Gas Turbine Actuation via Jamming Device Fluid Evacuation
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Solution Overview
Problem
Current technologies for actuating turbine components in gas turbine engines, such as piezoelectrics, smart memory alloys, and mechanical joints, face limitations in generating sufficient force, requiring controlled temperature conditions, and creating aero surface discontinuities, making it difficult to adapt to changing operating conditions effectively.
Innovation Solution
A system and method utilizing an integrated jamming device with a flexible bladder and jammable media, where the media transitions from an unjammed to a jammed state by evacuating fluid, applying a compressive force to actuate turbine components, allowing their shape or profile to be adjusted in response to changing operating conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If piezoelectrics are used for actuation, then the component can be actuated, but insufficient force is generated to displace stiff structures
Solution Approach 1:
The patent combines multiple actuation mechanisms (piezoelectric elements, shape memory alloys, and mechanical joints) into a single integrated actuator assembly. This merging allows the weak forces from piezoelectrics to be amplified through mechanical leverage and combined with the force from shape memory alloys, achieving sufficient total force to displace stiff turbine component structures while maintaining reliable actuation effectiveness
Solution Approach 2:
The patent employs dynamic control of the actuator assembly by selectively activating different components (piezoelectric elements for precise positioning, shape memory alloys for force generation) based on real-time operating conditions. This dynamic activation strategy ensures that the actuator generates appropriate force levels for different actuation tasks, resolving the contradiction between force magnitude and actuation reliability
2Adaptability or versatility
If shape memory alloys are used for actuation, then the component can be actuated, but controlled temperature conditions are required which are challenging in aircraft engine environment
Solution Approach 1:
The patent utilizes the self-service principle by leveraging the natural thermal environment of the gas turbine engine to activate shape memory alloys. Instead of requiring external temperature control systems, the actuator assembly allows shape memory alloy components to respond autonomously to the engine's operating temperature variations, enabling component reconfiguration without adding complex temperature control machinery
Solution Approach 2:
The patent exploits parameter changes in the shape memory alloy materials by selecting alloys with specific transformation temperatures that correspond to different engine operating conditions. This allows the actuator to automatically adjust component configuration based on temperature parameter changes inherent to engine operation, achieving adaptability without external control complexity
3Ease of operation
If mechanical joints are used for actuation, then the component can be actuated with well controlled motion, but hinges and joints tend to open and create aero surface discontinuities
Solution Approach 1:
The patent replaces traditional rigid mechanical hinges and joints with flexible membrane structures that can bend and deform to achieve the required motion. These flexible shells maintain continuous aero surfaces by eliminating discrete joints that would create discontinuities, while still providing well-controlled motion through the elastic deformation characteristics of the membrane material
Solution Approach 2:
The patent substitutes traditional mechanical joint systems with an integrated actuator assembly that uses distributed piezoelectric elements and shape memory alloys to produce motion. This replacement eliminates the need for discrete hinges and joints, thereby removing the source of aero surface discontinuities while maintaining precise motion control through the collective action of multiple actuator elements
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
Enables efficient adaptation of turbine components to varying operating conditions, improving performance and efficiency by applying sufficient force without the need for controlled temperature conditions and minimizing aero surface discontinuities.
Implementation Method 1
The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder
Data Source
AI summary
A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.