Gas Turbine Guide Vane Cover Plate Cooling via Plenum Leakage
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing gas turbine technologies require complex and labor-intensive cooling methods for guide vanes and rotor blades, particularly for the cover plates, which are crucial due to high hot gas temperatures, but these methods are inefficient and costly.
Innovation Solution
A simplified cooling system is implemented using a throttle element in the first plenum to control cooling medium pressure, allowing targeted leakage of cooling medium to cool the cover plate before it enters the hot-gas duct, and a second plenum connected to the hot-gas duct via throttling means, with sealing strips and a stepped gap to enhance cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If complex cooling methods (special cooling bores, impingement cooling techniques) are used for the cover plate, then cooling effectiveness is improved, but manufacturing and assembly effort increases significantly
Solution Approach 1:
The invention extracts the cooling function from complex internal cooling channels and impingement structures, achieving cooling through a simple leakage mechanism from the first plenum. The cooling effect is obtained by allowing controlled leakage of cooling medium from the plenum space above the cover plate, eliminating the need for complex cooling bore structures.
Solution Approach 2:
The cooling medium automatically leaks from the first plenum to cool the cover plate without requiring active control mechanisms or complex cooling systems. The system uses the natural pressure differential and leakage path to achieve cooling, making the cover plate self-cooling through its own structural design.
2Loss of energy
If targeted cooling of the cover plate is implemented, then heat management efficiency is improved, but device complexity increases
Solution Approach 1:
The invention applies cooling locally to the cover plate by allowing leakage of cooling medium specifically from the first plenum above the cover plate. This localized cooling approach targets the heat-affected area directly without requiring system-wide cooling modifications, improving heat management efficiency while keeping the overall system simple.
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 solution effectively and efficiently cools the cover plate using controlled leakage of cooling medium, reducing manufacturing and assembly complexity while maintaining effective heat management.
Implementation Method 1
cooling of the cover plate by cooling medium escaping in a targeted manner from the first plenum
Implementation Method 2
the first means comprising a throttle element which throttles the flow of the cooling medium through the inlet in the cover plate
Data Source
Figure 1
Figure 2
Figure 3~5
AI summary
The invention relates to a gas turbine comprising a guide vane (20) that is mounted on a vane support (38) and encompasses an airfoil (22) which extends in a radial direction from a cover plate (21) inward into a hot gas duct (44). A cooling medium, especially cooling air, flows through the interior of the airfoil (22). Said cooling medium flows through an access point (43) in the vane support (38) into a first plenum (41) located above the cover plate (21) and from there into the interior of the airfoil (22) via an inlet (36) located within the cover plate (21). In order to more easily cool the cover plate (21) in such a guide vane, first means (34, 35; 35a, 43) are provided for controlling the pressure of the cooling medium in the first plenum (41), and second means (42, 45, 46) are used which cause the cover plate (21) to be cooled by means of cooling medium that escapes in a targeted manner from the first plenum (41).