Turbine Airflow Modulation via Thermal Inserts
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Solution Overview
Problem
Existing gas turbine engine cooling systems are inefficient as they require a network of valves and pipes, increasing engine weight without adequately offsetting the negative impacts, and do not effectively modulate cooling fluid flow based on temperature changes.
Innovation Solution
A flow modulation insert within the airfoil or shroud of the gas turbine engine that shifts position based on temperature changes, using materials with varying coefficients of thermal expansion or shape memory alloys to control the flow of cooling fluid, allowing for increased cooling during high temperatures and reduced flow during lower temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If a network of valves and pipes is used to provide cooling flow to engine components, then cooling effectiveness is improved, but engine weight increases
Solution Approach 1:
The patent extracts the cooling flow control function from the traditional valve-and-pipe network and integrates it directly into the turbine component structure itself. The turbine component includes internal cooling passages and flow control features built into the component geometry, eliminating the need for separate external cooling systems with multiple valves and pipes, thereby reducing engine weight while maintaining cooling effectiveness.
Solution Approach 2:
The patent merges the cooling flow delivery function with the turbine component structure. The turbine component serves dual purposes: generating power from combustion gases and providing its own cooling through integrated internal passages. This consolidation eliminates separate cooling system components, reducing overall system weight and complexity.
2Use of energy by moving object
If cooling fluid flow is restricted during non-high power conditions, then specific fuel consumption is reduced, but cooling effectiveness during high power conditions may be compromised
Solution Approach 1:
The patent incorporates dynamic flow control features within the turbine component that allow the cooling flow rate to vary automatically with operating conditions. The internal geometry includes adjustable or responsive elements that modulate cooling flow based on the power demand and thermal loading of the component, ensuring adequate cooling during high power conditions while minimizing cooling flow during cruise or low power operations to reduce fuel consumption.
Solution Approach 2:
The patent changes the cooling flow parameter dynamically based on operating conditions. The system monitors or responds to changes in power demand, combustion gas temperature, or component thermal state and adjusts the cooling flow rate accordingly, optimizing the balance between cooling effectiveness and fuel efficiency across different operating regimes.
3Ease of operation
If a traditional valve and pipe network is used for cooling, then cooling flow can be controlled, but device complexity increases
Solution Approach 1:
The patent removes the complex external valve and pipe network from the cooling system and integrates the necessary flow control functions directly into the turbine component structure. The component itself contains internal passages, flow distributors, and control features that eliminate the need for separate external control mechanisms, thereby reducing system complexity while maintaining cooling flow control capability.
Solution Approach 2:
The turbine component is designed to perform multiple functions simultaneously: power generation from combustion gases, structural support, and cooling flow distribution. This multi-functionality consolidates what would traditionally require separate dedicated cooling system components into a single integrated unit, reducing overall system complexity.
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 solution reduces engine weight by eliminating unnecessary cooling fluid flow during non-high power conditions, improving efficiency and reducing specific fuel consumption by modulating cooling fluid flow effectively in response to temperature changes.
Implementation Method 1
such an insert that utilizes a difference in a coefficient of thermal expansion of the insert and the turbine section component to modulate the cooling flow
Implementation Method 2
such an insert that utilizes a shape memory alloy to modulate the cooling flow
Data Source
AI summary
Features and methods for modulating a flow of cooling fluid to gas turbine engine components are provided. In one embodiment, an airfoil is provided having a flow modulation insert for modulating a flow of cooling fluid received in a cavity of a body of the airfoil. In another embodiment, a shroud is provided comprising a cooling channel for a flow of cooling fluid and an insert that varies in position to modulate the flow of cooling fluid through the cooling channel. In yet another embodiment, a method for operating a gas turbine engine having a cooling circuit for cooling one or more components of the gas turbine engine comprises increasing power provided to the engine and decreasing power provided to the engine to modulate a position of a flow modulation insert located in the cooling circuit and thereby modulate the flow of cooling fluid through the cooling circuit.