Turbomachine Blade Cooling Circuit Layout
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Solution Overview
Problem
High-pressure turbine blades in turbomachine engines face severe temperature and pressure conditions, leading to the need for enhanced cooling systems to maintain strength and efficiency.
Innovation Solution
The turbine blade design incorporates multiple cooling circuits, including upstream, central, median, downstream, and lateral circuits, with distinct lateral cavities and conduits that form a trombone layout, providing efficient air distribution and thermal protection, and featuring turbulence promoters and calibrated passages for improved heat exchange.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If cooling circuits are added to improve cooling efficiency, then temperature control improves, but device complexity increases
Solution Approach 1:
The cooling system is divided into multiple independent circuits (upstream, central, downstream, lateral) that can be designed and optimized separately. Each circuit serves specific regions of the blade, allowing targeted cooling without requiring a single complex system to cover the entire blade surface.
Solution Approach 2:
Multiple cooling circuits are nested within the blade structure, with conduits and cavities arranged in concentric or overlapping patterns. The lateral cavities are positioned between the intrados wall and the extrados wall, creating a nested configuration that maximizes cooling surface area while minimizing the overall volume occupied by cooling infrastructure.
2Strength
If blade strength at high temperature is improved through redesign, then mechanical strength increases, but device complexity increases
Solution Approach 1:
The blade employs composite construction combining metallic airfoil sections with integrated cooling circuits and thermal barrier structures. The combination of structural metallic components and cooling functionality creates a composite system that achieves high-temperature strength while managing thermal loads through the integrated cooling architecture.
Solution Approach 2:
The cooling system transitions from two-dimensional surface cooling to three-dimensional volumetric cooling by introducing internal conduits and cavities throughout the blade thickness. This dimensional expansion allows cooling air to penetrate deep into the blade structure, providing thermal protection throughout the volume rather than just at the surface.
3Reliability
If cooling air is distributed through multiple circuits, then cooling uniformity improves, but air flow management complexity increases
Solution Approach 1:
Each cooling circuit is designed with specific characteristics tailored to the thermal requirements of its designated blade region. The upstream circuit addresses leading edge heating, the central circuit handles the mid-section, the downstream circuit manages the trailing edge, and lateral cavities protect specific sidewall areas. This localized optimization ensures uniform cooling across the entire blade surface.
Solution Approach 2:
The lateral cavities act as intermediary thermal management elements positioned between the intrados and extrados walls. These cavities receive cooling air from the cooling circuits and distribute it laterally along the blade, serving as intermediate distribution channels that balance the cooling flow between different blade surfaces and regions.
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 design enhances cooling efficiency, increases mechanical strength, and reduces thermal stresses by ensuring uniform air distribution and thermal protection across the blade, effectively managing high-temperature conditions.
Implementation Method 1
This cooling is achieved by circulating cool air drawn off from the turbojet upstream from combustion, inside these blades. This air is inlet at the root of the blade and is routed along an internal circuit in the blade to cool it
Implementation Method 2
it is evacuated outside the blade through drillings passing through the wall of this blade and distributed on this wall
Implementation Method 3
an upstream lateral cavity and a downstream lateral cavity extending along the intrados wall to form a heat shield
Data Source
AI summary
A turbine blade of a turbine engine such as a turbojet engine, comprising: a root supporting a blade and extending in a wingspan direction, ending in a vertex, the blade comprising a leading edge and a trailing edge, with a pressure side wall and a suction side wall separated from one another and connecting the leading edge (17) to the trailing edge, the blade also comprising: cooling ducts in which air collected at the blade root circulates; first and second inner side recesses running along the pressure side wall in order to form a heat shield spaced apart from one another along the pressure side wall; and at least one duct extending from the pressure side wall to the suction side wall between the first and second side recesses.