Turbine Vane Trailing Edge Turbulence Elements
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Solution Overview
Problem
Existing turbine blades for gas turbines face challenges in efficient cooling with minimal coolant usage and casting core stability during production, as larger openings for coolant flow lead to increased coolant consumption and reduced core stability.
Innovation Solution
Incorporating turbulence elements with concave inflow sides upstream of the trailing edge openings to increase pressure loss and heat transfer, allowing for larger openings without increased coolant consumption, and using a casting core with narrower first openings and wider separating webs for enhanced stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If the openings at the trailing edge are enlarged to improve coolant flow, then the coolant consumption increases, but the casting core stability deteriorates
Solution Approach 1:
The patent applies local quality by creating turbulence elements with specific concave geometries at localized positions upstream of the trailing edge openings. These turbulence elements are strategically placed only in regions where enhanced mixing is needed, rather than uniformly throughout the entire coolant path. This localized intervention improves coolant distribution and heat transfer efficiency without requiring overall enlargement of all openings, thus maintaining casting core stability while achieving better cooling performance in specific critical areas.
2Loss of energy
If the openings at the trailing edge are enlarged to reduce flow resistance, then the coolant consumption increases, but the pressure loss increases
Solution Approach 1:
The patent utilizes curvature by designing turbulence elements with concave surfaces that face the incoming coolant flow. These curved geometries create rotational flow patterns and enhance mixing efficiency as the coolant passes through. The concave shapes are specifically engineered to generate optimal turbulence intensity without causing excessive pressure loss, thereby improving heat transfer while maintaining acceptable energy efficiency and controlling coolant consumption.
3Stability of the object's composition
If the separating webs between openings are thin to maintain opening size, then the casting core becomes unstable, but the coolant flow is restricted
Solution Approach 1:
The patent applies preliminary action by introducing turbulence elements upstream of the trailing edge openings before the coolant reaches the separating webs. These turbulence elements pre-condition the coolant flow by creating mixing and rotational patterns in advance, which enhances the effectiveness of the coolant when it eventually passes through the openings and along the separating webs. This preliminary intervention ensures that even with thinner, more stable separating webs, the overall cooling efficiency is maintained or improved due to the enhanced mixing occurring earlier in the flow path.
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 solution achieves efficient cooling with reduced coolant consumption and increased stability of the casting core, preventing breakage and enabling robust handling, while maintaining the efficiency of the gas turbine.
Implementation Method 1
several turbulence elements are provided upstream of the webs, each having a coolant flow arriving there facing the inflow side, which is at least partially concave
Implementation Method 2
increase the pressure loss and heat transfer in the coolant flow
Data Source
Figure 1~2
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Figure 5~6
AI summary
The invention relates to a turbine vane having a novel interior structure. The invention further relates to novel turbulence elements (42) connected directly upstream of openings (28) disposed at the rear edge (20) of the vane blade (16) of the turbine vane. The same are disposed in a sequence, each having a flow side (44) against which a coolant (40) flows and which is at least partially arched in a concave manner according to the invention. Preferably, the turbulence elements (42) are configured in a crescent-shaped manner. This aerodynamically particularly unfavorable shape of the turbulence elements (42) causes increased pressure loss, thus complicating the through-flow of coolants. This makes it possible to enlarge the openings (28) without resulting in an increased consumption of coolant. The invention also provides a substantially more stable casting core (110), since the openings (130) required in the casting core (110) for the production of the webs (30) of a turbine vane may now be placed at further distances than before. This results in higher stability of the casting core (110) in the region of the casting core rear edge (120), thus the same is less prone to breakage in said region, and thus may be handled in a more robust manner.