Gas Turbine Hula Seal Cooling via Circumferential Flow
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Solution Overview
Problem
Gas turbine combustion systems face temperature-related issues due to hot combustion gases, particularly affecting hula seals and caps, where conventional cooling methods require significant quantities of cooling air.
Innovation Solution
A gas turbine combustion system design featuring a first member with an exterior and interior surface defining a wall, including a central area, where a cooling gas is directed through passageways oriented in a direction other than directly towards the central area, creating a circumferential flow to effectively cool hula seals and caps without excessive cooling air usage.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If conventional cooling arrangements are used to cool hula seals and caps, then the temperature of these components is reduced, but significant quantities of cooling air are required
Solution Approach 1:
The cooling system directs cooling air flow to specific localized areas where heat generation occurs. The cooling passages are configured to deliver cooling air precisely to the hula seal and cap regions that require cooling, rather than cooling entire components uniformly, thereby reducing the total quantity of cooling air needed while maintaining effective temperature control of critical components.
Solution Approach 2:
The invention utilizes the circumferential dimension by directing cooling air flow in a circumferential pattern around the combustion chamber. The cooling passages are oriented to deliver cooling air along the circumferential direction, creating a cooling film that effectively cools the hula seal and cap surfaces through circumferential convection, reducing the total cooling air quantity required compared to traditional axial or radial cooling approaches.
2Temperature
If cooling arrangements are designed to deal with particular cooling needs, then effective cooling is achieved, but the system complexity increases
Solution Approach 1:
The cooling passages in the first member are designed to serve multiple functions simultaneously. The same cooling passages that deliver cooling air to the combustion chamber also provide cooling to the hula seal and cap components. This multi-functional design achieves effective cooling of specific components without requiring separate dedicated cooling systems, thereby avoiding increased system complexity while maintaining cooling effectiveness.
Solution Approach 2:
The invention merges the cooling functions for the combustion chamber and the hula seal/cap components into a single integrated cooling arrangement. The cooling passages are configured to distribute cooling air to multiple target areas through a unified system, combining what could have been separate cooling subsystems into one cohesive structure, thus achieving effective component-specific cooling without proportionally increasing system complexity.
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 reduces temperature impacts on hula seals and caps, potentially extending their lifespan, reducing the need for frequent replacements, and optimizing gas turbine efficiency by minimizing cooling air requirements, while also controlling hot gas ingestion.
Implementation Method 1
A source of a cooling gas is in fluid communication with at least the exterior surface of the first member... The at least one passageway provides at least one passageway for the cooling gas to flow from the exterior surface of the first member through the wall of the first member to the substantially open space
Data Source
AI summary
Cooling is provided for a gas turbine combustion system that includes a first member, such as a liner, having exterior and interior surfaces that define a wall therebetween and a central area. A second member, such as a cap, is located adjacent that interior surface. A source of cooling gas is in fluid communication with the exterior surface of the first member. An open space, in which is located a hula seal, is located between the interior surface of the first member and the second member. At least one opening in the wall of the first member provides a passageway for the cooling gas from the exterior surface of the first member to the open space. The passageway has a directional axis along which the cooling gas flows and is discharged into the open space. The directional axis is substantially oriented in a direction other than a direction towards the central area of the first member.