Gas Turbine Guide Vane Sealing and Cooling Design
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Solution Overview
Problem
Current guide vanes for gas turbine engines face challenges in sealing and cooling efficiency, particularly in high-temperature environments, where existing designs often result in leakage and seal strip damage due to thermal expansion and stress.
Innovation Solution
The guide vane design incorporates an inner and outer platform with strategically placed seal slots and an airfoil structure, featuring a closed loop configuration for seal strips and internal cooling channels with turbulator ribs and pin fins to enhance sealing and cooling efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If seal strips are used in conventional guide vane designs, then sealing is achieved, but seal strip damage occurs due to thermal expansion and stress in high-temperature environments
Solution Approach 1:
The patent changes the geometric parameters of the seal slot configuration from conventional single or linear slots to a closed loop configuration with multiple segments. This parameter change allows the seal strips to accommodate thermal expansion and stress through the distributed geometry, preventing damage while maintaining sealing reliability in high-temperature environments
Solution Approach 2:
The patent segments the seal slot into multiple distinct slots (first, second, and third outer seal slots) arranged in a closed loop configuration. This segmentation allows each seal strip to experience reduced individual stress while collectively providing comprehensive sealing, thereby preventing seal strip damage without compromising sealing effectiveness
2Temperature
If conventional cooling designs are used, then cooling is provided, but cooling efficiency is insufficient in high-temperature environments
Solution Approach 1:
The patent applies local quality by implementing cooling channels at specific locations within the guide vane structure, including regions served by the closed loop seal slots. This targeted cooling approach delivers cooling efficiency where thermal loads are highest, effectively managing temperature in critical areas without requiring uniform cooling throughout the entire component
Solution Approach 2:
The patent implements nested cooling channels within the guide vane structure, where cooling passages are embedded inside the vane body and interconnected with the external cooling system. This nesting arrangement maximizes cooling surface area and heat transfer efficiency within the constrained geometry of the guide vane, enabling effective thermal management in high-temperature environments
3Power
If guide vanes operate in high-temperature environments, then power generation is maintained, but leakage increases and operational efficiency decreases
Solution Approach 1:
The patent implements a dynamic seal slot configuration that adapts to thermal conditions through its closed loop geometry with multiple segments. As the guide vane experiences thermal expansion in high-temperature operation, the segmented closed loop structure dynamically adjusts to maintain optimal seal contact, preventing gas leakage and preserving power generation efficiency without requiring active control mechanisms
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 improves sealing by allowing for thermal expansion and reduces seal strip damage, while the internal cooling features enhance heat management, leading to increased durability and operational efficiency in high-temperature conditions.
Implementation Method 1
internal cooling channels with turbulator ribs and pin fins to enhance sealing and cooling efficiency
Implementation Method 2
turbulator ribs
Implementation Method 3
improves sealing by allowing for thermal expansion
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A guide vane (200, 300, 400, 500, 700) in a gas turbine engine (100) includes an inner platform (202), an outer platform (204), and an airfoil (206) extending therebetween. Side surfaces (302, 304) of the inner platform and outer platform between the guide vane (300) and an adjacent guide vane define a first seal slot (310, 318), a second seal slot (312, 320), and a third seal slot (314, 322) forming a closed loop having three corners (316, 324). At least one of the corners is rounded. The guide vane (500, 600) includes turbulator ribs (504) and pin fins (506, 604) disposed in an airfoil interior (406). The pin fins (604) are disposed in a region of a trailing edge (212). The inner platform defines film cooling holes (410) disposed at an outer surface (408) facing the airfoil. The film cooling holes are arranged in a fan shape. An inner surface (804) of the inner platform and an outer surface (704) of the outer platform include impingement cooling ribs (802, 702) The inner platform protrudes further towards upstream in a flow direction than the outer platform.