COOLING STRUCTURE FOR RADIAL TURBINE

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COOLING STRUCTURE FOR RADIAL TURBINE - A simplified explanation of the abstract

This abstract first appeared for US patent application 18610437 titled 'COOLING STRUCTURE FOR RADIAL TURBINE

Simplified Explanation:

The patent application describes a cooling structure for a radial turbine that includes a partition wall between a compressor and the turbine. A through hole in the partition wall supplies compressed air to cool the turbine's rear surface. The through hole is inclined in the turbine's rotational direction.

The cooling structure includes a partition wall and a through hole for supplying compressed air to cool the turbine.
The through hole is inclined in the rotational direction of the turbine.
The angle of inclination is between 40° to 80° with respect to the rotation axis of the turbine.

Potential Applications: This technology can be applied in various radial turbine systems where cooling of the turbine is necessary to improve efficiency and performance.

Problems Solved: 1. Efficient cooling of the radial turbine. 2. Enhanced performance and longevity of the turbine. 3. Optimal utilization of compressed air for cooling purposes.

Benefits: 1. Improved efficiency and performance of radial turbines. 2. Extended lifespan of turbine components. 3. Enhanced overall system reliability.

Commercial Applications: Cooling systems for radial turbines in aerospace, automotive, and power generation industries can benefit from this innovative technology, leading to more efficient and reliable turbine operations.

Questions about Cooling Structure for a Radial Turbine: 1. How does the inclined through hole improve the cooling efficiency of the radial turbine? 2. What are the potential cost savings associated with implementing this cooling structure in turbine systems?

Original Abstract Submitted

A cooling structure for a radial turbine is equipped with a partition wall arranged between a compressor and the radial turbine, and a through hole formed in the partition wall supplying a part of air compressed by the compressor to the rear surface of the radial turbine as cooling air. The through hole is inclined in a rotational direction of the radial turbine in the range of 40° to 80° with respect to a rotation axis of the radial turbine.