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Cooled wall of a turbine component and a method for cooling this wall

A technology for cooling walls and turbines, which is applied in the cooling of turbine/propulsion devices, the cooling of engines, combustion methods, etc., can solve problems such as infeasible convection cooling features, and achieve the effect of achieving coverage and reducing temperature gradients

Active Publication Date: 2017-08-25
ANSALDO ENERGIA SWITZERLAND AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This scheme presents a fairly flexible system, but the simplistic convective cooling feature is not feasible for state-of-the-art first stage components

Method used

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  • Cooled wall of a turbine component and a method for cooling this wall
  • Cooled wall of a turbine component and a method for cooling this wall
  • Cooled wall of a turbine component and a method for cooling this wall

Examples

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Embodiment Construction

[0057] figure 1 , 2 and 3 show a first embodiment of the claimed invention, i.e. a cooling wall for a turbine component (heat exchange device for a turbine component) comprising a first layer 3 of serpentine cooling channels for the coolant, a second Layer 5 is used for the serpentine cooling channels of the coolant. These passages are tubes. Each of the serpentine cooling channels in the first layer 3 includes an inlet 1 and an outlet 8 . Each of the serpentine cooling channels of the second layer 5 comprises an inlet 9 and an outlet 7 . Each channel of the first layer comprises a first 90 degree bend 2 positioned close to the inlet 1 of each channel of the first layer. Each channel of the first layer includes a second 90-degree bend positioned adjacent to the outlet 8 of each channel of the first layer, and each channel of the second layer includes a second 90-degree bend positioned adjacent to each channel of the second layer. The third 90 degree bend of the entrance 9...

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PUM

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Abstract

A cooled wall of a turbine component includes a first layer of channels for a coolant arranged along a side of the wall facing to a flow of hot gas, the first layer of channels having a serpentine shape, each channel of the first layer having an inlet and an outlet; a second layer of channels for the coolant disposed further from the flow of hot gas than the first layer, each channel of the second layer having an inlet and an outlet, the outlet of each of the channels of the first layer being in fluid communication with corresponding inlet of associated channel of the second layer creating a bend for changing a direction of the coolant leaving the channel of the first layer when entering the channel of the second layer.

Description

technical field [0001] The invention relates to cooling walls for turbomachine components. Background technique [0002] A general task in the development of heavy-duty gas turbine engines is to increase the efficiency, power output and life of the components of the turbine. The temperature hot gas level at the turbine inlet section of the state of the art is 1800-1900K, which is well above the thermal stability limit of the turbine material and only allows with reasonable coolant consumption using a highly sophisticated cooling system reach the desired lifespan. However, the introduction of a cooling system inevitably provides a temperature gradient across the staves and thus introduces thermal stresses, it is the task of the cooling system to provide both the lowest temperature and the smallest level of temperature non-uniformity for an acceptable lifetime s reason. [0003] Such components of gas turbines as the combustor liner and first stage guide vanes due to the hi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/18F01D9/02F23R3/00
CPCF01D5/189F01D9/02F23R3/002F05D2260/201F01D5/187F01D25/12F05D2250/185F23R2900/03043F05D2260/204F02C7/12F23R2900/03045F05D2260/20F01D5/18F01D9/041F01D25/14
Inventor A·塞德洛夫M·普洛迪斯蒂O·纳兹恩
Owner ANSALDO ENERGIA SWITZERLAND AG