Integrated Compressor Turbine Wheel Cooling
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Solution Overview
Problem
Existing gas turbine engine compressor impellers and radial inflow turbines face challenges such as increased physical dimensions, higher costs, unwanted impeller deflection, and inefficiencies in cooling, which affect performance and cycle efficiency.
Innovation Solution
A compressor turbine wheel design that integrates a compressor impeller with a radial inflow turbine, allowing for heat transfer via conduction and utilizing passages for air flow to cool the turbine, potentially reducing dimensions and costs while minimizing deflection and optimizing cycle efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If separate compressor impeller and radial inflow turbine designs are used, then functional requirements are met, but physical dimensions increase and costs increase
Solution Approach 1:
The patent combines the compressor impeller and radial inflow turbine into a single integrated wheel assembly. The impeller and turbine are positioned adjacent to each other on the same wheel, sharing common structural elements and mounting features, thereby reducing overall physical dimensions while maintaining separate functional capabilities.
Solution Approach 2:
The integrated wheel assembly serves multiple functions simultaneously: the impeller section compresses air while the turbine section extracts energy from exhaust gases. Both functions are performed by a single rotating component assembly, reducing the need for separate devices and minimizing space requirements.
2Temperature
If traditional cooling methods are used for the radial inflow turbine, then cooling is provided, but device complexity and costs increase
Solution Approach 1:
The integrated wheel assembly uses its own rotating structure to facilitate cooling. The impeller and turbine share common cooling passages and thermal management features built into the wheel itself, eliminating the need for external cooling systems and reducing overall device complexity.
Solution Approach 2:
Cooling passages are integrated within the internal structure of the wheel assembly, with cooling channels nested within the impeller and turbine sections. This nested arrangement provides effective cooling while minimizing external components and maintaining a compact design.
3Ease of manufacture
If integrated design is used, then physical dimensions are reduced and costs are reduced, but manufacturing precision requirements increase
Solution Approach 1:
The impeller and turbine are manufactured as a single integrated wheel assembly using additive manufacturing or other advanced fabrication processes. This merging approach reduces the number of separate parts requiring assembly, thereby reducing overall manufacturing costs despite the complexity of the integrated structure.
Solution Approach 2:
The patent utilizes advanced manufacturing parameters and processes, such as additive manufacturing, to produce the integrated wheel assembly with complex internal geometries and precise features. These parameter changes enable cost-effective production of high-precision integrated structures that would be difficult or expensive to manufacture using traditional methods.
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 integrated design reduces physical dimensions and costs, minimizes unwanted impeller deflection, and enhances performance by efficiently cooling the radial inflow turbine through conduction and air flow management, leading to improved cycle efficiency and tighter tip clearances.
Implementation Method 1
Air is compressed in the compressor(s)
Implementation Method 2
The exhaust gas rotates the turbine, which is typically used to turn a shaft and produce shaft work output
Implementation Method 3
The compressor turbine wheel may be configured to cool the radial inflow turbine by conduction from the radial inflow turbine to the compressor impeller
Implementation Method 4
A passage may extend between the aft inner surface and the forward inner turbine surface, the passage configured to direct flow of air between the compressor impeller and the radial inflow turbine
Data Source
AI summary
A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.