly increasing complexity
Solution Approach 2:
The patent introduces a new dimensional aspect by angling the engine core axis at approximately 30 degrees relative to the propulsor axis. This angular offset creates a three-dimensional mounting configuration that accommodates alternate aircraft architectures, transforming the traditional coplanar arrangement into a spatial configuration that provides architectural flexibility
2Adaptability or versatility
If engines are mounted closer together to enable alternate architectures, then adaptability improves, but risk of fragmentation interference increases
Solution Approach 1:
The patent converts the potential harm of fragmentation into a beneficial design constraint by defining burst zones and establishing minimum angular separations. The skew angle configuration naturally positions engines such that their burst zones do not overlap, transforming the fragmentation risk into a geometric solution that simultaneously enables close mounting while ensuring safety
Solution Approach 2:
The patent applies preliminary anti-action by pre-defining burst zones around each engine and configuring the skew angle to ensure engines are positioned outside each other's burst zones. This preventive geometric arrangement eliminates fragmentation interference before it can occur, allowing engines to be mounted in close proximity without safety concerns
3Adaptability or versatility
If engine cores are positioned at angled positions, then mounting flexibility improves, but manufacturing and assembly difficulty increases
Solution Approach 1:
The patent applies parameter changes by establishing a specific skew angle parameter (approximately 30 degrees) between the engine core axis and propulsor axis. This standardized angular parameter provides mounting flexibility while maintaining manufacturability, as the fixed angle can be incorporated into the engine design and assembly fixtures, reducing the complexity that would arise from arbitrary angular configurations
Data Source
AI summary
A propulsion system for an aircraft includes first and second turbine engines mounted within a fuselage of the aircraft. The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor axis. The second turbine engine includes a second engine core and a second propulsor disposed about a second propulsor axis parallel to the first propulsor axis. The first engine core and the second engine core are mounted at an angle relative to corresponding ones of the first and second propulsor axes.